ARTES-5.1 – ESA Telecom Technology Workplan ... - Emits - ESA

March 2009ARTES-5.1 – ESA Telecom TechnologyWorkplan 20091 IntroductionA key role of ESA in telecommunications is to promote a significant level of R&D activities to ensure thereadiness and competitiveness of European industry in the short and long term.ARTES Element 5.1, short ARTES 5.1, is the Agency’s main programme for preparatory development ofsatellite communications, and it covers the long term R&D activities. ARTES 5.1 activities containsignificant amount of industrial research and technical risk and are therefore fully funded.ARTES 5 is concerned with the early stages of development of systems and exploitation of new andpromising technologies for satellite communications. In several cases the ARTES 5 activities are acontinuation of a TRP activity. Within the TRP the components are developed and basic feasibility isdemonstrated, while within ARTES 5 the equipments are developed to breadboard or engineering modellevel. The further development to a space qualified or industrialised product is supported within the cofundedARTES 3-4 element.Through ARTES 5, ESA sponsors the exploitation of new technologies into equipment such that in the longterm the industry will be able to offer state-of-the-art equipment and systems at competitive prices. Itencompasses activities related to the development of subsystems and equipment for satellitecommunications.The Workplan 2009 addresses specifically the Technology and Equipment activities in support of theactivity lines defined in the Telecommunications Long Term Plan. The Workplan 2009 has beencoordinated with other ESA technology programs according to the E2E process described inESA/IPC(2008)61, rev.1. The activities are organized per application area with System, Space Segment -Platform, Space segment - Payload, Ground Segment and Application and Services being the main areas(see Annex 2).2 Distribution of Activities in the Workplan 2009The Workplan 2009 consists of in total 67 activities (including some carried forward from previous workplans). Priorities have been assigned to the activities to clearly identify those, which the Executiveconsiders should be implemented without further discussion. The complete Workplan 2009 is presented inAnnex 1 in tabular form. The descriptions of the activities in the Workplan 2009 are presented in Annex 2.Most of the activities are addressing the space segment for which the development of equipment using newtechnologies is connected with a relatively high risk in the early phases justifying the full funding offeredby the ARTES-5.1 program. Developments related to user terminals tend to be relatively close to the

Page 2market, hence the rather low number of such activities in the Workplan 2009. User terminal activities arewell covered in the co-funded ARTES-3/4.The System area covers networking and propagation. There are five activities related to communicationnetworks covering mobile satellite services, large broadband systems and IP based systems. There are twoactivities in the area of propagation.The activities in the Space Segment – Platform area are divided into platform – system and architecture,propulsion, AOCS, thermal, mechanical and power. The equipment developments are for geostationarysatellite telecommunication platforms, but some of the equipments are also of potential use on othersatellite platforms.The activities in the Space Segment – Payload are divided into antenna, repeater, TT&C and data handling.The antenna related activities address in particular multibeam antennas for high capacity satellites and thedevelopment of an unfurlable reflector of 4 to 7 m diameter for, for example, S-band digital audiobroadcast missions and C-band multibeam missions. The repeater activities address passive components,active high power equipment and one activity to on a Q/V band TWT.Five activities are proposed for development of different types of user terminals.3 ImplementationPhasing: Phasing of the contractual activities may be considered depending on the risk associated with thedevelopments, the maturity of the technologies and market perspectives.Parallel contracts: In accordance with the ARTES-5 Implementing Rules, parallel contracts will not beawarded in ARTES-5.1.Procurement Policy: The following procurement policies are foreseen for the proposed activities. Thedefinition of the measures is according to ESA/IPC(2005)87,rev.4(*):• C:• C1:• C2:• C3:• C4:Activities in open competition without any further restrictions.Activities in open competition limited to non-Large-System Integrators (LSIs) as prime. LSIs areallowed to participate as sub-contractors.Activities are in open competition, where a significant participation of non-LSIs is requested.Activity restricted to SMEs & R&D organisations, preferably in cooperation.Activities in open competition, subject to the SME subcontracting clause.(*) for full definitions please refer to text of this IPC paper.Priority: The Workplan 2009 consists of a number of activities assigned Priority 1 and a number assignedPriority 2. Activities assigned Priority 1 will be initiated on the initiative of the Executive. A planning forthe issue of the invitation to tender as well as the duration of the activity is stated in the heading of thedescription of each activity in Annex 2. The planning will also be published on the telecom web site.Priority 1 activities, for which industry and Participating States show an interest, will be implementedwithout undue delay. Such interest can be notified directly to the ARTES-5.1 Programme Office.Priority 2 activities will only be initiated either:1. on the explicit request of at least one delegation; or2. on the initiative of the Executive following consultation of the JCB.

Annex 1Page 1ANNEX 1SUMMARY TABLE FOR ARTES-5.1 ACTIVITIES IN WORKPLAN 2009ActivityRef.Title Cost PriorityCost (K€)(priority 1)Cost (K€)(priority 2)SYSTEM/ NETWORK / PROTOCOLSSystem, Networking and Management3A.022 MSS data terminals for ad-hoc networks 350 P2 0 350 C n/a3A.023 MIMO Hardware Demonstrator 1200 P1 1200 0 C 3Q3A.024 Consumer Interactive Service Optimisation for Large Satellite Networks 300 P2 0 300 C n/a3A.034 Techniques and Technologies for Multi-spot Beam Ku-band Satellite Networks 350 P1 350 0 C 4Q3A.035 Tool for hybrid mobile broadcasting system performance analysis and network dimensioning 300 P1 300 0 C 3Q3A.036 Security of broadband satellite systems for commercial and institutional applications 250 P1 250 0 C 4Q3A.037 Hardware demonstrator of the Fourth Generation Mobile Satellite Systems 2000 P2 0 2000 C n/a3A.038 All-IP Broadcast Satellite Networks Technologies and Demonstration 700 P1 700 0 C 3Qsubtotal 2800 2650Propagation3B.017 Propagation analysis tool for design of fixed and mobile multimedia systems 400 P1 400 0 C2 1Q3B.018 Characterisation of the MIMO channel for mobile systems 350 P1 350 0 C 1Q3B.021 Development of miniaturized microwave ground radiometers for SatCom ground stations 400 P2 0 400 C1 n/a3B.022 Physical-statistical models for mobile satellite communication systems below 10 GHz 250 P1 250 0 C1 3Qsubtotal 1000 400SPACE SEGMENT - GENERALPlatform - System and Architecture4A.021 ESD/electrical transients monitor 400 P1 400 0 C2 2Q4A.024 Improved level of information provided in TM 500 P1 500 0 C 2Q4A.028 Standard Satcom Provisions for Life-extension 400 P2 0 400 C n/asubtotal 900 400Propulsion System4B.029 Plastic liners for pressurant tanks (*) 400 P1 400 0 C1 2Q4B.034 Low Cost Fabrication Techniques for Titanium Propellant Tanks 500 P2 0 500 C n/a4B.035 Alternative Bi-Prop Regulator 500 P1 500 0 C1 2Q4B.036 Development of a Cost-Effective Hall-effect Propulsion Subsystem 300 P2 0 300 C 2Q4B.037 Propellant Simulant Assessment / Propellant Tank Offload 250 P1 250 0 C 2Q4B.038 MEMS-based Satellite Propellant Gauging System 1200 P1 1200 0 C1 2Qsubtotal 2350 800AOCS4C.015 Autonomous Orbit Determination and Station Keeping Control for Competitive Telecom Missions 600 P1 600 0 C 2Q4C.016 Robust Control Techniques for Large Telecom Satellites with Demanding Pointing Performance 400 P1 400 0 C 2Q4C.017 Graveyard and passivation strategies for GEO satellites 200 P2 0 200 C n/asubtotal 1000 200Proc.PolicyIntendedIssue

Annex 1Page 2ActivityRef.Title Cost PriorityCost (K€)(priority 1)Cost (K€)(priority 2)Proc.PolicyIntendedIssueThermal System4D.008 Loop Heat Pipe with Integrated Peltier Element 400 P1 400 0 C4 1Qsubtotal 400 0Mechanical System4E.029 Development of a versatile European Eddy Current Damper 400 P2 0 400 C1 n/a4E.031 Friction less lateral deployment hinge 330 P2 0 330 DN n/a4E.033 Moulding techniques for Telecommunications Antenna Reflectors 500 P1 500 0 C1 1Q4E.036 Fine Pointing and Trim Mechanism 700 P1 700 0 C1 3Q4E.037 Ultra Light Compact Shock Damping Device 400 P1 400 0 C1 3Qsubtotal 1600 730Power System4F.020 Quenching Circuit for Solar Array Power Arcing Events 200 P1 200 0 C 3Q4F.039 Solar array charging voltage limitation by neutralizer 200 P1 200 0 C 3Q4F.041 Flash over evaluation on large solar panels 900 P1 900 0 C 2Qsubtotal 1300 0SPACE SEGMENT - PAYLOADPayload - System and Architecture5A.011 On ground beam forming techniques 300 P1 300 0 C 1Q5A.015 Architectural Definition and Preliminary Design of a Future Flexible Multibeam Ka band payload 350 P1 350 0 C 2Q5A.016 Payload On Board Self Calibration Techniques 200 P1 200 0 C 4Qsubtotal 850 0Antenna5B.019 Large Deployable Antenna Integration on European Spacecraft 300 P2 0 300 C n/a5B.044 Antenna Reflectors using European Mesh 750 P2 0 750 C n/a5B.050 Polarisation flexible (dual linear/dual circular) feed system 350 P2 0 350 C n/a5B.065 Multiple beam port-to-beam synthesis methodology and antenna architectures 300 P2 0 300 C n/a5B.066 Active Multibeam Sparse Array Demonstrator 750 P1 750 0 C 3Q5B.067 Ku-band High power feed components 400 P1 400 0 C 2Q5B.068 Multi-mission and Multi-frequency reflector antennas 600 P1 600 0 C 3Q5B.069 Medium size unfurlable reflector antenna 1500 P1 1500 0 C 3Q5B.070 High accuracy Antenna Pointing System 350 P1 350 0 C 2Q5B.071 Ka-band integrated active feed for multiple beams antenna 600 P1 600 0 C 3Qsubtotal 4200 1700

Annex 1Page 3ActivityRef.Title Cost PriorityCost (K€)(priority 1)Cost (K€)(priority 2)Proc.PolicyIntendedIssueRepeater Equipment5C.070 Lightweight RF power cables with high phase stability 500 P1 500 0 C 1Q5C.085 Opto-microwave wideband reconfigurable receiver 2000 P1 2000 0 C 2Q5C.087 SSPAs with European GaN devices 1200 P1 1200 0 C 3Q5C.088 Low phase noise reference oscillatoR 500 P1 500 0 C 2Q5C.093 Compact High Power S-band Output Matrix 450 P2 0 450 C n/a5C.102 Input Filters for L-, S-band applications 400 P1 400 0 C1 4Q5C.103 Reduced Footprint SSPA for telecom payloads 600 P2 0 600 C n/a5C.104 High Temperature EPC for GaN SSPA application 600 P1 600 0 C 3Q5C.105 Modelling of Passive Intermodulation in Multicarrier operation 300 P1 300 0 C 4Q5C.106 Frequency Synthesizer Phase Noise Modelling 350 P1 350 0 C2 3Q5C.107 100 W Q/V-band TWT 500 P1 500 0 C1 4Q5C.108 High power Ka-band TWT with AlN collector 600 P2 0 600 C1 n/a5C.110 Extreme environment RF power cables for telecommunication payloads 500 P2 0 500 C1 n/asubtotal 6350 2150TT&C and Data Handling5D.016 Cryptographic processor for control of telecom processing payloads 700 P1 700 0 C 3Q5D.017 Safe Satellite Wireless Access point on launcher for intra S/C monitoring 500 P2 0 500 C2 n/asubtotal 700 500USER TERMINALS7-.006 Self-pointing, Planar Antenna for Television Reception 1000 P2 0 1000 C1 n/a7-.012 Integrated User Terminal for Interactive applications 600 P2 0 600 C1 n/a7-.015 Distributed receive antenna for vehicles 500 P2 0 500 C1 n/a7-.016 COSPAS/SARSAT antennas 350 P2 0 350 C1 n/a7-.017 Antenna radome for SATCOM user mobile terminals 400 P1 400 0 C1 3Q7-.018 Cost Effective Satellite Terminals for MESH Overlay Networking 1500 P1 1500 0 C1 3Qsubtotal 1900 2450TOTAL (k€) 25,350 11,980

Annex 2Page 1ANNEX 2ARTES 5.1 WORKPLAN 2009The activities are grouped into the following categories:1. SYSTEM/NETWORK/PROTOCOLS1.1 System, Networking and Management1.2 Propagation2. SPACE SEGMENT – GENERAL2.1 Platform – System and Architecture2.2 Propulsion System2.3 AOCS2.4 Thermal System2.5 Mechanical System2.6 Power System3. SPACE SEGMENT – PAYLOAD3.1 Payload – System and Architecture3.2 Antenna3.3 Repeater Equipment3.4 TT&C and Data Handling4. USER TERMINALS

Annex 2Page 21. SYSTEM/NETWORKS/PROTOCOLS1.1 System, Networking and ManagementRef. Activity Title Procurement Policy Budget(KEUR)3A.022(08.153.37)Objective:Planned TenderIssueMSS data terminals for ad-hoc networks Open Competitive Tender Type: C 350 Priority 2 15Estimated Duration(months)This activity is to assess the commercial viability of MSS data terminals contributing gateway capacity into terrestrial ad-hoc networks. The terminal cost, space segment costs and terminalperformance will be assessed for different terminal architectures, satellites networks, and different network topologies.Description: Several MSS satellites offering capacity in L-band and S-band exist or will soon be launched. Terminals for such systems may be developed to offer data capacity in the order of several 100’sof kbps. This capacity could be used within mobile or statically formed ad-hoc terrestrial networks. A mobile ad-hoc network (MANet) is a kind of wireless ad-hoc network and is a selfconfiguringnetwork of mobile routers/nodes (and associated hosts) connected by wireless links – the union of which form an arbitrary topology. The nodes are free to move randomly andorganise themselves arbitrarily; thus, the network's wireless topology may change rapidly and unpredictably. Such a network may operate in a standalone fashion, or may be connected to thelarger Internet. This connection to the Internet could be provided by the MSS data terminal. Such a node in an ad-hoc network is called a gateway node. Several terrestrial vendors currentlyoffer terrestrial based Wi-Fi or WiMax products able to form into mobile ad-hoc networks.The idea of this study would be to investigate the ability to build new type of MSS terminal that would integrate both the MSS functionality and the Wi-Fi/WiMax ad-hoc functionality. TheMSS data terminals would be based on existing building blocks such as existing multi-band antennas that work with Wi-Fi, WiMax and cellular networks, existing MSS terminals, andexisting Wi-Fi/WiMax components and software for acting as gateway node in the ad-hoc network. Other Wi-Fi/WiMax-only nodes in the vicinity of this gateway node would then be able toroute their traffic via satellite to the Internet.The study would look at handheld, vehicular mobile or fixed MSS terminals:• current commercially available mobile antennas, investigate the possible implications(design, prices, risk, …) of adding access to MSS satellites• evaluation of possible air interface options for satellite link• look at data rates that could be supported with each terminal and antenna combination• look into architectures and cost for including ad-hoc network functionality to this MSS data terminal• options for obtaining satellite capacity on existing and planned MSS satellites• assess possible applications that could be supported given the terminal costs and performances• analyse most appropriate network topologies suited to application scenarios• produce a development plan for parts of system requiring development such as development of terminal and hub hardware and software, air interface and protocols.NOTE: This activity has been designated as "Priority 2". Priority 2 activities will only be initiated on the explicit request of at least one delegation.

Annex 2Page 3Ref. Activity Title Procurement Policy Budget(KEUR)3A.023(08.153.11)Objective:Description:Planned TenderIssueMIMO Hardware Demonstrator Open Competitive Tender Type: C 1200 Priority 2 => 2Q2009Implement a hardware demonstrator to prove the feasibility and the benefits of MIMO techniques for satellite networks.Estimated Duration(months)Recent years have seen a dramatic increase in demand for new capacity in wireless networks, both in terms of numbers of users and in terms of enhanced capabilities for individual users. Thisdemand, together with the rise of new techniques for creating and exploiting diversity, has led to a situation in which the performance and design of wireless networks is increasinglydominated by considerations of interference. This issue is exacerbated by the tight limits on bandwidth and transmitter power typical of all wireless systems as well as the need to use smalland easy-to-deploy low-directivity antennas on the user side. For these reasons multi-user detection, which deals with the detection of data in interference channels, has become thecentrepiece of advanced signal processing techniques for enabling capacity growth in wireless networks. The contract (CN 20547) “MIMO Applicability to Satellite Networks” isinvestigating the potentials of MIMO techniques to broadcast to mobile systems. Preliminary outcomes are very promising showing a capacity improvement in the order of 50%.This activity is to demonstrate the advantages of MIMO techniques by building a demonstrator and operate it a realistic environment. The S-band broadcast multimedia to mobile is the targetapplication scenarios.The demonstrator shall implement a complete end-to-end system employing the selected MIMO technique. Of particular importance is also the implementation of a powerful channelemulator capable of faithfully reproducing the key characteristics of the selected satellite (and terrestrial if applicable) system. Both spatial and polarization channel diversity shall be includedtogether with a realistic satellite and user terminal antenna model which are the elements permitting the exploitation of such diversity.The modulator and demodulator unit shall implement the required algorithms capable of exploiting the MIMO channel diversity. The performance in terms of throughput and availability ofthe selected study case will be extensively analysed, after a careful tuning of the algorithm parameters.24

Annex 2Page 4Ref. Activity Title Procurement Policy Budget(KEUR)3A.024(08.153.38)Objective:Description:Planned TenderIssueConsumer Interactive Service Optimisation for Large Satellite Networks Open Competitive Tender Type: C 300 Priority 2 15Estimated Duration(months)To identify potential inefficiencies of the current DVB-RCS standard when applied to large and fully loaded satellite networks, and propose modifications/solutions to optimise the systemcost and increase the end-user QoS experience.So far the deployed DVB-RCS networks are limited to a few thousand users. Also, in most of these networks, the load (number of active users per MHz of satellite Bandwidth) is kept low inorder to limit the stress on the system. However, upcoming large Ka-band satellite networks as well as the need to reduce the cost of the service to be competitive for the consumer market,requires a large user population (> 10000 terminals) and a fully loaded system. DVB-RCS networks have not been tested under such conditions, and some inefficiencies may exist such as:i) long log-on and re-log-on timeii) excessive delay in assignment of capacity to usersiii) excessive signalling overhead due to the need to maintain network synchronization and reduce the network access reaction timeiv) excessive complexity of the network resource manager.In this activity a multi-spot beam network with capability to address population of users in excess of 100000 terminals shall be considered. The consumer access market shall be primarilyaddressed with user QoS requirements similar to current terrestrial access systems (like ADSL). In this scenario, the cost effectiveness of a network based on the current DVB-RCS standardshall be analysed together with its capability to deliver the required user QoS. To this end the service business case shall be derived and the major weak points identified. For the issues relatedto delivering the required user QoS, analysis and network simulations shall be carried out to quantify the issue. Techniques to improve the cost effectiveness and the end user QoS shall beproposed and its impact/benefits to the system assessed. Among the innovative techniques to be tested to improve the service, the integration of a random access channel with the DAMAchannel shall be considered.NOTE: This activity has been designated as "Priority 2". Priority 2 activities will only be initiated on the explicit request of at least one delegation.

Annex 2Page 5Ref. Activity Title Procurement Policy Budget(KEUR)Planned TenderIssueEstimated Duration(months)3A.034 Techniques and Technologies for Multi-spot Beam Ku-band Satellite Networks Open Competitive Tender Type: C 350 4Q 2009 12(09.153.22)Objective: To analyse mission opportunities of multi-beam Ku-band satellite communication systems; to derive optimum architectural design and system requirements in terms of services, flexibility andspace segment performance; to analyse, simulate and optimize system performance; to identify required technology improvements for Ku-band multi-beam payloads; to define payloadflexibility evolution and necessary developments.Description:Ku-band frequencies are less prone to atmospheric propagation effects than Ka-band. This makes Ku-band an option for areas with high annual rain rates (e.g. South East Asia, Africa, SouthAmerica and tropical regions) as an alternative to C-band for broadcast and VSAT networks. Two main streams of evolution can be foreseen for Ku-band satellite communication systems:i) a reinforcement of existing fleets of Ku-band satellites with a request for increased flexibility and efficiencyii) an introduction of a mix of advanced interactive and broadcasting services in Ku-band for those regions where the spectrum is still available or the Ku-band offers clear feasibility andavailability advantages.The activity will start with an analysis of the opportunity for this type of missions in particular targeting non-EU geographical areas, investigations of the propagation aspects and a review ofthe existing Ku-band multi-beam satellite technology (particularly on the payload and antenna side). Payload flexibility requirements, a system sizing and a high level architectural design ofthe payload will be derived based on a number of realistic user and traffic distributions and target coverage. Networking aspects relative to the combination of broadcast and interactiveservices shall also be tackled. A software emulator model of the payload shall be derived, including the electrical characterization of all the sub-systems with their flexibility aspects.Simulation tests shall then be performed to characterize the model in terms of input-output connectivity, transfer functions and signal to noise and intermodulation performance. The modelshall allow to trade-off different payload and sub-system configurations in terms of performances, complexity, flexibility, efficiency, mass, power and cost. Desirable technologyimprovements shall be identified to realise the mission opportunities in a cost efficient way.

Annex 2Page 6Ref. Activity Title Procurement Policy Budget(KEUR)Planned TenderIssueEstimated Duration(months)3A.035(09.153.23)SW tool for hybrid satellite/terrestrial mobile broadcasting system performance analysisand network dimensioningOpen Competitive Tender Type: C 300 3Q 2009 15Objective:Description:To develop a software simulation tool for the assessment of hybrid satellite/terrestrial mobile broadcast system performance. This tool shall contain functions allowing designers to derivesystem performance (coverage, service quality, availability) and to support them in the system dimensioning and trade-off analysis (satellite and terminal characteristics, complementaryterrestrial network deployment strategies).System engineers in the terrestrial and the satellite industry have traditionally worked with distinctive system performance assessment tools adapted to their specific scenarios. The licenses foroperation of hybrid satellite/terrestrial systems on the S-Band will be granted in Europe in the near future. In this scenario, there is a need to harmonise the way this system analyses are doneand also to introduce new methodologies allowing to model the interactions between the satellite and terrestrial signals.Tools available for terrestrial network deployment are based on ray tracing or statistical models. The first allows obtaining an accurate picture of the power level obtained in a specific area aslong as the environment is described with a high level of detail (building data bases). On the other hand, the statistical models do not require a detailed description of the environment but theyonly give a rough indication of the cell radius. Both methods give a probability of obtaining a certain power, but none of them take into account the physical layer behaviour in differentmobile conditions. Similarly for satellite dimensioning, the link budgets give an indication of the signal to noise ratio in Line Of Sight conditions but they cannot conclude on how the physicallayer behaves while moving under the satellite the coverage. The activity will provide a powerful system engineering design tool to satellite operators and industry planning the deployment ofhybrid satellite/terrestrial systems.This tool shall build up on existing tools and methodologies and fill the gap by including realistic and flexible models of the physical and link layers of a hybrid system comprising of aterrestrial and a satellite component. Moreover, the tool shall allow deriving system performances over the areas where both satellite and terrestrial signals are present. This implies analysingaspects such as hybrid combining in SFN and MFN configurations, exclusion zones and intra system interference. It shall also contain realistic satellite antenna models in order to assess theoverall coverage. The tool shall provide system performance information (percentage of coverage served with a target service quality, throughput, spectral efficiency, overall capacity) and itshall be able to convey this information both in a tabular and in a graphical way (displaying maps of the coverage).The tool shall be built with a modular approach and it shall be flexible enough to be able to model different hybrid systems scenarios in the short term using DVB-SH, which will be used as abaseline in this activity, and also in the long term including future evolutions of the air interface and satellite system architectures. The activity will also include a validation phase in whichthe tool results will be cross-checked against the experimental data extracted from different on going and planned campaigns such as Ortigia, J-Ortigia and any other additional data available(e.g. from the DVB-SH validation task force).The final goal of the activity is to build a Software simulation tool and a methodology allowing operators to plan their hybrid network efficiently and guarantee the best frequency utilizationand use of satellite and terrestrial component power resources.

Annex 2Page 7Ref. Activity Title Procurement Policy Budget(KEUR)Planned TenderIssueEstimated Duration(months)3A.036(09.153.24)Security of broadband satellite systems for commercial and institutional applications Open Competitive Tender Type: C 250 4Q 2009 12Objective:Description:To perform a security risk analysis on current and future broadband satellite systems used for commercial and institutional applications and derive system security requirements; to proposeand define appropriate network security measures; to validate new security protocols through simulations or emulations; to define a generic security architecture; to provide recommendationsfor standard evolutions.Interactive broadband satellite systems may encounter several types of threats e.g. data communication eavesdropping, satellite system signalling spoofing. The integration of securitycountermeasures is therefore seen as a major system requirement for institutional as well as commercial systems. Today some security solutions may be used, however they are not alwaysadapted to satellite networks (e.g. end-to-end IPSec is not compatible with PEP) and are far from addressing all the security requirements, which moreover may vary substantially per systemand business case. The activity will address fixed and mobile satellite systems, used for commercial or institutional applications, having a star or meshed topology (notably DVB-RCS/S2satellite systems). The activity shall:- define reference system architectures, perform a security risk analysis and derive system security requirements,- define appropriate security mechanisms (these mechanisms, located in data, control and management planes, shall satisfy the system security requirements for commercial and institutionalmarkets as well as take into account the current standardisation and requirements in terms of security certification),- analyse their implementation, system effectiveness and related operational aspects,- validate new security protocols through simulations or emulations,- define a generic security architecture with the appropriate method to accommodate it to actual systems,- provide recommendations for standard evolutions,- perform a proof-of-concept demonstration over simulator/emulator between end-systems.For control and management plane measures, the outcomes of the ARTES 1 study ‘Security for DVB-RCS at management and control planes’ will be used. For data plane, both satellite-linkonly and end-to-end security will be addressed as well as the different types of connectivity, e.g. unicast, multicast and broadcast.

Annex 2Page 8Ref. Activity Title Procurement Policy Budget Planned Tender Estimated(KEUR) IssueDuration (months)3A.037 Hardware Demonstrator of Fourth Generation Mobile Satellite Systems Open Competitive Tender Type: C 2000 Priority 2 18(09.153.01)Objective: To build a hardware demonstrator implementing the physical, link and MAC layer of the satellite component of 4th Generation Mobile Satellite systems. The demonstrator will also includesatellite channel and satellite system emulation functions.Description: The ARTES 1 “Study of the role of satellite in 4G networks” highlighted the role of the satellite to complement the terrestrial evolution of the 3rd Generation mobile systems either in areaswhere the terrestrial deployment cannot be guaranteed or with services more efficiently provided by the satellite wide coverage. Therefore, this demonstrator follows the ARTES 1 activitywhere the evolutions of two terrestrial air interfaces were identified as candidates for the satellite component of the 4G: WiMAX and 3GPP LTE.These air interfaces include mechanisms to increase throughput in the terrestrial wireless channel. However, most of the mechanisms are not applicable to or counterproductive in the satellitechannel characterised by slow flat fading, non-linear distortion and long round trip delays. On the other hand, the compatibility of the satellite access schemes with the terrestrial counterpartsis one of the most important criteria to keep the user terminal cost and form factor at an acceptable level and facilitate interoperability between terrestrial and satellite networks. Therefore,adaptations to these air interfaces are required to achieve good performance over satellite while reusing as much as possible the terrestrial technology. Furthermore, both the LTE and WiMAXfamily offer the possibility of different transmission bandwidths which will help to the scalability and flexibility of the overall system.The activity aims at providing a system solution for satellite operators and industry manufactures, who are already busy planning the next generation of Mobile Satellite Systems.The main challenges for this demonstrator reside in selection and optimisation of the physical layer and link layer parameters, the design of algorithms allowing synchronising the signal atvery low C/N values, the introduction of techniques to increase robustness against non-linear distortion and phase noise and the design and implementation of mechanisms allowing forefficient operation over the LMS channel. To do so, the demonstrator shall model in an accurate manner the satellite channel.In addition, the demonstrator shall implement MIMO techniques. To this purpose the channel emulator shall be capable of faithfully reproducing the key characteristics of the selected satellite(and terrestrial if applicable) system. Both spatial and polarization channel diversity shall be included together with a realistic satellite and user terminal antenna model which are the elementspermitting the exploitation of such diversity.This activity will be carried out in two phases: a first phase will analyse the relevant system scenarios and define the demonstrator requirements including the preliminary architectural designof the main HW demonstrator modules (terminal emulator, Hub emulator, channel simulators, traffic generators, etc); it will be followed by an implementation phase that will include thesystem and functional validation and the 4G MSS system performance tests covering different operational scenarios.The first goal of the activity is to prove the feasibility and performance of the satellite component in the 4G context. It is expected that these outcomes will be used in the relevantstandardisation bodies like ETSI MSS WG. The second objective of this activity is to provide a platform for trials and demonstrations for future projects constituting a key asset to satelliteoperators and industry for the development of the commercial MSS systems.NOTE: This activity has been designated as "Priority 2". Priority 2 activities will only be initiated on the explicit request of at least one delegation.

Annex 2Page 9Ref. Activity Title Procurement Policy Budget(KEUR)Planned TenderIssueEstimated Duration(months)3A.038 All-IP Broadcast Satellite Networks Technologies and Demonstration Open Competitive Tender Type: C 700 3Q 2009 18(09.153.02)Objective: To study the system and prototype and validate key technologies for IP-based broadcasting services over DVB-S2 adaptive Ka-band satellite systemsDescription:Ka-band satellites are finally emerging and changing the way satellite services are offered to the end users. Ka-band satellites will not only offer broadband interactive services, but alsoadvanced broadcasting services (e.g. IPTV at several hundreds of Mbps) directly to the end users. IPTV will allow a personalised and interactive environment, integration withcommunication services and integration of mobile & fixed TV. Two types of satellite terminals shall be present: the interactive and the receive-only terminals. The latter ones may becombined with a terrestrial network access at lower data rates providing the interactivity (e.g. ADSL). In this new context, it is pivotal that broadband satellite systems support the newservices effectively and seamlessly. The activity shall be divided in two phases:i) Study phase: This first phase will start with the definition of the advanced broadcasting multimedia services (e.g. HDTV, multimedia content delivery, content on demand) and study theirintegration over a DVB-S2 based satellite system in Ka-band and with the home networks. Among others the following issues will be addressed:a. Support of very high symbol rates (200 Msps) over DVB-S2 chipsets (using for example techniques like time-slicing)b. Efficient transport of the RTP packets over DVB-S2c. Integration of scalable video coding (e.g. supporting SD and HDTV) over DVB-S2 VCM waveforms for broadcast and over DVB-S2 ACM waveforms for unicastd. Integration of the satellite-link router configuration and received content (live feeds, cached) with the multimedia home networking standards (Open IPTV Forum, DVB IPTV Forum,DLNA, ITU IPTV, IPTV Interoperability Forum will be studied)This phase will be completed with the specification of an end-to-end demonstrator and the identification of the required technologies to be prototyped in the next phase. Among these, akey component is deemed to be the satellite-link IP-Based router.ii) Prototyping and demonstration phase: During the second phase, the prototypes of the required technologies including the satellite-link router shall be implemented (e.g. a Linux basedimplementation) including the necessary protocols and software to support the advanced broadcasting services. The demonstrator shall be able to validate the services and techniquesdefined in the study phase and shall realistically emulate a Ka-band satellite channel. The remaining of the demonstrator shall be also setup including:a. DVB-S2 modulator (with ACM, VCM, MPEG, GSE support)b. Ka channel emulatorc. Multimedia content encoders (with SVC support) and multiplexersd. Decoders on the end-user appliances and measurement equipmentA test/validation effort in a controlled laboratory environment shall then follow. Different services and combination of them will be demonstrated over different satellite channelconditions.

Annex 2Page 101.2 PropagationRef.alNumber3B.017(08.153.39)Objective:Description:Activity Title Procurement Policy Budget(KEUR)Propagation analysis tool for design of fixed and mobile multimedia systemsOpen Competitive Tender Type:C(2)Planned TenderIssue400 2Q 18Estimated Duration(months)To develop a WEB based propagation analysis tool to be used by industry designing multimedia satellite telecommunication systems for fixed, mobile or airborne user terminals using GEOand non GEO satellites. The frequency range is from L to V band.The use of propagation models and ITU-R recommendations can be quite difficult for industry and the non-propagation engineers due to the large number of interrelated issues and the regularrelease of new or updated ITU-R recommendations. This can result in duplicated implementations and validation procedures that increase industrial cost. In addition errors in dealing withcomplex propagation parameters and models can result in wrong design assumptions and lengthy review procedures.During the 1990’s ESA developed the RAPIDS tool, which is a WEB based system to produce the link budget propagation parameters for satellite telecommunications systems with fixedterminals. It is based on a core of ITU-R recommendations for the prediction of atmospheric attenuation statistic. Thanks to the encapsulation of the complexity of propagation models,meteorological data and system parameters the tool can be managed easily also by users without a deep background on propagation. Its configuration and reporting capabilities make RAPIDSapplicable to propagation experts for in-depth analyses. Over the years it has been proven that RAPIDS increased the efficiency of system analysis and trade-off activities for various projects(e.g. Galileo ground segment, Alphasat mission preliminary and phase A design, the telecommunication link of Science and Earth Observation new missions). However, a new version isrequired due to the continuous evolution of models and obsolescence of its platform with respect to new software standards.The area of application of propagation models and tools is also developing because the SatCom systems are evolving into integrated systems capable of providing global communicationservices to fixed, mobile and aeronautical terminals. The design of such systems shall address several propagation issues for frequencies ranging from L to V band and shall accommodate avariety of system configurations (e.g. GEO and non-GEO satellites, point-to-point or point to-multipoint communications). For most of these issues models have been developed recently, alsothrough ESA activities, and they did not exist when RAPIDS was developed.Therefore, a new tool is required to improve and expand the propagation software tools for the telecom engineer to address the requirements of new and upcoming satellite communicationssystem design. The new tool shall include:• Tropospheric, ionospheric and environmental effects for a wide range of frequency bands.• Channel models for dynamic properties (time series generator) and spatial correlation and spectral properties• Propagation aspects for interference assessment from both terrestrial and spatial systems.• Harmonisation of models from different application areas.• Common approach and User Interface based on system issues.• Analyses and comparison of models with real propagation measurements.The proposed activity can leverage on recent developments in ESA and European projects on radiowave propagation to produce a modernised WEB based computational server for Europeanindustry and organizations. The tool will be made available to industry and organizations involved in ESA and European satellite telecommunications system design activities.

Annex 2Page 11Ref. Activity Title Procurement Policy Budget(KEUR)3B.018(08.153.40)Objective:Description:Planned TenderIssueCharacterisation of the MIMO channel for mobile systems Open Competitive Tender Type: C 350 1Q 2009 15The activity is to develop a propagation model for mobile satellite systems at L and S bands including multiple simultaneous propagation paths.Estimated Duration(months)The Multiple-Input Multiple-Output (MIMO) concept is extensively used in wireless terrestrial communications providing ways to increase the efficient use of the spectrum and/or to improvethe availability of the system. The basic idea is to process simultaneously the signals transmitted via different propagation channels, for instance, using multiple antennas in transmitter andreceiver, or multiple polarisations. If the channels are uncorrelated, an efficient combination of the signals is possible resulting in either an increase of the capacity or a more resistantconnection to propagation impairments. For highly correlated channels, the advantages of MIMO techniques need to be investigated. The good characterization and modelling of the MIMOpropagation channels and the cross-correlation between them (represented in MIMO notation as a channel matrix) is a key element to evaluate the performance and the advantages of a MIMOmobile satellite communications system.For satellite communications, there are a number of possibilities to take advantage of MIMO techniques: polarisation diversity (one satellite and one receiver using two polarisations),multipath diversity (multiple antennas on the user terminal) and satellite diversity (more than one satellite and multiple antennas in the receiver side). All those possibilities have advantagesand drawbacks that are being analysed in an ongoing activity.For the activity proposed the results of the ongoing activity will be an input to the development of a propagation model including multiple simultaneous propagation paths. During the activitymeasurements shall be performed to derive the cross-correlation of dual-polarised and multiple-antenna channels in different environments. Satellite diversity characteristics shall be derivedfrom the results of the ARTES5 activity “Channel Modelling for multi-satellite systems with angle diversity”.

Annex 2Page 12Ref. Activity Title Procurement Policy Budget(KEUR)3B.021(09.153.25)Objective:Description:Planned TenderIssueDevelopment of miniaturized microwave ground radiometers for SatCom ground stations Open Competitive Tender Type: C1 400 Priority 2 12Estimated Duration(months)To design and build a prototype of a microwave ground radiometer operating at Ka and V band with a reduction in mass, volume, power consumption and costs with respect to current off-theshelfunits. The instrument is to be used by satellite ground terminals to perform the characterization of atmospheric propagation conditions in real time.The activity will allow the manufacturing of ground microwave radiometers for satellite communication systems with a substantial reduction of cost and complexity with respect to currentequipment technology. Currently COTS ground radiometer equipment, mainly targeting meteorology applications, can only be procured from two companies, one in USA and another inEurope. The activity aims at strengthening the capabilities of the European manufacturer or opening this market segment to other European suppliers. Areas of application are the in orbitvalidation and mission monitoring of the signal level or propagation campaigns like the Alphasat TDP5 experiment.Ground Based microwave radiometers are commonly used by ground stations to monitor various propagation parameters relevant for satellite systems, like the atmospheric attenuation and thesignal path delay. Actually current commercial units are designed to be used as an high accuracy atmospheric remote sensing instrument and the target customers are meteorologicalorganizations, whit different requirements in terms of accuracy and physical characteristics. For example radiometers for meteorology use several lines in Ka and V band to get the verticalprofile of meteorological parameters, and in order to improve accuracy they perform calibration by looking at an external reference rather than using a Dicke switch design. Therefore the offthe-shelfinstruments currently available are characterised by costs and operational requirements that make difficult their adoption and use by SatCom operators or propagation experimenters.As an example the purchase and operations of microwave radiometers in a network of ground stations, being hub stations or propagation terminals, can account for a significant overall cost.As a result the actual adoption of microwave radiometers in SatCom ground stations is very limited. Moreover current commercial microwave radiometers are based on discrete microwavecomponents (e.g. waveguides, connectors, etc.) making them larger, heavier and more demanding for thermal control systems.Actually the complexity of microwave radiometer for SatCom ground station can be reduced by:- Using a number of frequency lines lower than the ones used in meteorological instruments. Options are: to use frequency lines near the SatCom system frequency bands (mainly at Ku,Ka and Q/V bands) and/or to use few frequency lines selected according to the emission spectrum of the atmospheric components (gases, clouds and rain) and to perform frequencyscaling.- To design a radiometric unit as a subsystem of the receiver front-end, eliminating the need for an additional antenna and data acquisition system.- The adoption of monolithic microwave integrated circuits technology (MMIC) derived from mass production components characterised by reduced costs, dimensions and powerrequirements. This technology has been already used even for spaceborne instruments, e.g. the Jason−1 Microwave Radiometer and the ESA Planck radiometer at 30, 44 and 70 GHz.Considering all the above mentioned issues, and in particular the availability of MMIC components and the different (and in a sense simpler) satcom ground station requirements, it appears tobe possible to design an implement a miniaturized microwave ground radiometer for SatCom applications, characterised by a 50 % reduction in size, weight, power consumption and cost withrespect to current off the shelf units.The activity aims at designing and developing a prototype of a microwave radiometer to be used as a stand-alone or sub-system unit in satellite Radio communication systems characterised byreduced production and operational costs with respect to current commercial units. Testing and validation of MMIC components and advanced antenna technologies for ground basedradiometric receivers. Development and improvement of radiometric algorithms for the real-time assessment of channel conditions for Propagation Impairment Mitigation Techniques(PIMT).NOTE: This activity has been designated as "Priority 2". Priority 2 activities will only be initiated on the explicit request of at least one delegation.

Annex 2Page 13Ref. Activity Title Procurement Policy Budget(KEUR)3B.022(09.153.26)Objective:Description:Planned TenderIssuePhysical-statistical models for mobile satellite communication systems below 10 GHz Open Competitive Tender Type: C1 250 3Q 2009 15Estimated Duration(months)To develop a propagation modelling software tool and channel propagation models combining deterministic and statistical approaches. The models will combine physical principles(diffraction, reflection, transmission) at existing obstacles together with stochastic parameters in order to be able to reuse the model on different environments or locations. The models willcover land-mobile satellite, aeronautical and maritime environments.Typically for the description of channel characteristics two types of models are available: those based on physical principles (GO / PO / UTD/GTD / MoM) and the ones based on empiricalformulas or statistical fitting from measurements. Implementing the first type with high level of detail require an extreme degree of complexity and many times a number of assumptions areprovided which limit the validity of the models to coverage and average fading values but they are usually not accurate enough for fading time series generation. Furthermore, the requiredlevel of detail of the surrounding environment is very demanding.On the other hand empirical and in particular statistical models derived from measurements present a good trade-off between accuracy and simplicity; however their applicability is limited tothe scenario where the measurements were obtained (or those with similar characteristics). For instance, there are major differences between suburban scenarios in different Europeancountries.An intermediate step consists in the development of hybrid physical-statistical models, where a general baseline model is derived from general physical principles (reflection and diffractionfrom airplane structure, reflection from ground and sea, diffraction and transmission from trees, diffraction and reflection from buildings, and different combinations of the mechanisms...). Toadapt the baseline model to a particular environment of interest, the environment is characterised by stochastic parameters. The major advantage is that once the baseline model is developed,it is possible to extend its applicability to other environments or frequency bands with limited effort considering a general description of the environment (e.g. mean building height, meanwidth of the streets etc) and a reduced number of measurements performed on the new environment to fit the stochastical parameters..ESA has performed various measurement campaigns for the modelling of channel characteristics in Land Mobile Satellite environments useful for the design of Satellite MobileCommunication Systems and Satellite Broadcast to Mobile Systems. Also a number of campaigns have been performed in the framework of satellite navigation, which results can be adaptedto Satellite Mobile Telecommunications. ESA has also performed a small number of activities to build simulators of theoretical channel propagation models.The state-of-the-art of hybrid physical-statistical propagation models is limited to a few studies done by the research community. At this stage there are no models available for satellitecommunication systems. Only one hybrid model is available for land-mobile satellite navigation systems. This model is proposed to become an ITU recommendation. This model is notapplicable to satellite communication systems.In this activity a hybrid propagation model will be developed for satellite communication systems between 1 and 5 GHz. The model will consider the specific characteristics of the airinterface of satellite communication systems. The model will be based on existing literature and propagation datasets. It will aim for an implementation presenting a low complexity to theuser. It will cover a number of typical environments in Europe, and it will be used for system design, equipment design and development of propagation impairment mitigation techniques.The activity will include the following tasks:- Physical modelling of typical propagation obstacles: e.g. trees, sea, plane structure, buildings.- Characterisation of stochastic parameters of the model using data from previous ESA campaigns on environments of interest.- Implementation of operational software integrating both the physical and statistical models.- Adaptation to other environments and frequency bands.The final deliverables will include technical documentation, input to ITU-R for standardisation and the propagation modelling software tool able to produce both statistical parameters of thechannel and also channel simulation in time or frequency for a given configuration.

Annex 2Page 142. SPACE SEGMENT - GENERAL2.1 Platform – System and ArchitectureRef. Activity Title Procurement Policy Budget(KEUR)4A.021(08.153.41)Objective:Description:Planned TenderIssueESD/electrical transients monitor Open Competitive Tender Type: C2 400 2Q 2009 25Estimated Duration(months)To develop, manufacture and test an engineering model of an equipment to monitor the electrical transients and electro magnetic interferences induced onto the spacecraft power bus as aresult of electro static discharges (ESDs) on the spacecraft.Environment-induced electrostatic discharge (ESD) is a major cause of anomalies in telecommunications spacecraft. These are inferred to cause electrical transients in electronic systems,causing damage and upsets. However, they have not been directly monitored on European spacecraft. The detection and characterisation of electrical transients in cabling and electromagneticinterference resulting from ESDs will be beneficial in anomaly diagnosis, improvement of modelling and the development of more robust spacecraft.Various concepts exist for the detection of electro magnetic variations resulting from ESD on bus voltage. These concepts will be traded-off and the most promising will be implemented. Theengineering model will also include a standard interface to a GEO telecom satellite data handling bus to enable transmission of the data to the satellite control centre.Ref. Activity Title Procurement Policy Budget(KEUR)4A.024(08.153.15)Objective:Description:Planned TenderIssueImproved level of information provided in TM Open Competitive Tender Type: C 500 2Q 2009 12Estimated Duration(months)The objective is to design, manufacture and test an EM model of a TM interface unit implementing new techniques in measurement and multiplexing of satellite TM improving the access tocritical information during nominal and emergency operations.This proposed work will take a fresh look at the needs of the operators and prime contractors as regards the TM/TC capability of GEO telecom spacecraft. The outcome will be a list of TM, anew method of accessing TM during spacecraft emergencies, a fresh set of requirements for dwell and accuracy on specific TM, and the incorporation of lessons learned from AnomalyReview Boards concerning spacecraft failures. With the growing sophistication of GEO spacecraft has come an enormous increase in the amount of TM on-board. At the same time,improvements in A/D conversion plus the digitalisation of the TM has lead to a potentially huge increase in the TM accuracy, with TM sometimes being quoted to 6 figures after the decimalpoint. At the same time, pressure on integration has lead to the widespread use of multiplexing techniques at high sampling frequencies, and this together with increased bus noise due to highpower has lead to an effective decrease in the quality of TM available to the satellite operators. The overall result, as highlighted by dialogue with operators and primes is threefold as follows:1. A large part of the TM is wasted since inaccuracies far exceed precision of measurement (sometimes by a factor of 1000 or more)2. Some specific TM, such as solar array section current and bus current, is extremely useful for anomaly detection and yet still not available with sufficient precision to allow it to be usedmeaningfully. One example is the need for traceability of bus current consumption before and after an equipment turns on as used during in orbit testing or anomaly investigations.3. During spacecraft emergencies, operators have little flexibility on TM dwelling and have difficulty in operating the spacecraft due to the impractical amount of TM and information onTM, which they have to treat. A further impact is that on the mass of the system due to the hardware required to handle the TM available on-board.The requirements for TM will be defined in a document and an Engineering Model will be designed, manufactured and tested of a TM interface unit implementing the requirements.

Annex 2Page 15Ref. Activity Title Procurement Policy Budget(KEUR)4A.028(09.153.27)Objective:Description:Planned TenderIssueStandard Satcom Provisions for Life-extension Open Competitive Tender Type: C1 400 Priority 2 18Estimated Duration(months)The objective of this activity is to study satcom life-extension systems, to identify the most promising concept for telecom geostationary satellites and to define standard interface requirementsfor a satcom life-extension system.The characteristics of the existing European telecommunication satellites shall be considered for establishing a standardized approach for the Life-extension System Concept. The majorsystem impacts on the geostationary satellite being life-extended shall also be identified and a solution shall be proposed for standardisation.The subject of orbital life extension has recently been addressed by ESA activities Orbital life extension has two pre-eminent ways to be realised:- Captive carrying: a servicer spacecraft attaches permanently to an end-of-life satcom client and implements station keeping orbital control.- Refuelling: a servicer spacecraft (a tanker) attaches to different end-of-life satcoms to refill their tanks.The Captive-carrying option was explored by ESA in the course of the ConeXpress OLEV project. The project focussed on satcom targets that were uncooperative to the servicer (i.e. had noprovision to make RVD easy). The refuelling option was briefly studied in the TRP activity Satellite Servicing Building Blocks (SSBB) being completed in Q4/2008. The study has identifiedthat some satellite servicing operation can be economically advantageous and technically feasible. Operators interviewed during the study showed interest in the refuelling solutions. Inparticular, operators were puzzled by the fact that the technology is being readied in the military space sector.Considering European and international developments, there is definitely the prospect that satcom satellite servicing, particularly Life-extension, may become reality within a decade. In theprocess of acquiring new spacecraft, which when commissioned will last over 15 years, Operators may ask satcom manufacturers on the possibility to introduce servicing provisions whichthey see as an opportunity to future-proof their new assets. To have any chance to be used in a future, these servicing provisions need to be standardised across the industry. With the activityin subject, ESA intends, together with the European satellite manufacturers to conceive and promote standard servicing provisions that can be installed in present European satcom platforms.ESA intends to involve all the European telecommunication satellite primes in order to ensure that the proposed solution will be standardised.This study shall first review the possible solutions to perform geostationary satcom life extension function and identify the most promising solution in term of economic and technicalfeasibility. The study shall than design the architecture of the chosen solution in all its elements (e.g. servicer, other orbital elements) and their interfaces. Finally the study shall define theprovisions that will be needed to be implemented on the geostationary satellite. (e.g. docking and refuelling interfaces). The activity shall finally compile the result of the above work into adocument to be proposed to the ECSS standardisation body to achieve the status of recognised standard.NOTE: This activity has been designated as "Priority 2". Priority 2 activities will only be initiated on the explicit request of at least one delegation.

Annex 2Page 162.2 Propulsion SystemRef. Activity Title Procurement Policy Budget(KEUR)4B.029(07.153.50)Objective:Description:Planned TenderIssuePlastic liners for pressure tanks Open Competitive Tender Type: C1 400 2Q 2009 18The objective of the activity is to design, manufacture and test and engineering model of a High Pressure gas tank using a plastic liner.Estimated Duration(months)Current generation High Pressure gas tanks used on telecommunication satellites are manufactured by machining or spin forming a metallic shell (usually a titanium alloy, or possibly astainless steel), welding the parts together, and then over-wrapping the tank with a composite material. A plastic liner could be moulded or injected into a preformed carbon composite shell toprovide extremely lightweight liner, directly replacing the current metallic liners. The use of a moulding or injection technique would eliminate for expensive metal processing (machining,welding, inspection), eliminate supply problems such as titanium shortages at forge house, and reduce the lead time for tanks by many months.It is expected that as a minimum the following phases will be undertaken:1. Demonstration of proof-of-concept2. Development model manufacture and testing3. Design/test review (BDR / PDR level).As well as investigating the design, develop and manufacture of such liners, other issues that must be addressed is the moulding/joining techniques of the liner and Non-destructiveInvestigation methods once the final tank plus liner has been manufacturedRef. Activity Title Procurement Policy Budget(KEUR)Planned TenderIssueEstimated Duration(months)4B.034 Low Cost Fabrication Techniques for Titanium Propellant Tanks Open Competitive Tender Type: C 500 Priority 2 21(09.153.03)Objective: To research, develop and prepare for later qualification innovative techniques for the manufacture of titanium propellant tanks that is significantly cheaper than the existing billet / forging /machining / welding techniques employed. Ideally these techniques will also be quicker, more flexible to enable production of more than one tank size per set of tooling, and compatible withthe current state of the art NDI techniques and fracture control and safety requirements.Description: As detailed in the 2005 harmonisation activity and reinforced during the 2008 harmonisation re-visit for Propellant Tanks and High Pressure vessels, there is a need to increase thecompetitiveness of European tanks, and provide products that maximise the propellant capacity whilst minimising the mass and recurring cost. Current techniques of forging (thick) shells andmachining require extensive tooling, only suited to one size of component, and incur high quantities of expensive wasted material, and are very long lead time items, so need to be orderedvery early in the spacecraft manufacturing process. If new manufacturing techniques are developed that are more flexible, and do away with the need for specific and several sets of tooling foreach shell component, the cost and potentially lead time can be reduced. This could then allow a later decision on the tank size to be selected, allowing more flexibility for the spacecraftmanufacturer, and thus market a more competitive tailor made product. There is some knowledge of spin forming certain titanium products (used largely in the launch vehicle segment),,explosive forming, hydro forming and plastic forming of a cylindrical piece. However further development is required of these techniques to ensure chemical compatibility with the currentgeneration of hypergolic propellants.The activity will include manufacturing of samples using the new techniques.NOTE: This activity has been designated as "Priority 2". Priority 2 activities will only be initiated on the explicit request of at least one delegation.

Annex 2Page 17Ref. Activity Title Procurement Policy Budget(KEUR)4B.035(09.153.04)Objective:Description:Planned TenderIssueAlternative Bi-Prop Regulator Open Competitive Tender Type: C1 500 2Q 2009 24To design, manufacture and test a breadboard of a new electronic helium pressure regulator for bi-propellant propulsion systems.Estimated Duration(months)The current state of the art in helium regulation for commercial satellites remains mechanical regulators. There is also only one indigenous European supplier at present. There are limitationswith these regulators: They have single fixed set points so they cannot vary the gas pressure delivered to the propellant tanks. This limits the mission flexibility. They also have comparativelyhigh leak rates. Over time the pressure will equalise across the low and high pressure sections of the propulsion system. Normally this pressure exceeds the operating capability of thepropellant tank. Therefore the regulator has to be isolated early in the mission using pyro valves and the propulsion system is consequently operated in a blow down mode. This mode preventsthe CPS from operating at its most optimum. It also prevents the high performance main engine from being used again for any orbit changes that may be desired late in the space craft life. Allthese issues translate into higher propellant budgets for a given mission. An electronic regulator built to meet commercial satellite requirements would represent a significant technologicalimprovement. The electronic regulator would be more flexible than current mechanical designs. It would present a second source for a vital European component and an internationallycompetitive product. An electronic regulator would be free of the mechanical design constraints that limit the current units. This would present many more opportunities to solve the leakissue. In turn these features would translate into an increase in satellite capabilities.Ref. Activity Title Procurement Policy Budget(KEUR)4B.036(09.153.28)Objective:Planned TenderIssueDevelopment of a Cost-Effective Hall-effect Propulsion Subsystem Open Competitive Tender Type: C 300 Priority 2 24Estimated Duration(months)To redesign the PPS-1350-G propulsion subsystem in order to obtain an important reduction of the overall recurring cost. To manufacture critical items to verify by test the feasibility of there-design to meet the PPS subsystem specifications.Description:The currently qualified Hall-effect thruster PPS-1350-G is a successful SNECMA delta-development of the Russian counterpart from Fakel, the SPT-100 also commercialised by SNECMAthrough an ISTI agreement. Even though the PPS-1350-G has a better performance and total impulse than the SPT-100, European Primes are still flying the SPT-100 (except Alphabus)because of the large difference in price. Other applications are attracted by the PPS-1350-G subsystem performance but deterred by the overall recurring cost judged excessive to remaincompetitive at platform level. There is therefore a strong interest to render the PPS-1350-G at least as attractive as the SPT-100 in terms of price and hopefully further decrease by at least 20-30% the recurring price. In this activity, the Contractor shall functionally optimise the subsystem-level configuration and define cost-saving unit-level specifications for the power supply, theflow controller, the electrical filter unit, and the thruster. The Contractor shall identify the most critical cost-sensitive functions, technologies, and processes for each of the units. TheContractor shall perform a cost-effective redesign of the above mentioned units to be compliant with the newly defined specifications. The Contractor shall manufacture and test critical itemswithin the units to demonstrate feasibility of re-designed units.NOTE: This activity has been designated as "Priority 2". Priority 2 activities will only be initiated on the explicit request of at least one delegation.

Annex 2Page 18Ref. Activity Title Procurement Policy Budget(KEUR)4B.037(09.153.29)Objective:Description:Planned TenderIssuePropellant Simulant Assessment and Propellant Tank Offload Open Competitive Tender Type: C 250 2Q 2009 6Estimated Duration(months)Produce a study report identifying suitable simulants for use in classical spacecraft propulsion systems to simulate Mixed Oxides of Nitrogen (MON) oxidiser and identifying the currentcapabilities of spacecraft propellant tanks to be offloaded of liquid propellants and to be re-used for flight.The study shall propose suitable simulant materials and shall assess each of the proposed simulants against all of the applicable criteria for selection including:- Representativeness as a simulant for MON in terms of density, viscosity etc.- Compatibility with common materials used in the manufacture of propulsion systems e.g. Ti alloy, Stainless Steels, Fluorocarbon polymers, elastomers- Stress corrosion cracking considerations- Environmental hazards and personnel safety- Operational issues for filling, draining and drying of propulsion systems- Costs- Any additional testing which would be required to qualify suitable simulants for use with flight hardware- Compliance with all applicable specifications including:- ECSS-E-30 Part 5.1A- ECSS-E-10-03- ECSS-E-30 part 8- ECSS-Q-70-36- ECSS-Q-70-01A- MIL-STD-1522APreviously simulants such as Freon-114 have been used to represent oxidiser in the environmental testing of spacecraft propellant tanks at equipment and subsystem level. The simulantprovides both a representative mass load on the tank and spacecraft structurally and replicates the sloshing of propellants during vibration testing producing dynamic loads. In the late 1990sFreon-114 was prohibited for use in this way for environmental reasons and from this point on other more or less representative simulants have been used in the place of Freon. Theimplementation of other simulants has occurred in an inconsistent way between equipment and subsystem suppliers with no clear qualification for spacecraft propulsion applications. The aimof this study is to identify the most suitable simulants which are currently available, identify any additional qualification effort which may be required and to provide input towards aharmonised verification with simulant for future European propulsion equipments and subsystems.Current design requirements for liquid propellant tanks include a requirement that they can be offloaded at the launch site. This very general statement does not go into detail on the level ofdraining that should be achievable (e.g. to tank expulsion efficiency levels, to tank dryness levels, to propellant threshold limit values), does not require the tank design authority to provideprocesses for the draining and does not include a requirement that the tank must be reusable after draining. The storable liquid propellants (Anhydrous Hydrazine, Monomethyl Hydrazine andMixed Oxides of Nitrogen (MON)) are normally maintained under closely controlled nominal storage conditions however during tank offloads these nominal conditions are no longermaintained creating conditions which can lead to a reduction in the capability of the propellant tank in terms of the propellant delivery capability or the safe design life of the tank. Whilstpropellant tank offloads are rare they have occurred in the past due to launcher delays or technical problems on the spacecraft requiring a rework which is not considered safe in a fuelled forflight configuration. The study shall identify and assess the issues which effect the tanks e.g. depressurisation from flight pressure and possible pressurant gas entrapment in tank PMDs duringdraining, propellant degradation, tank material degradation, residual propellants and processes to remove the residual propellant efficiently and without detrimental effect to the integrity of thepropellant tanks for future use e.g. by the formation of Nitric Acid. The current requirements for offloading shall be reviewed aiming at identifying less stringent requirements which meets theapplicable safety and technical requirements without risking the propellant tank integrity. Any future developments in tank design and/or additional requirements on the tanks shall beidentified to allow a realistic offload and re-use policy to be followed. The possibility for propellant manufacture and storage in-situ should also be considered.

Annex 2Page 19Ref. Activity Title Procurement Policy Budget(KEUR)4B.038(09.153.05)Objective:Description:Planned TenderIssueMEMS-based Satellite Propellant Gauging System Open Competitive Tender Type: C1 1200 2Q 2009 36To develop and test a MEMS-based (Micro Electro Mechanical Systems) Engineering Model of a Satellite Propellant Gauging SystemEstimated Duration(months)The market need for a small and accurate satellite propellant gauging system has previously been identified, e.g. in the work under ESTEC Contracts No. 21148/07/NL/CP and 9454/92. As anexample, there is a market demand for a gauging system that can reduce the operational uncertainty at telecommunication satellites end-of-life from typically six months down to a few weeks.If this can be achieved, the added value of the system is several months prolonged operational time in space for the satellite, which in turn translates into large revenues for the satellite ownerand its customers. A MEMS-based (Micro Electro Mechanical System) design results in miniaturization, higher accuracy and increased redundancy compared to existing designs. In acurrently running GSTP activity a breadboard is being developed of a MEMS based satellite propellant gauging system. This breadboard includes a reduced size non-flight representative tank,non-flight representative fuel lines, MEMS valves and MEMS pressure transducer. In the frame of the proposed activity an Engineering Model (EM) of a precision propellant gauging systemwill de designed, manufactured and tested. This system will be fully representative of the flight hardware and will make use of flight propellant.

Annex 2Page 202.3 AOCSRef. Activity Title Procurement Policy Budget(KEUR)4C.015(09.153.06)Objective:Description:Autonomous Orbit Determination and Station Keeping Control for Competitive TelecomMissionsPlanned TenderIssueOpen Competitive Tender Type: C 600 2Q 2009 18Estimated Duration(months)The objective of the activity is to define an overall autonomous orbit determination and control (AOCS) system onboard of telecom satellites including manoeuvre planning and executing,with orbit determination using optical navigation or GNSS.As far as the autonomous orbit determination is concerned it shall be based either on an optical navigation sensor or a GNSS sensor. These two sensors shall be traded for best performance,cost and availability, and the activity shall in particular consider the current ARTES-5 contract "GEO Orbit Determination Using an APS-based Navigation Sensor" and the current TRPcontract "Feasibility of GNSS sensors for AOCS applications in GEO and higher altitudes". The activity shall define a suitable orbit determination and propagation scheme, selecting asuitable computation method and defining a solver/estimator that can be easily implemented on-board and meeting the performance needed. A worst-case data outage has to be considered forthe different sensor technologies, including the effect on the overall performance. For the autonomous station keeping control scheme, the activity shall also develop and justify the necessaryalgorithms allowing for a complete on-board manoeuvre planning and execution. The design should be fully fault tolerant and safe and provide full visibility and configurability from anoperational point of view. The strategies shall be verified in a closed loop simulation environment. The activity shall define and demonstrate an overall AOCS architecture, resulting in anautomated and robust platform design, with reduced operational costs and increased availability. The study should focus on an electric propulsion based platform, allowing for more efficientautonomous manoeuvre planning. The output of the activity shall include algorithmic description of orbit determination and station keeping strategies, prototype SW, benchmarking testbed,and simulation tools.Ref. Activity Title Procurement Policy Budget(KEUR)4C.016(09.153.30)Objective:Description:Robust Control Techniques for Large Telecom Satellites with Demanding PointingPerformancePlanned TenderIssueOpen Competitive Tender Type: C 400 2Q 2009 18Estimated Duration(months)The objective of the activity is to improve the overall pointing performance and robustness of large telecom platforms with highly flexible appendages and demanding payload pointing.The activity shall investigate novel control techniques (overall system solutions) for improved pointing and robustness of large telecom platforms. Many larger platforms are suffering inperformance and robustness due to a combination of demanding flex modes from large appendages (solar arrays and antenna structures), together with very tight payload pointingrequirements, and coarse control means due to actuator selection. This is in particular important for more performing missions such as Ka-band and GEO-mobile missions. Several factors arecausing problems in current design solutions (e.g. too large minimum impulse bit, thermal snap of arrays, reflectors during entry/exit of eclipse, low resonance frequencies, etc) and need to beanalysed in more detail. The activity shall analyse the whole system for an optimal solution at system level, considering:1) advanced control techniques (addressing also the modulation/phasing of the control demand);2) dedicated sensors to measure bending and deflection of the appendages in order to allow for an active damping;3) the structural design of appendages (e.g. mechanical design &material selection for reduced elasticity and improved damping);4) active control of the appendage considering embedded dedicated actuators for control of the appendage itself; and5) the typical platform actuators (wheels and thrusters and their sizing, accommodation and interfaces).These options should be considered individually and together. The activity shall revisit current design solutions and identify the limitations faced today. Alternative design solutions shall beinvestigated and provided in the respective areas for an improved overall system performance and robustness, respecting also the unique telecom needs in terms of cost and recurrence. Thesuggested design solutions shall be traded and fully justified through analyses or test as deemed necessary and feasible. The output of the activity shall include design and justificationdocumentation files, software modelling/tools, and test samples (where needed).

Annex 2Page 21Ref. Activity Title Procurement Policy Budget(KEUR)4C.017(09.153.31)Objective:Description:Planned TenderIssueGraveyard and passivation strategies for GEO satellites Open Competitive Tender Type: C 200 Priority 2 12The purpose of this study is to define, develop and implement novel concepts and strategies for both chemically and electrically propelled satellites on GEO boxes.Estimated Duration(months)This study will focus on novel concepts to perform a graveyard manoeuvre in the presence or not of other spacecraft in the same GEO box. Special attention to fleets in the same GEO box orcontiguous box shall be placed. This means that the activity shall include collision probability sensitivity analysis. Propellant management and manoeuvre strategies shall be carefullyanalyzed. The study shall also include techniques for satellite passivation after de-orbiting. The study shall consider the worst case of attitude loss due to the emptying of the tanks, it shalldetermine an altitude threshold to respect and determine the passivation duration when knowing the achieved altitude at the end of the re-orbiting phase. The strategies shall focus onminimising the quantity of used propellant, using the thrusters’ configuration allowing the best efficiency. The activity shall also consider long-term behaviour in graveyard orbit.Graveyard manoeuvres at the end of phase E of a GEO satellite are now standard and mandatory for all satellites in the GEO ring. A graveyard orbit, also called a super -synchronous orbit, isan orbit significantly above synchronous orbit where spacecraft are intentionally placed at the end of their operational life. It is a measure performed in order to lower the probability ofcollisions with operational spacecraft and of the generation of additional space debris. Several kilograms of propellant is the estimation that operations are reserving to make the graveyardorbit for each tone of mass of spacecraft. This amounts to a big total that could consume months or even a full year of operations. This propellant consumption shortens the operational file ofa spacecraft and hence reduces revenues for the telecom operator. Moreover, a good propellant budget must be made available to avoid collisions with other spacecraft either in the same GEObox or the contiguous ones. The disposal phase at the end of operational mission of a telecommunication satellite recommends a safe disposal of space system (re-orbit the space system into adisposal orbit with a minimum perigee altitude (around 300km) above the geostationary altitude) and passivation (depletion of all on-board sources of stored energy). Disposal is a commontask that operators perform regularly. However, the recommendation of passivating the on board sources of energy is relatively new, and operators are beginning to include it into thespacecraft specifications. In future, both disposal and passivation will become not only regular practice but also mandatory activities. The challenge of tank passivation is to be able to depletethe tanks form residuals propellant and gas and to guaranty the spacecraft altitude of perigee. Thruster performances are very different in the different phases. Transitions between the differentphases are not simultaneous in all the thrusters. The control of spacecraft Earth pointed attitude with thrusters during these phases is not guarantied. If thrusters are commanded in a noncontrolled attitude, there is a risk to decrease the spacecraft minimum altitude down to geosynchronous protected region.This study will be divided in 2 phases:- Phase 1: feasibility part: solutions design, overall system strategies definition for several types of spacecraft, flight dynamics analyses, power, and communication analyses, AOCSanalyses and simulation, propulsion and thermal analyses, operational aspects, trade off and choice of the most appropriate strategies.- Phase 2: development, development of software simulation facility, validation of simulator and verification of the compatibility with flight software, development of flight operationalprocedures.NOTE: This activity has been designated as "Priority 2". Priority 2 activities will only be initiated on the explicit request of at least one delegation.

Annex 2Page 222.4 Thermal SystemRef. Activity Title Procurement Policy Budget(KEUR)4D.008(06.153.49)Objective:Description:Planned TenderIssueLoop Heat Pipe with Integrated Peltier Element Open Competitive Tender Type: C4 400 1Q 2009 24Estimated Duration(months)This activity is to design, manufacture and test a breadboard of a loop heat pipe with integrated Peltier elements to identify the advantages at product, thermal subsystem and at system leveloffered by the integration of Peltier elements into current Loop Heat Pipe (LHP) designs.In current applications of loop heat pipes on S/C level quite some efforts are spent to reduce/control parasitic heat leaks into the liquid lines and/or the reservoir, however such parasitic heatleaks can never be fully removed. Therefore there is always the need to use part of the radiator area to compensate for all these unavoidable parasitic heat leaks and to provide the necessarysub cooling at the inlet of the evaporator. However, this sub cooling requirement reduces the overall heat rejection efficiency of the system. The implementation of a Peltier element betweenthe reservoir and the evaporator could produce the necessary local sub cooling, thus resulting in a more efficient spacecraft radiator. It could also simplify the integration of the loop heat pipeat S/C level (e.g. no need for specific insulation). At system level, the benefit could be either smaller overall mass or higher payload dissipation level in exchange for some electrical powerand electronic commands. Moreover, Peltier elements could enhance the loop start-up process and provide a better control of the payload temperature. The study will consider several aspects.First perform a complete review/assessment of Peltier elements for space applications and assess their compatibility with respect to telecommunication satellite environment (compatibilitywith the bus avionics, Peltier element size, mounting and layout aspects between the reservoir and evaporator (power re-injection to the evaporator), lifetime requirement). Then a breadboardof a loop heat pipe with integrated Peltier will be designed and manufactured and tested. The test results will be compared with the ones of loop heat pipes without Peltier elements tohighlight the advantages at loop heat pipe product level.

Annex 2Page 232.5 Mechanical SystemRef. Activity Title Procurement Policy Budget(KEUR)4E.029(07.153.21)Objective:Description:Planned TenderIssueDevelopment of a Versatile European Eddy Current Damper Open Competitive Tender Type: C 600 Priority 2 18Estimated Duration(months)The objective is to develop, manufacture and test an Engineering Model of a European Eddy Current Damper suitable for the control and regulation of the deployment of medium sizedappendages on board small telecom platforms. The activity shall fully demonstrate the performances of the developed model in representative environment.The intended activity covers recommendations and conclusions of the harmonisation meeting on Space Mechanisms Hold Down/Separation Systems/Deployment Components held during thefirst semester 2004. The deployment of appendages like reflector antennas, radiators and solar arrays, requires regulation in order to control the dynamic of the deployment and to avoid thebuilding up of important kinetic energy. Too high kinetic energy would generate large latching shocks at the end of the deployment which would be critical for the integrity of the appendage,the platform and the AOCS. Regulation is most of the time achieved using passive damping systems which provide a constant deployment velocity. This is currently deemed as one of themost optimised/cost efficient deployment strategy. Only one space qualified damper is currently available in Europe and it is limited in performances. Most of the eddy current dampers usedon European spacecraft are from the US.The proposed activity is to develop a European Rotary Eddy Current Damper. Eddy Current Dampers are based on static magnets providing a constant and uniform magnetic field. Rotation ofa disk in the field produces a generated voltage in the disk. This voltage develops circulating currents (Eddy Currents) within the disk, which results in a restraining torque proportional tovelocity. The drag torque created is a linear function of the rotational speed of the disk. The main advantages of this reliable technology is unlimited rotation range, high temperatureoperational range, no degradation of performances versus temperature, no issues of contamination, high configurability with respect to deployment torque and velocity, and very highupgrading capabilities to achieve active damping when deemed necessary. The targeted application is the Small GEO spacecraft for which cost and mass efficiency are mandatory and ITARregulation is an issue.NOTE: This activity has been designated as "Priority 2". Priority 2 activities will only be initiated on the explicit request of at least one delegation.Ref. Activity Title Procurement Policy Budget(KEUR)4E.031(08.153.44)Objective:Description:Planned TenderIssueFriction Less lateral deployment hinge Open Competitive Tender Type: C 330 Priority 2 18Estimated Duration(months)To develop, manufacture and test an Engineering Model of Friction Less Deployment Hinge following promising work performed during an ESA ITI Contract. The demonstration ofperformance will be achieved through representative testing of an Engineering Model.Lateral deployment of Telecom spacecraft solar array panels is presently achieved by making use of standard in-line hinges or very low friction torque hinges that are rather complex andheavy.The innovative proposed concept, which feasibility was demonstrated in the frame of an ITI contract, will be fully demonstrated through a complete design documentation as well as the builtand test of an Engineering Model. By concept, this new generation of hinge is not prone to any wear or ageing and will then by concept simplify the solar array verification sequence as theground testing of lateral deployment will be required.NOTE: This activity has been designated as "Priority 2". Priority 2 activities will only be initiated on the explicit request of at least one delegation.

Annex 2Page 25Ref. Activity Title Procurement Policy Budget(KEUR)4E.037(09.153.32)Objective:Description:Planned TenderIssueUltra Light Compact Shock Damping Device Open Competitive Tender Type: C1 400 Priority 2 15Estimated Duration(months)This activity is to design, manufacture and characterise (test) a breadboard of an Ultra Light Compact Shock Damping Device intended to be used in combination with inertial deploymentsystems (e.g. ULMAAS). The proposed Ultra Light Compact Shock Damping Device is intended for implementation at the deployment hinge between antenna and spacecraft. It should betuneable to meet the needs of the new generation of telecom antennae and match with the interfaces to the antenna or its trim mechanism.A new generation of compact telecom S/C with light weight antennas is being developed for the GEO commercial market. New inertial deployment systems, e.g. ULMAAS, and compacttrimming mechanism are being developed to meet the demands of this sector. One of the toughest challenge of inertial deployment is meeting the high torque requirements and the highstiffness in deployed configuration while minimising the shock levels at the end of the deployment. This activity centres on the development of a compact damping system which can beintegrated to the antenna or trimming mechanism I/F and dampens the shock to minimal levels. In a first step a review of state-of-the-art damping devices and a trade-off of shock controlsystems for space applications will be performed. In parallel, the requirements of new telecom antenna assemblies will be reviewed. This part will conclude with a consolidated set ofrequirements including expected shock damping characteristics, stiffness, envelopes, mass and all other performance criteria for the device. The damping system will be developed to meet theconstraints of the specification, performance being verified by analysis and built breadboard. Its shock damping efficiency will be measured both at beginning of life and after acceleratedageing. The ability of the system to comply with the typical environmental, lifetime and positioning requirements of a selected target application will be assessed and, where applicable, tested.The versatility of the system for larger payloads and alternative deployment kinematics will be tested and correlated to previous analysis.NOTE: This activity has been designated as "Priority 2". Priority 2 activities will only be initiated on the explicit request of at least one delegation.

Annex 2Page 262.6 Power SystemRef. Activity Title Procurement Policy Budget(KEUR)4F.020(06.153.72)Objective:Description:Planned TenderIssueQuenching Circuit for Solar Array Power Arcing Events Open Competitive Tender Type: C 200 3Q 2009 12The objective of this activity is to design, manufacture and test a breadboard of a Quenching Circuit for Solar Array Arcing Events.Estimated Duration(months)Geosynchronous telecommunication satellites having system power levels in the tens of kilowatt range, now have typically power bus voltages of 100 volts or greater. If under sun illuminatedconditions of the solar array, any conductive particles bridge across opposite polarity electrical conductors that are carrying electrical power (i.e. adjacent solar cells, bus bars, or slip rings),any initial current flow will very likely rapidly evaporate such particles. What happens next however is very unpredictable. Either following the fusing of the particle, any residual arc maysimply extinguish, or alternatively if sufficient plasma, heat and material damage has already occurred, a sustained arcing event can be initiated. If this latter situation proves to be the case, theextreme localised heat generated by the arcing event can rapidly degrade any local insulating barrier and quickly result in a permanent short circuit condition, resulting in a dramatic powerloss for the satellite.A possible solution for the suppression of arcing is one, which will detect the initial short-circuit/arc and then allow a short delay time, so as to give a chance for any short-circuiting materialto evaporate. If the phenomenon persists beyond this short delay, any maintained arcing will then be quenched by removing the applied voltage for a much longer period by driving on theappropriate array section dump of the power system shunt regulator. Of key importance in this activity will be the ability to configure this circuit feature as simply as possible within existingpower dump stages of the shunt regulator. Within this proposed activity the contractor will be asked to design, manufacture and test a breadboard concept of a reliable arc quenching circuitconcept to be integrated within individual power dump stages of a Sequential Switching Shunt Regulator (S3R).Ref. Activity Title Procurement Policy Budget(KEUR)4F.039(09.153.33)Objective:Planned TenderIssueSolar Array Charging Voltage Limited by Neutralizer Open Competitive Tender Type: C 200 3Q 2009 12Estimated Duration(months)The objective is to study the feasibility of using a charge neutralizer mounted on the S/C body to reduce the overall solar array charging voltage to minimize the risk of damaging ESD onsolar arrays (primary and secondary arcs). The potential impact of such a neutralizer on the lifetime, performance of the solar array (such as contamination or sputtering effects on solar cellinterconnections) and the spacecraft attitude control management shall be assessed.Description:Solar arrays operating in GEO are typically charged to very high potentials resulting in ESD. Under various conditions primary arcs trigger damaging secondary arcs. Several in-flight solararray anomalies/failures were attributed to this phenomenon. It is known that the operation of ion engines on GEO S/C is changing the S/C floating potential. Having this in mind they mightalso be used to limit the max solar array charging potential.The main task of this activity is to find out if it is possible to use ion engines/neutralizers, to limit the maximum charging potential of a solar array. It shall be investigated if AOCS engines(modified either in performance and/or orientation) can be used or if dedicated units (identical to an AOCS engine or with equivalent performance) are required. Please note, that thisparticular phenomena and resulting potential solution of the problem is exclusively applicable for solar arrays in GEO.

Annex 2Page 27Ref. Activity Title Procurement Policy Budget(KEUR)4F.041(09.153.08)Objective:Description:Planned TenderIssueFlash-over evaluation on large solar panels Open Competitive Tender Type: C 900 4Q 2009 18Estimated Duration(months)The objective is to perform ESD tests in vacuum chamber on a large solar panel (8m 2 ), to derive the flash-over current characteristic over the panel and to manufacture and validate a flashover simulator for coupon testing.A better understanding of the characteristics and effects of electrostatic discharge (ESD) events have to be established. Some in-orbit failures on telecom satellites in GEO environments havebeen assigned to ESD events. The new generation of solar cells based on GaAs is more vulnerable to ESD than Silicon. Therefore, an ISO standard is planned to be issued describing test andqualification methods to simulate ESD effects on solar array panels in GEO environment. However, certain points still need to be clarified to avoid unnecessary over-design of the solargenerator as this could result in extra costs. Most important is to determine the maximum surface area that can be neutralized by the flash-over occurring during an ESD event, since thisresults in the maximum energy available to harm the solar panel and helps to define realistic test conditions.Today there is no model allowing to reliably extrapolate ESD laboratory test on small samples to large area solar arrays. It will be the objective of this activity to define extrapolation modelsthat will allow to use coupon testing. A flight-representative panel (8m2) shall be tested in a large vacuum chamber. Once, the correct shape of the flash-over current has been derived a flashoversimulator will be developed and validated that allows for representative tests on small coupons.This particular ESD phenomena and resulting potential solar array performance degradation is exclusively applicable for solar arrays in GEO.Qualification of solar arrays requires a set-up representative to in-flight configuration. It is known that the flash-over current involved in the electrostatic discharge is related to the totaldielectric surface neutralised during the ESD. This flash-over is represented in the classical electrical set-up by a capacitance added to those representing the satellite but this capacitanceshould be replaced by a "flash-over simulator" i.e. a set-up which could deliver the real shape over time of the flash-over current.Two main questions have to be answered to lead to a more representative set-up :- Which maximum surface can be neutralised by the flash-over during an ESD?- Is the flash-over current critical for secondary arc initiation and sustainment?To answer the first question, an experiment has to be performed on a complete solar panel. A large solar panel (8m2) will be tested in a large vacuum chamber with two electron guns facingthe panel. The panel will be biased and charged under the electron flux to reach an Inverted Voltage Gradient state. The panel will be instrumented to detect the blow-off and flash-overcurrents i.e. each string will be cabled and instrumented independently. Then a test in presence of plasma has to be performed and the adaptation of a plasma source has to be considered andplanned to check for the comparability between tests performed with the electron gun and in plasma. The experiment shall be repeated for other capacitance values (to simulate other types ofcover glasses). Once the equivalence of the plasma environment with the electron environment has been proven for at least two different capacitance values, the remaining part of theparametric study will be performed in a plasma environment that is easier to use. Based on the test results on the large panel, a flash-over simulator will be developed and validated to allow allfuture qualification tests to be performed on small coupons (2x2 cells) in plasma environment.

Annex 2Page 283. SPACE SEGMENT - PAYLOAD3.1 Payload – System and ArchitectureRef. Activity Title Procurement Policy Budget(KEUR)5A.011(08.153.45)Objective:Description:Planned TenderIssueOn ground beam forming techniques Open Competitive Tender Type: C 300 1Q 2009 12Estimated Duration(months)The activity is to evaluate the potential benefit of on-ground compared to on-board beam forming in terms of complexity/mass/power and cost for missions with a high number of spot beamslike Mobile Satellite Systems.On-Ground Beamforming (OGB) is an attractive technique allowing a high degree of satellite coverage flexibility while maintaining an affordable satellite payload complexity. OGBtechnology is used on a new generation of hybrid mobile satellite terrestrial networks under development in the USA.Potential advantages of dynamic and adaptive beam forming techniques are widely documented and recognized. Various kinds of flexibility, adaptations and real time pattern control(including interference mitigation and Multi-Input-Multi-Output processing) could be provided to increase the overall telecommunication system traffic capacity or to render the system robustto interferences. The full exploitation of the state-of-the-art techniques in an on-board processor will demand technologies currently at the limit of state of the art.The concept to perform the demanding processing on ground to implement the more sophisticated techniques was first seen for the US TDRSS S-band multiple access service and has recentlybeen adopted by US Mobile Satellite Services (MSS) operators (ICO, MSV, Terrestar). The OGB techniques rely on the transfer of radiating element signals to ground and vice versa. Theforming of beams is realised on-ground with all the flexibility offered by on-ground computer processing power (number of beams, beams’ shapes, adaptive processing, interferencecancellation, MIMO, etc.). The OGB results in a simplification of the on-board routing functions. Tasks to be carried out shall include:• Candidate missions identification• Efficient ground/space partitioning and payload architecture definition• Return and Forward links beam forming requirements definition• Beamforming impairments analysis (mismatches, different frequency conversions, propagation channel, different Doppler per channel, etc.) and countermeasures• Techniques for feeder-link bandwidth reduction (e.g. combined A/D conversion, vector quantization and high-order modulation transmission of the data-flow)• On-ground advanced signal processing algorithms• End-to-end simulator development for identified application scenariosSpace and ground-segment functionalities shall be jointly addressed to identify an effective architecture and to assess overall performances and cost. A roadmap of key technologicaldevelopments shall be prepared to ensure European industry competitiveness in this strategic field.

Annex 2Page 29Ref. Activity Title Procurement Policy Budget(KEUR)5A.015(09.153.34)Objective:Description:Architectural Definition and Preliminary Design of a Future Flexible Multibeam Ka bandpayloadPlanned TenderIssueOpen Competitive Tender Type: C 350 2Q 2009 12Estimated Duration(months)To perform the architectural trade-off and preliminary design of a next generation of Ka band flexible broadband multimedia payload. The payload design shall be driven to match varyingtraffics per beam during the mission life and shall therefore allow on board flexibility in terms of variable bandwidth and RF power to beams, according to the traffic. The use of physicallayer with Adaptive Coding and Modulation shall be assumed for the payload parameter optimisation (i.e. antenna patterns).First, some examples of likely future traffic per beam scenarios shall be identified. In particular, these scenarios will identify beams with higher/lower traffic expected and with higher/lowerdegree of uncertainty in their traffic estimation. Based on these scenarios, and assuming one specific satellite platform, the contractor will then identify different payload architectures thatcould efficiently cope with the levels of traffic and associated uncertainty. In particular, the payload can make use of different groups of beams assigned to either classical ‘non flexible’channelised hardware or to ‘flexible’ hardware implementation based on the use of MPAs and/or flexible TWTAs. Different shares between MPAs and flexible TWTAs may be considereddepending on the level of flexibility required by the different beams. The C/I requirements will be analysed in depth. In particular, the use of a physical layer using ACM techniques can leadto side lobe level relaxations and to increase the level of frequency reuse. The proposed payload architectures will then be evaluated and adequately optimised. The selection and optimisationof payload architectures shall be performed using results from multi dimensional link budgets. Payload accommodation exercise for the final selected and optimised payload will then follow.Key performances will be defined for each equipment and the required development effort will be estimated.Ref. Activity Title Procurement Policy Budget(KEUR)5A.016(09.153.35)Objective:Description:Planned TenderIssuePayload On Board Self Calibration Techniques Open Competitive Tender Type: C 200 4Q 2009 12Estimated Duration(months)The aim of this activity is to define on board self calibration techniques for payloads using distributed elements such as active/semi-active antennas and MPAs to identify architectural optionsfor their implementation. A trade-off between the options will be performed and the feasibility will be analysed. Emphasis will be given to the definition of the type of calibration techniqueand signal to be used (single tone, multi-tone, modulated carrier, spread-spectrum signal, etc.).With the increasing complexity of payload architectures using active/semi-active antennas and MPAs, the achievement of good amplitude and phase tracking becomes compulsory to meet theexpected payload performance. In particular, this is related to end-to-end delay, amplitude and phase tracking as well as synchronisation since payload architectures are using one or several ofthe following equipments: Multi Port Amplifier, active/semi-active antennas, multiple frequency conversion stages, separated LOs, Digital Signal Processors (making use of several Analogueto Digital and Digital to Analogue converters), etc. Equipment performance variation over temperature and lifetime would also have an effect on the tracking and shall be taken into account inthe calibration system analysis and evaluation. The activity will focus on techniques for end-to-end calibration and tracking of amplitude and phase of parallel paths in payloads usingdistributed elements. Calibration and tracking of amplitude and phase of individual equipments such as MPA is addressed in another ARTES 5 activity.In addition, it should be noted that theintroduction of an overall payload calibration system could possibly simplify the stability, tracking and delay performance requirements currently specified for each RF, Analogue and Digitalequipment.The required technology developments will be identified for the preferred calibration technique.

Annex 2Page 303.2 AntennaRef. Activity Title Procurement Policy Budget(KEUR)5B.019(07.153.24)Objective:Description:Planned TenderIssueLarge deployable Antenna Integration on European Spacecraft Open Competitive Tender Type: C 300 Priority 2 12Estimated Duration(months)The Large Deployable Antenna EQM is expected to be available late 2006. This activity deals with the accommodation of this antenna on one European telecommunication spacecraft.Starting from antenna geometry and RF/mechanical/thermal analysis available from LDA development, the contractor will perform satellite accommodation and identify all critical systemsaspects (launcher fairing, AOCS, RF performances, Mechanical behaviour, etc.).The need to prepare 9-25 m Large Deployable Antennas for their integration on European platforms is identified as a combined System and Technology activity. Although commonassumptions with existing antennas in terms of I/F have to be considered, it is understood that the accommodating spacecraft will have to provide dedicated resources for such kind of largeantenna subsystem. Aspects such as geometrical envelope in stowed and deployed configurations, AOCS compatibility, mechanical I/F and RF compatibility have to be addressed to concludeon the compatibility of this kind of antenna with European platform. This activity shall be performed considering the Large deployable Antenna under development in Europe. A developmentplan identifying all actions to be performed for a commercial application using this antenna shall be provided. Expected deliverables Technical notes on multidisciplinary analyses involving:"mission scenario" system analysis "accommodation" RF performances "Assessment of mechanical/thermal antenna environment and behaviour when installed on the spacecraft"Development plan. This activity is included in the 2004 “Telecommunication reflector antenna” harmonisation dossier.NOTE: This activity has been designated as "Priority 2". Priority 2 activities will only be initiated on the explicit request of at least one delegation.

Annex 2Page 31Ref. Activity Title Procurement Policy Budget(KEUR)5B.044(07.153.04)Objective:Description:Planned TenderIssueAntenna Reflectors using European Mesh Open Competitive Tender Type: C 750 Priority 2 16Estimated Duration(months)The objective is to study antenna reflectors using mesh technology with applications in frequencies up to Ka-band. The study shall include the design of a reflector using mesh technology andrealisation and test of representatively sized mesh samples suitable at least for Ku band.The need for larger sized apertures has been identified for different telecommunication applications, namely Mobile Communications (currently L and S band), Broadcast applications (todaytypically in C and Ku-band and in near-future Ka-band) and high data traffic spot-beam type applications (Ka-band). For these applications the antenna configurations and requirements areknown. The knitted mesh has been identified as an enabling technology for several of these antenna configurations. It is therefore important to secure such technology in Europe. Specialknitted mesh with its elastic properties when appropriately tensioned allows realisation of antennas for such applications for various reflector antenna configurations for the mentionedfrequency bands. Recent developments in the US and Japan have demonstrated applications for antennas at up to Ka-band. Its application potential has been investigated in part also in Europefor the lower frequency bands with advanced demonstrators for deployable (for instance 5 m) reflectors and more recently in the frame of the large deployable reflector qualification model.That demonstration obviously included the excellent benefit of mesh for stowed versus deployed volume (packaging during launch as needed for deployable reflectors).Furthermore, adaptation to desirable coverage or flexible multi-beam scenarios is becoming more and more important, with the longer lifetime of satellites and changes of interests for theproviders during the lifetime, this require adaptive antenna configurations. All these mission applications put strong demands on the costs and therefore on the critical elements, in particularthe antenna. The knitted mesh is identified as an enabling technology for such antenna configurations.Dedicated explorations and current experiences indicate very well, that knitted mesh - for different frequency band applications - can be realised with European knowledge and capabilities(available material, processes and know-how). The implementation of a source of European mesh is a long-term strategy and needs a demonstration with a realisation of space-qualified meshsamples.The activity concerns the reflector design and the definition of the requirements on the mesh. This shall be performed for the wide range of frequencies up Ka band. Then it will include theimplementation and demonstration of a source in Europe to provide mesh for different antenna applications up to Ka-band. Representative samples suitable for Ku band shall be produced ofsufficient size and number and validated by tests including: RF (including PIM), mechanical/structural, thermal, thermo-elastic, thermal cycling and ageing. Mesh handling and integration onreflector supporting structures shall be closely investigated via sample testing.NOTE: This activity has been designated as "Priority 2". Priority 2 activities will only be initiated on the explicit request of at least one delegation.

Annex 2Page 32Ref. Activity Title Procurement Policy Budget(KEUR)5B.050(07.153.57)Objective:Description:Planned TenderIssuePolarisation flexible (dual linear/dual circular) feed system Open Competitive Tender Type: C 350 Priority 2 15Estimated Duration(months)The objective of the activity is develop and test an engineering model of a transmit/receive compact feed that can be reconfigured in flight to dual linear or dual circular polarisation.Due to historical, technical and regulatory reasons, satellites at C, Ku and Ka band operate with different polarisations. The recent operator merging is expected to lead to fleet rationalisationas demonstrated by the purchase of PanAmSat by Intelsat, the fist using C-band linear polarisation and the second mainly circular polarisation. It has been identified that changing the radiatedpolarisation of the space segment is by far less expensive than upgrading the large number of user terminals. It is expected that future telecom missions at C, Ku and Ka band will requiremultiple polarisation reconfiguration capabilities (dual linear and dual circular) to provide service over different geographical areas (orbital relocation over different ITU zones). Feeds mustbe able to operate in transmit and receive mode and to be in flight reconfigured either in linear or circular polarization. Innovative methods for selecting between circular and linearpolarisation shall be investigated, minimizing feed losses, polarisation purity impairment, reliability and mechanical complexity. The proposed concepts will be studied in detail up to thedesign of complete feed, including all high power building blocks (OMT, Polarisers, Filters, Exciters, Switches, Phase shifters,.. as required) with due consideration for multipaction and PIMissues.An engineering model will be developed and tested of the preferred concept.NOTE: This activity has been designated as "Priority 2". Priority 2 activities will only be initiated on the explicit request of at least one delegation.Ref. Activity Title Procurement Policy Budget(KEUR)5B.065(09.153.36)Objective:Description:Planned TenderIssueMultiple beam port-to-beam synthesis methodology and antenna architectures Open Competitive Tender Type: C 300 Priority 2 18To develop a multi-beam multi-frequency tool for the combined optimisation of the complete antenna system.Estimated Duration(months)The capability to optimise the complete antenna system is required for user terminal antennas with wide scan range and polarisation tracking as well as for large multi-beam satellite antennas.In both applications there is a strong need to optimise the antenna architecture to reduce complexity and avoid component over-design. The synthesis of efficient antennas for multiple-beammulti-frequency dual-polarisation coverages is a complex task involving a large number of components in the chain. Furthermore there is a growing need to be able to address multiple andquite different configurations and compare them in a unified systematic way. A tool optimising the whole antenna system is expected to result in improved overall performances and in aproper balance between the requirements on the individual antenna components. The increase of computing power has enabled very sophisticated synthesis methodologies for the initialdefinition of the necessary characteristics of the individual components, and optimisation methodologies for the refinement of their design. Independent optimisation tools exist for mostantenna architecture components, but nothing is available for the initial synthesis and the global refinement of the overall antenna architecture and configuration. Furthermore some areas, likethe optimal selection of beam generation weights, which are very critical in multi-beam multi-frequency antennas as well as for beam hopping and for beam re-configuration, are not yetproperly addressed. The activity will cover these areas by either extending the reach of existing tools or developing new ones, and achieve the overall objective by assembling the differentcomponents into a tool for the overall antenna design to be included in the European Antenna Modelling Library. The resulting design tool will be applied to operational test cases derivedfrom system studies.

Annex 2Page 33Ref. Activity Title Procurement Policy Budget(KEUR)5B.066(09.153.09)Objective:Description:Planned TenderIssueActive Multibeam Sparse Array Demonstrator Open Competitive Tender Type: C 750 3Q 2009 24Estimated Duration(months)The objective of this activity is to design a Ka-band Active Multibeam Sparse Array Antenna considering satellite interfaces and accommodation constraints and to validate the RFperformances by a demonstrator model.Active Direct Radiating Arrays allow generating multiple beams for broadband satellite communication systems with a high degree of reconfigurability and flexibility. They have been rarelyimplemented because of their complexity and cost. These drawbacks are due to the high number of active and radiating elements, and to the poor efficiency of the HPAs (also associated totapering). Active Sparse Arrays with equal amplitude distribution represent a valid alternative to periodic arrays. They offer the advantage of minimizing complexity and cost of the entireantenna system. In fact, a periodic arrays may generate an equivalent tapering by changing the elements positions and allow:- to reduce the number of elements;- to realise phased arrays with a simplified BFN (no amplitude control);- to increase the DC to RF efficiency of active antennas.These major advantages, combined with recent improvements in RF HPAs, may enable drastic improvements in multibeam active arrays.Description of the activity:- pre-design of the Direct Radiating Array including RF, themomechanical and integration aspects.- trade-off on the architectures and technologies reducing power dissipation and mass.- definition of possibly self standing thermal control with dedicated North/South radiators to ease array integration.- establishment of satellite accommodation on earth deck minimising I/F between platform and DRA.- optimisation of the sparse DRA architecture and the performance including: gain/EIRP, isolation, mutual coupling, intermodulation, DC-to-RF conversion efficiency, considering thestate of the art transmit active modules in solid state or Mini-TWTAs.- identification of the required technology improvements and extrapolation of the full antenna performances. Concerning the implementation of the transmit active modules the followingoptions shall be traded-off:- Solid state technology. Emphasis shall be given to wide bandgap semiconductor materials (e.g. GaN) that have been identified as key disruptive technologies for SSPAperformance improvements (RF power, efficiency, thermal properties). Attention shall be given to the thermal properties that will allow increasing baseplate temperatures withsimplified thermal control. The reliability is important as well.- Mini-TWTAs technology Low saturation power TWTs with high efficiency, low dissipated power, small size and footprint, would allow direct connection of TWTs to radiatingelements.- Design, manufacture and test a demonstrator representative of a full antenna aperture. Regarding the active devices, from input beam ports to radiating elements, the use oflaboratory equipments might be considered provided that array performances over the angular domain and frequency range can be validated by tests.Preparation of a cost estimate and comparison of cost with existing designs.

Annex 2Page 34Ref. Activity Title Procurement Policy Budget(KEUR)5B.067(09.153.37)Objective:Description:Planned TenderIssueKu-band High power feed components Open Competitive Tender Type: C 400 2Q 2009 12To design and test an EM of a Ku-band feed system having more than 4 kW input power and dedicated Transmit and Receive access.Estimated Duration(months)Large European telecom satellites are requested to provide a large number of channels (typically > 2 x 20 channels) resulting in more than 4 kW input power at feed level. For such Ku-bandmissions, satellite primes normally decide to reduce risk splitting the power between two different Tx antennas. However, to be more competitive it would be highly desirable to consider onlyone Tx antenna or even better one Tx/Rx antenna. This will ease the satellite accommodation of the Ku-band mission and at the same time, the satellite will be able to accommodate moreantennas for other missions. Both Ku-band FSS and Ku-band BSS have to be considered.There are two standard architectures for Ku-band Tx/Rx antenna feeds. The first one consists in the following components: horn + OMT + Tx/Rx diplexers and the second one: horn + OMJwith Tx filters (or exciter) + OMT in Rx (Polarisers have to be added to both architectures in case of circular polarisation). The critical component in terms of power handling in the firstarchitecture is the Tx/Rx diplexer and the OMT whereas for the second one it is the OMJ with Tx filters. The OMT of the first configuration has been already studied in past ARTES contractshowever, it is not the case for the high-power diplexers which are the bottleneck (i. e. there are OMTs capable of handling 4KW but the diplexers, even if there is one per polarisation, are notable to handle the necessary input power). It would be highly desirable to improve the diplexers in terms of power handling and insertion losses with PIM-free manufacturing technologies.For this last point it is also important to locate the diplexer as close to the OMT as possible within the feed system to avoid long waveguide runs that are prone to generate PIM with potentialimpact at a later stage of integration. The development proposed here shall consider having dedicated Tx and Rx accesses at feed level, the splitting being done either by diplexers or filters.The OMJ of the second architecture is more complex to design because it has to be calculated with its Tx filters. However, the power is split into two filters per polarisation which is a clearadvantage in terms of power handling. This topology should be studied further and compared to the previous one. With the help of state of the art electromagnetic tools, these antenna feedarchitectures as well as new ones can be revisited to improve their performances. Recent developments in the field of high power waveguide components could be applied to design newantenna feeds with low losses, high power handling, high RF multipaction margins and PIM free manufacture. A trade off needs to be made among different configurations of Tx/Rx feedsand select one candidate capable of handling > 4KW. Thermal control will be an important part of the trade-off since the selected feed will probably need to accommodate radiators forthermal dissipation.An Engineering Model will be designed, manufactured and tested.Ref. Activity Title Procurement Policy Budget(KEUR)5B.068(09.153.10)Objective:Description:Planned TenderIssueMulti-mission and Multi-frequency reflector antennas Open Competitive Tender Type: C 600 3Q 2009 18To design, manufacture and test an EM of an antenna feed system for multi-mission (Ku- and Ka-band) reflector antenna systems.Estimated Duration(months)For European satellite operators to take advantage of emerging markets for telecommunications systems, whilst also serving existing markets, it is necessary to embark several largedeployable antennas per satellite. For example, Eutelsat W3B, which serves Europe and Africa, and Eutelsat W7, which serves Europe, Africa and Eurasia, both have up to 4 deployed Kubandreflectors, whilst the Earth decks are heavily populated by the Ka-band antennas. Consequently, the future expansion of missions/services on the same satellite is limited by antennaaccommodation issues. Techniques to combine missions by the use of frequency (FSS) or polarization (PSS) filtering, as used in other domains such as millimetre wave quasi-optic boxes, orearth station beam-waveguide multi-frequency reflectors may be considered for space telecommunication antennas. Also, using multi-frequency (Ku/Ka) feeds in a focal array eitherindividually or combined with dedicated beam forming networks per frequency is of major interest for realising multi-mission antennas. This activity will investigate the feasibility of thesemulti-frequency, multi polarisation feeds possibly in a focal array and either used individually or combined. A selected most promising concept will be designed, analysed, manufactured atEM level and RF tested.

Annex 2Page 35Ref. Activity Title Procurement Policy Budget(KEUR)5B.069(09.153.11)Objective:Description:Planned TenderIssueMedium size unfurlable reflector antenna Open Competitive Tender Type: C 1500 3Q 2009 18Estimated Duration(months)To design, analyse, manufacture and test an Elegant Breadboard of a 4 to 7 metre reflector for telecom satellites. Special attention shall be given in deployment reliability and accuracy, RF,PIM and thermo-elastic behaviour.Reflectors are typical risk area for satellites if no qualification model is available before project start. Technologies available today in Europe such as thick shell, thin shell with stiffeners, ultralight reflectors and dual gridded reflectors are able to handle Ku-band, and sometimes up to Ka-band, but are limited respectively to 3.8 meters (launcher fairing constraint for one piecereflector) and 2.5 meters ( thermo-elastic behaviour). On the other hand, for L and S band frequencies bands, a Large Deployable Antenna has been developed up to qualification level for theMobile Satellite Service programmes with reflector diameters in the range of 12m to 15m (with grow capability). Reflectors in the range from 4 to 7 meters are not qualified in Europe whileseveral applications require them such as:- Digital Audio Broadcast at S-Band- European linguistic and multi-beam coverage at C-Band and possibly Ku-Band- Intersatellite links at S-band- Signal intelligenceTo fulfil the needs for such missions, reflector shall have:- A diameter in the range 4 to 7 meters (even 3 meters for low cost, small launcher, fairing compatibility might be of interest)- An offset configuration and a shaping capability- An in flight surface accuracy of typically one wavelength/ 50- A stowed envelope compatible with small launchersAmong the different reflector architectures identified so far, a concept based on existing CFRP reflector for the central part and on either rigid/foldable panels/reflective mesh/CFRS isconsidered as a good candidate. This concept may allow securing the development with proven technologies where the most critical constraints exist in term of power handling and surfaceaccuracy. This concept will be traded-off with other concepts such as unfurlable, inflatable, membrane and shape controlled by rib bending and other concepts. After selection of the mostpromising concept, the activity will address antenna RF analysis, reflector RF/ mechanical/ thermal design/analysis, deployment reliability and accuracy and reflectormanufacturing/development of an Elegant Breadboard sufficiently representative to allow meaningful RF/ PIM tests, deployment tests and thermo-elastic test.

Annex 2Page 36Ref. Activity Title Procurement Policy Budget(KEUR)5B.070(09.153.38)Objective:Description:Planned TenderIssueHigh Accuracy Antenna Pointing System Open Competitive Tender Type: C 350 2Q 2009 16Estimated Duration(months)To analyse antenna pointing errors budget and investigate the techniques and technologies required to increase pointing accuracy for broadband multiple high gain pencil beams. To identifythe methodology and the hardware/software required for the antenna pointing determination and correction for single and multiple feed per beam concepts. To elaborate the achievableantenna pointing error budget and associated development plan.Broadband communication request a large number of highly directive beams to be generated. These missions are currently performed using the Ka band and for the future the use of Q/V-bandis considered. In order to optimise the use of satellite power resources, the antenna footprints need to be pointed to match their respective service area. Moreover, missions call forfrequency/polarization reuse among the beams. This imposes severe constraints on sidelobe and cross-polarisation isolation between beams, possibly originated from different antennas, tomeet C/I requirements. These constraints translate in stringent pointing requirements and antenna pointing accuracy shall be improved. Antenna Pointing System using RF sensors have beendeveloped recently and are now available and implemented in all multiple beam applications. The state of the art regarding antenna pointing accuracy is ±0.05 deg. This figure, which alreadyinduce typically a 1 dB decrease of the End Of Coverage Gain for the typical 0.5/0.6 degree beamwidth, shall be improved to meet the demand of even smaller beams (0,3/0.4 deg). For thesesmaller beams a target of ±0.03 deg for the antenna pointing accuracy will be considered. Having smaller beams is considered as of major interest to increase the frequency re-use capabilityover a given geographical area (such as Europe) for a better use of the frequency resource and allow a power to beam allocation with a better granularity to match traffic demand. Severalsources of error affect the antenna pointing such as mechanical misalignment, satellite pointing, platform and antenna thermal deformation, and manufacturing imperfections. Most of theseerrors can be either measured on -ground or compensated with the Antenna Pointing System. This study will address all the contributions to error budget. For the major ones, a thoroughanalysis will be performed to identify the techniques and technologies required to decrease the contribution to pointing errors. It will be considered that both very small sized beams and verylarge coverage areas are required and may enable an alternative pointing technique to the sum and delta beam systems implemented today. Synergies with solutions considered for mobilemissions, yaw determination from separated beams, use of data available from platform AOCS to improve the optimal pointing for a set of beams, thermo-elastic deformation calibration areexample of possible ways forward. Regarding the ways to compensate for the depointing, all high frequency solution will have to be investigated for reflector antennas using single feed perbeam and multiple feed per beam. Several beams being generated by the same reflector, the pointing system shall be optimised for best EOC gain and C/I performances considering all beamsgenerated by the mission. This study will be concluded by an update of the pointing budget and the identification of the necessary hardware and software required to validate the proposedfigures.

Annex 2Page 37Ref. Activity Title Procurement Policy Budget(KEUR)5B.071(09.153.12)Objective:Description:Planned TenderIssueKa-band integrated active feed for multiple beams antenna Open Competitive Tender Type: C 600 3Q 2009 12To manufacture and test an EM of a Ka-band integrated active feed chain including a radiating element with an OMT or polarizer, a filter, a redundancy switch and LNA’s.Estimated Duration(months)Multiple beam receive antennas operating at Ka-band require a very large number of long waveguide runs from the feed clusters to the Low Noise Amplifiers (LNA) located in the platform.The use of waveguide is imposed by the Noise Figure requirements but induces very large constraints on satellite accommodation and mass budgets. The use of active feeds (feeds includingredundant LNA) is considered of high interest to reduce the overall complexity and possibly operate at lower temperature achieving better Gain and Noise Figure performance. It is expectedthat making use of the same technology for the different feed elements (OMT or polarizer, filter and LNA) and investigating spin-off from developments at millimetre wave (science, earthobservation, etc.) would allow identifying more integrated and less complex feed assembly.Integrated feed for Ka band missions have already been developed as part of ESA contracts. However these developments were made for multi-beam per feed concept (e.g. Focal Array FedReflector) with 1λ to 1.2λ feed spacing resulting in specific selection of technologies for the implementation of the feed elements technologies.Single feed concept or multi feed per beam concept with long focal length are now considered for multi-beam antenna. These concepts offer a larger spacing between elements (~3 to 5λ) thusmaking possible the integration of functionalities in the feed element which have not been considered in the previous ESA studies (e.g. the input filter, the low loss redundancy switch) butalso the use of new technologies which have the possibility to improve the performance and will allow further integration level. For example, for the implementation of the OMT or polarizer,filter and redundant LNA a single technology making use of suspended stripline on organic substrate, micromachining techniques or metallised plastic could be considered.The aim of the activity is to investigate the feed architectures and technologies that are able to integrate several elements of the same feed chain at once rather than having each componentmanufactured separately. This activity will look at integrating a radiated element, an OMT or polarizer, a filter, a redundancy switch and associated LNA’s all together in the feed system. Thedevelopment shall take into account large scale production and future integration in feed cluster. This development should investigate the applicability to both single feed per beam andmultiple feed per beam concepts. To ensure state of the art performance, for the LNA metamorphic technology could be considered but the LNA MMIC will be an off-the-shelf item bought infor the activity and MMIC development is not part of this activity. Promising technologies for the selected applications will be traded-off and one feed chain Engineering Model will bedesigned, manufactured and tested.

Annex 2Page 383.3 Repeater EquipmentRef. Activity Title Procurement Policy Budget(KEUR)5C.070(07.153.09)Objective:Planned TenderIssueLightweight RF power cables with high phase stability Open Competitive Tender Type: C1 500 1Q 2009 24Estimated Duration(months)The objective of this activity is to design, manufacture and test RF cables with excellent phase stability and with a significant reduction in the overall weight compared to currently availablecables.Description:This activity shall focus on the development of ultra light RF cables capable to handle the RF power signals within modern telecom payloads. The typical power levels that these cables willhave to handle are up to 50 watts CW. Phase changes in the RF signal due to pour mechanical stability and heat dissipation from the inner conductor have become a new technological/designchallenge. Presently, RF power cables have a serious limitation imposed by the poor thermal conductance from the inner conductor to the outside of the cable. This also implies poor phasestability which is an important requirement when combining amplifiers in reconfigurable or extremely high power payloads.The necessary theory and modelling shall be developed to predict thermal characteristics, loss, phase stability and RF breakdown in coaxial lines including the cable and connectors.An engineering model of a cable shall be designed, manufactured and tested. The cable shall have a reduction in mass in the order of 30-40% compared to currently available cables with anequivalent loss and shall meet stringent requirements on phase stability.Ref. Activity Title Procurement Policy Budget(KEUR)5C.085(08.153.51)Objective:Description:Planned TenderIssueOpto-microwave wideband reconfigurable receiver Non-Competitive Tender: DN 2000 1Q 2009 30Estimated Duration(months)This activity is to design, manufacture and test an Engineering Model of an opto-microwave wideband reconfigurable receiver front-end (OWR-RFE) for broadband transparent telecompayloads.In the TRP contract Sat’n Light (Contract No. 15695/01/NL/ND) optical technologies and techniques were investigated and developed for broadband transparent analogue repeaters. Thefeasibility was demonstrated of optical distribution of microwave LO signals, optical frequency down-conversion and optical cross-connection in a proof-of-concept demonstrator. Given atypical telecom satellite lifetime of 15 yeras, a flexible repeater architecture that can be adapted to the evolving telecom traffic and connectivity needs is essential for the satellite operators. AnOWR-RFE offers a system solution with superior advantages compared to a full RF/microwave implementation in terms of wideband operation, signal transparency, flexible crossconnectivity,scalability to multiple antenna beams and mass. An OWR-RFE represents the core part of a transparent analogue repeater, but can also be used as a pre-processor for a digitalprocessor or as part of a receiver antenna with a digital BFN.Within the activity, the state of the art shall be reviewed of optical technologies and building blocks, with special attention to the recent improvements (e.g. ESA ARTES-5 activities onMOEMS switches, optical amplifiers, modulators, etc.), and the system level requirements shall be established in terms of cross-connectivity, reconfigurability, system size (number of beams,channels, frequency re-use factor), transparency to multiple microwave bands, etc. The overall OWR-RFE shall be designed according to the end-to-end system level requirements. Thisincludes optimization of the physical partitioning and assessment of (optical and opto-microwave) packaging and integration concepts to demonstrate the expected reductions in mass, size andpower consumption. An EM model shall be designed, manufactured and thoroughly tested.This activity shall also include the delta technology development of the individual optical components of the OWR-RFE to meet the system level requirements. Modifications at componentand packaging levels shall be assessed taking into account interfacing, partitioning and integration aspects of the overall OWR-RFE design.

Annex 2Page 39Ref. Activity Title Procurement Policy Budget(KEUR)5C.087(08.153.32)Objective:Description:Planned TenderIssueSSPAs with European GaN devices Open Competitive Tender Type: C 1200 Priority 2 36The activity is to design, manufacture and test two Elegant Breadboards of SSPAs using European GaN devices and operating in different frequency bands.Estimated Duration(months)GaN technology enables SSPAs with significant increases in RF output power and efficiency compared to other semiconductor technologies. The GaN technology is capable of operating athigher temperatures than for example GaAs technology. This may enable new types of application such as direct radiating arrays and reduce the requirements on the thermal control.Simplification of the design and size reduction with higher operational voltage and higher power density leads towards overall cost reduction at equipment level.The scope of the activity is focused on the validation of the GaN technology developed in the framework of the EU GREAT2 initiative and provision of feedback to further enhance thetechnology. The requirements are to be derived on solid-state high power amplifiers for commercial and institutional telecommunication satellites required in mid term future from UHF bandup to Ka-band. On this basis Elegant Breadboards of two SSPAs operating in two different frequency bands (most probably in L and C Bands) with power levels of several tenths of Wattswill be designed, manufactured and tested. The SSPAs shall be implemented using GaN devices coming from the EU GREAT2 initiative, which aims at significantly improving the reliabilityof the European GaN technology,. The SSPA design and develop shall allow for several iterations incorporating new versions of the GaN devices as they become available. Most of thebreadboard effort shall be focused on the optimization of the output stage. The final Elegant Breadboards shall use the devices finally resulting from the GREAT2 initiative.NOTE: This activity has been designated as "Priority 2". Priority 2 activities will only be initiated on the explicit request of at least one delegation.Ref. Activity Title Procurement Policy Budget(KEUR)5C.088(08.153.33)Objective:Description:Planned TenderIssueLow phase noise reference oscillator Open Competitive Tender Type: C 500 2Q 24The activity is to design, manufacture and test an Engineering Model of a compact and low-cost European reference oscillator with low phase noise and high stability.Estimated Duration(months)The current development and implementation of high order and bandwidth-efficient modulation schemes significantly strengthens the phase noise and stability requirements on the localoscillator. At the same time, flexible payloads require some frequency agility of the local oscillators. The introduction of agility in converter equipment implies that complex architectures (e.g.dual conversion scheme) with multiple LO’s will be used. The generation of these LO’s will be using complex frequency synthesis and conversion schemes, using reference oscillators (in the10 to 25MHz range) with very low phase noise and high absolute frequency stability. A thorough trade-off shall be made of various designs considering different technologies for the activeparts and a crystal being used as resonator. Temperature stabilisation and the required control loops shall also be addressed. A preferred design shall be selected. The target is to have withreference oscillator for which the mass and volume performances are improved while improving phase noise performances from about -150 dBc/Hz to -160 dBc/Hz at 1 kHz. offset.An Engineering Model shall be designed, manufactured and tested of a the preferred design meeting the demanding phase noise and stability requirements. The reference oscillator shall useEuropean technology to the maximum extent and shall have a competitive recurrent cost.

Annex 2Page 40Ref. Activity Title Procurement Policy Budget(KEUR)5C.093(09.153.39)Objective:Description:Planned TenderIssueCompact High Power S -band Output Matrix Open Competitive Tender Type: C 450 Priority 2 24Estimated Duration(months)The objective of this activity is to develop and test a Breadboard of a large compact multiport coupler for high power output matrices needed for 8x8 or larger MPAs in S-band. RFperformance, mass, footprint and cost savings shall be evaluated.Output matrices such as Butler Matrices are an enabling technology for multiport amplifiers (MPA) to achieve beam switching and steering in satellite systems. Standard output matrixconfigurations employed today consist of several stages of hybrids that are interconnected. For matrices larger than 4x4 this requires crossovers of connections resulting in complexassemblies. However, existing concepts of n -dimensional Riblet couplers or other single layer coupling concepts could offer considerable footprint reduction and significantly simplerassemblies. For output matrices this opens the possibility for improved thermal designs and less risk of PIM due to reduced number of piece parts as well as enabling compact high powerequipments for next generation satellite systems handling twice the power per channel compared to current designs. In addition it is well known that noise reduction of MPAs can be achievedby careful design of the output matrix. Thus the propagation of intermodulation products shall be analysed and considered in the selection of the design concept In order to demonstrate theadvantages and limitations of the developed concepts a compact S-band high power output matrix Breadboard shall be built and tested.NOTE: This activity has been designated as "Priority 2". Priority 2 activities will only be initiated on the explicit request of at least one delegation.Ref. Activity Title Procurement Policy Budget(KEUR)5C.102(09.153.40)Objective:Description:Planned TenderIssueInput Filters for L-, S-band applications Open Competitive Tender Type: C1 400 4Q 2009 24The objective of this activity is to manufacture and test breadboards of a new class of compact low loss L-, S-band input filters.Estimated Duration(months)Coaxial filters are currently standard technologies for L-, S-band input filters. The technology offers a wide range of flexibility as it can be tailored to narrow bandwidths, but also bandwidthsup to one octave can be achieved whilst maintaining excellent out-of band performance. However, this technology is inherently large and bulky since it is based on TEM air resonators. In thisactivity a new class of input filters shall be developed and tested based on TM mode dielectric resonators. Preliminary work has shown that a resonator footprint reduction up to 50% can beachieved compared with coaxial technology whilst maintaining the same in-band RF performance. However, this need to be carefully traded-off against the spurious performance and a designconcept for in-line and cross coupled filters for complex transfer functions shall be developed. Other challenges exist in mounting the dielectrics, which shall be addressed and solutionssuitable for space application shall be developed. In order to evaluate the developed concepts, different breadboards (3) shall be built and tested to validate this new technology including theachievable bandwidth and out-of band performance.

Annex 2Page 41Ref. Activity Title Procurement Policy Budget(KEUR)5C.103(09.153.13)Objective:Description:Planned TenderIssueReduced Footprint SSPA for telecom payloads Open Competitive Tender Type: C 600 Priority 2 18Estimated Duration(months)The objective of this activity is to manufacture and test an EM of a SSPA with a vertically mounted structure offering a significantly reduced footprint (reduced by >50%) compared to today’shorizontally mounted designs. The aim is to improve the layouts of the payload by enabling a higher density of equipment offering reduced cable lengths and therefore reduced losses.In Telecom satellites for mobile applications, SSPAs are used in the payload. However, due to the high number of SSPAs and the use of the largest side for mounting onto the satellite panels,the payload occupies a large area forcing the use of long RF cables generating high losses (up to 3dB). This can be improved significantly by SSPAs with smaller footprint. The solution existsto reduce significantly the SSPA footprint and it is even proposed by some overseas SSPA suppliers (e.g. Japan). The objective of this activity is to demonstrate the feasibility of verticallymounted SSPA where the RF power modules and drivers are kept close to the bottom of the equipment and therefore close to the heat pipes in the satellite panels. Various solutions can beinvestigated ranging from a simple flip of the whole equipment to a redistribution of the RF modules, and in particular the power and driver modules kept flat mounted and the low power RFsection and EPC mounted vertically. Additionally to this, the activity shall investigate in depth the application of new high performance materials providing improved heat conductivity inimprove the thermal management of such units. New materials (e.g. metal matrix materials) shall be considered for the SSPA structure (instead of standard aluminium) but also for the RFpower modules, while keeping the low weight of the unit. The objective is a footprint reduction >50% with no mass impact or even a mass reduction. The output power target is 20 to 30Wmulticarrier in L or S band for 15dB Noise Power Ratio. The activity aims at developing an EM SSPA structure populated with representative output and driver RF section and withrepresentative components for the EPC (DC/DC converter). As the whole structure would be re-designed with new materials and the internal layout of the equipment may be significantlyaffected, mechanical validation tests (e.g. vibration) and thermal validation tests will be included. The optimization of the thermal management of the overall equipment and of the RFtransition from vertical to the horizontal plane will be carefully studied. Finally the overall footprint might be compatible with a typical Ku (Ka) TWT (i.e. TWTA without EPC). This mayhave the further advantage to allow a standard heat pipe configuration for different types of payloads limiting the engineering costs and improving the level of standardization for payloadlayout and components.NOTE: This activity has been designated as "Priority 2". Priority 2 activities will only be initiated on the explicit request of at least one delegation.

Annex 2Page 42Ref. Activity Title Procurement Policy Budget(KEUR)Planned TenderIssueEstimated Duration(months)5C.104(09.153.14)Objective:Description:High Temperature EPC for GaN SSPA application Open Competitive Tender Type: C 600 3Q 2009 24To investigate the components & technologies limiting the operation of solid state power amplifiers (SSPA) equipments (RF tray integrated with the EPC) at high baseplate temperature (i.e.90-100 deg and above). The selected technologies will be validated through the manufacturing and test of a breadboard of the most critical building blocks and improved processes todemonstrate the feasibility of SSPAs for high temperature operation.GaN technology is expected to offer significant advantages by operating at higher junction temperature (e.g. 150 deg vs. 115 deg for GaAs). A way to exploit this feature would be theoperation of SSPA at higher baseplate temperatures.The major MSS telecom programs using a high number of SSPAs, are indeed limited by thermal dissipation and relaxation on the thermal subsystem will be of great benefit for this type ofmission.An on-going ARTES 5 activity has demonstrated the possibility to increase the baseplate temperature of SSPA from 65deg to 85deg just by replacing the GaAs RF Driver and HPA by thecorresponding GaN based equivalents. In order to go beyond and relax further the thermal subsystem with a SSPA baseplate temperature in the range 90-125deg the limiting factor will be thesurrounding Silicon based electronics primarily the EPC. In this context, this activity aims at reviewing all the components, materials (PCBs…) and assembly processes (attachmentsprocesses…) which limit the design and the operation of high power RF equipment's like SSPA.Two targets of operational cases shall be considered:- Operation at max 100 deg baseplate temperature which would provide the freedom to place the SSPA in the hot area of the satellite platform (simplification of accommodation issues).This correspond to today's heat pipe capabilities (i.e. no evolution on the thermal subsystem technology)- Operation at higher operating temperature around 125 deg which may help further reducing the size of the thermal radiating panels. This is covering the application of high temperatureloop heat pipe currently investigated in the frame of an ARTES 5 activity.The baseline target shall be typical telecom L, S or C band SSPA (30-50W range), where the detailed thermal model of the equipment shall be used to study the behaviour of the limitingelectronics at the required temperature (in particular EPC). This shall be done assuming that the RF chain shall be based on GaN technology and considering the associated implications, inparticular for the EPC which shall feature higher voltage operation on the secondary side (i.e. 30 to 50V).In a second phase replacement solutions for critical components of the EPC, materials and/or assembly processes as well as design of work around solutions potentially eliminating thelimiting components not based on GaN shall be investigated (e.g. high temperature capacitors, evaluation of MOSFETs operation at high temperature, etc…). One potential direction ofinvestigation resides in the area of automotive electronics, where new components are developed to work within engines. Also, advanced materials for EPC PCB with enhanced heat transfercapabilities shall be investigated (e.g. Alunat etc…).In the last phase the performance of the most critical components shall be evaluated and the most critical building blocks of an EPC parts shall be bread boarded and tested at hightemperature.This activity may have implications also in the future for other RF equipments today limited to operation at baseplate temperature of 60-65 deg.

Annex 2Page 43Ref. Activity Title Procurement Policy Budget(KEUR)Planned TenderIssue5C.105 Modelling of Passive Intermodulation in Multicarrier operation Open Competitive Tender Type: C 300 4Q 2009 12Objective:Description:Estimated Duration(months)The objective of this activity is to develop modelling software capable to evaluate and predict passive Intermodulation levels (using realistic modulations and frequency plans) on multicarriersystems from test measurements of two carriers PIM products.With the advent of high power channel communication satellites, a new source of interference, passive intermodulation (PIM), has arisen as a spacecraft performance of considerableimportance. Waveguide flanges and coaxial connectors have been identified as major source of Intermodulation Products in telecommunications satellites. Actual satellite requirements pushtechnology to achieve levels of PIM bellow -200 dBc.In multicarrier systems, PIM prediction is even more complicated than for two carriers, making in some case impossible to qualify by test. In this activity, a modelling tool shall be developedto quantify the level of PIM in multicarrier non-modulated and modulated systems using test data based on two input non-modulated carriers. The modelling shall also consider amplitude andphase of the carriers as inputs plus the temperature range during the mission and will analyse the G/T degradation due to PIM. The modelling software shall be validated through anappropriate test campaign to demonstrate accuracy of predictions versus real test measurements.Ref. Activity Title Procurement Policy Budget(KEUR)5C.106(09.153.42)Objective:Description:Planned TenderIssueFrequency Synthesizer Phase Noise Modelling Open Competitive Tender Type: C2 350 3Q 2009 24Estimated Duration(months)To characterize and model the baseband phase noise performance of the key frequency synthesizer components (transistors, Voltage Controlled Oscillators (VCOs), Phase-FrequencyDetectors, followed by the creation of linear/non linear models of the overall synthesizer loop for phase noise performance optimisation. Finally, a breadboard of a representative synthesiserwill be developed for validation of the design methodology.Due to the introduction of higher order modulations, future satellite telecommunication payloads will require improved phase noise performance. In addition, the introduction of flexiblepayload and tuneable LO sources, call for the utilisation of frequency synthesizers with the associated compromises between tuning bandwidth, frequency setting resolution and phase noiseperformance. As a consequence, the currently used phase noise modelling and design methodologies need to be improved in order to allow better optimised and performing phase noiseperformance. The proposed design methodology is based on the creation of a baseband noise data base, covering the currently used components for the implementation of frequencysynthesizers (i.e. VCO transistors, phase/frequency detectors, frequency dividers. This baseband noise data can then be introduced in a model of the complete synthesizer, that includes asuitable non linear model of the VCO able to correctly model the upconversion process from baseband noise to phase noise modulating the LO signal . The models of the various elements inthe synthesizer will be introduced in an off-the-shelf software tool to calculate the resulting phase noise performance of the synthesizer. The activity shall also investigate the possibility oftopological improvements to the LO synthesizer (i.e. improved VCO design).

Annex 2Page 44Ref. Activity Title Procurement Policy Budget(KEUR)5C.107(09.153.15)Objective:Description:Planned TenderIssue100 W Q/V-band TWT Open Competitive Tender Type: C1 500 4Q 2009 24Estimated Duration(months)To identify the generic technological limits of current high frequency TWTs, to select and develop alternative technologies and, finally, to demonstrate and validate such technologies bydesigning, manufacturing and testing a Q/V-band 100 W TWT Breadboard.The use of the Q/V band is expected to increase and the European TWT manufacturer has identified a potential market outside Europe for Q/V band TWTs.The activity shall start with an extended consultation of the main payload manufactures and satellite operators aiming at refining the preliminary TWT specifications provided by the Agency,especially with respect to the most critical parameters (e.g. power level). The consultation activities shall be complemented by the identification of the technological limits of high-frequencyTWTs, in particular in terms of trade-off between maximum available output power, bandwidth and RF/DC efficiency. The critical parts/sub-assemblies of high frequency TWTs shall beanalysed and the associated constraints shall be fully evaluated. This feasibility study will lead to the finalisation of the specifications and to the preliminary definition of the technologicalbuilding blocks that can be used for next generation high frequency TWTs. The identified high frequency technological building blocks will be validated by designing, manufacturing andtesting a 100 W Q/V-band TWT Breadboard according to the specs identified.The activity will be divided into two phases of 250 kEuro each. In the first phase the technical feasibility will be established and the commercial potential will be evaluated of the preferreddesign. Upon successful completion of the first phase, the second phase will be released for the breadboarding and test of the TWT.Ref. Activity Title Procurement Policy Budget(KEUR)Planned TenderIssue5C.108 High power Ka-band TWT with AlN collector Open Competitive Tender Type: C1 600 Priority 2 24(09.153.16)Objective: To manufacture and test a high power Ka band TWT EM using AlN materials as a high-dissipation ceramic for the TWT collectors (shrink-fitted and brazed technologies) .Description:Estimated Duration(months)Past ESA TRP and GSTP activities have identified Aluminium Nitride (AlN) as an excellent ceramic to handle high power dissipation and high voltage and have proven the suitability of AlNas an electrical insulator in shrink fitted collector. However, the mastering of the material processes as well as of the preliminary treatments need to be improved in order to fully secure theuse of AlN for future high power applications. The activity will comprise a thorough validation of the AlN material for standard shrink-fitted collectors. This will include the batch analysis tocheck the material reproducibility, margin tests on gun-collector sub-assemblies, and tests with a typical mission profile on existing radiation cooled TWTs. Brazed collector technologies willalso be addressed enabling a further increase of the power density. Technological activities shall aim at developing processes for the metallization and high temperature brazing of AlN,without modifying its physical properties. Secondly, several brazed collectors with AlN shall be assembled and tested on dedicated sub-assemblies. Finally, one AlN collector (shrink-fitted orbrazed technologies) shall be integrated and functionally tested on existing high-power (above 170 W) Ka-band EM TWT.NOTE: This activity has been designated as "Priority 2". Priority 2 activities will only be initiated on the explicit request of at least one delegation.

Annex 2Page 45Ref. Activity Title Procurement Policy Budget(KEUR)5C.110(09.153.17)Objective:Description:Planned TenderIssueExtreme environment RF power cables for telecommunication payloads Open Competitive Tender Type: C1 500 Priority 2 24Estimated Duration(months)The objective of this activity is to develop and test RF power flexible cable assemblies capable of surviving extreme environmental conditions when exposed to outer space in GEO orbit.European cable manufactures have already a wide range of flexible coaxial cables for space use but the qualification status of those cables is limited to internal satellite payload environment.In most of the telecommunication satellites there is a need for a few cables being exposed to the free space to connect the antennas, thus lack of proper shielding against radiation andtemperatures normally provided by the actual satellite structure.. Presently, only few American suppliers can deliver cables qualified to survive under extreme space environmental conditions.The main technical challenges to cover are the followings:- To improve the radiation capability of cables to a minimum of 120 Mrads including change of jacket material and/or increase of metal shielding. The best compromise between massbudget and radiation hardness shall be found.- To increase the temperature range of cable assemblies to, at least -100°C to +165°C instead of 0.5°C, +150°C.- In this sense, the main problems to be solved are shrinkage of the dielectric under temperature cycles and the retention of it by the coaxial connector at the interface between cable andconnector. If a gap appears between the insulator of the connector and the dielectric of the cable, the VSWR will be strongly affected and the multipactor threshold will be severelydegraded. The potential ways to solve the problems mentioned are:- Investigate new raw materials for cables to replace expanded PTFE ribbon by an exhaustive comparison of the different suppliers available on the market and then audits of supplierprocesses to understand differences between batches with shrinkage and batches without shrinkage then validation of selected process and material.- Manufacturing process of coaxial cable itself. Investigate the influence of wrapping process (insulator and copper tape as well). A large experience plan is needed because manyparameters can be involved in the result like ribbon pitch, angle of wrapping, overlap, tension applied on tape by cabling machines, type of copper braid, etc. addition, a significantmanufacturing length is necessary each time to validate that the result is stable over the whole manufacturing batch.- Design of coaxial connector: If the shrinkage of cable remains limited it is possible to improve also the behaviour of cable assemblies through a design of the connector that retains thecable dielectric inside connector insulator and block the shrinkage of cable.A baseline design will be established and a cable will be manufactured and tested to verify its performances.NOTE: This activity has been designated as "Priority 2". Priority 2 activities will only be initiated on the explicit request of at least one delegation.

Annex 2Page 463.4 TT&C and Data HandlingRef. Activity Title Procurement Policy Budget(KEUR)5D.016(09.153.18)Objective:Description:Planned TenderIssueCryptographic processor for control of telecom processing payloads Open Competitive Tender Type: C 700 3Q 2009 18Estimated Duration(months)To manufacture and test a breadboard of a standalone cryptographic module to protect communications for control and reconfiguration of advanced payloads (SDR-based). The normalsatellite TT&C path is independent of the path for control and operation of the payload.This activity addresses the early phases of a program to develop a spaceborne cryptographic module to protect space communications for control and operation of advanced telecom satellitepayloads. It is oriented towards establishing requirements and solutions considering in particular the security aspects ensuring advanced telecom payloads can be commanded and reconfiguredalso under adverse conditions. Existing TT&C–based solutions suffer from limitations imposed by old packet protocol standards. New ECSS telecommand and telemetry packet protocolsstandards (ECSS-E-50-04-A and ECSS-E-50-03-A approved in November 2007) offer the required flexibility and data transport capability to accommodate both security overhead and higherdata throughput.The target product of the program is a standalone cryptographic module capable of independent operation in a space environment. It is intended to be used to protect communications forcontrol and operation of payloads independently from the platform command path and aims at providing with a number of advantages over traditional platform TTC solutions (e.g. emergenceof separate security domains mapping with distinct responsible parties, capability for payload and platform security requirements and technology to evolve separately). This module isintended to be used in various application contexts, including the protection of space communications for control and configuration management of commercial communication satellitepayloads implementing on-board digital processing. The target product shall have the capability to be used as part of a larger configuration of a trustworthy system (e.g. communicationsecurity subsystems, information security systems) without undermining the security of the whole. Motivation: Since 2003, the U.S. government, through NSTISSP No. 12 ‘NationalInformation Assurance (IA) Policy for U.S. Space Systems’, mandates the use of appropriate security methods to protect space systems, including commercial communication satellites usedfor government services. In Europe the need for cryptographic capabilities has been identified and the demand is likely to grow as customers and operators focus on the vulnerability ofoperation links and associated risk for the availability of space communication services.The activity will include the system design and the design, breadboarding and test of a cryptographic processor compliant to the ECSS-E-50-03-A and ECSS-E-50-04-A.Ref.: S. Clarke, A. Mason, J. Russell. ‘Bridging the Gap between Military and Civil Security in Satellite Applications’, 24th AIAA International Communications Satellite SystemsConference (ICSSC), San Diego, California, June 2006.

Annex 2Page 47Ref. Activity Title Procurement Policy Budget(KEUR)5D.017(09.153.19)Objective:Description:Planned TenderIssueSatellite Wireless Access point on launcher for monitoring of the passenger Open Competitive Tender Type: C2 500 Priority 2 18To define, design, manufacture and test a breadboard of a Satellite Wireless Access point on launchers for monitoring of the passenger satellite.Estimated Duration(months)Satellite designers would like to monitor a lot of parameters during the launch (temperature, vibrations, shocks) to make correlations with the predicted behaviour and the specifications. Thisis difficult because the launcher services for TM are limited, most units are off on the passenger satellites and currently any data link for monitoring purpose will require wires between thelauncher and the passenger satellite and a special connector. With a dedicated wireless TM access on the launcher itself, data can be transmitted from sensors implemented on the criticalpoints of the passenger satellite without the complication of wires to the launcher and special connectors.The distance between the launcher and the passenger satellite is at most a few meters implying RF and optical system can be used. Optical systems bring the benefit of no radio emission andshould be easily acceptable to the launcher authorities. The mass is important because units are implemented at the last stage of the launcher and on the satellite. The data rate varies from low(temperature) to high (shocks). The average data rate will be constrained by the TM allocation given by the launcher TTC sub-system. Compression techniques can be used but without loss ofinformation to ensure a generic design for any satellite and any parameter. Storage can be used to smooth the data rate up to the final separation. After separation the launcher TM facilities areno more available and communication to ground will be cut. On the satellite, there will be a centralized unit connected to a set of key monitoring points determined by the satellitemanufacturer on a case by case basis. This extra hardware shall be very light and have a very low power consumption. The existence of mixed analogue digital ASICs allows monitoring oftemperature, vibrations and shocks with a minimal impact on the passenger satellite budgets. The internal monitoring system can possibly also make use of wireless techniques or a lightweight wired bus.The experience acquired on optical wireless communications includes test flights (INTA Nanosat-1) and Photon (optical wireless implementing the CAN bus protocol) shows the technicalfeasibility of the concept from the communication side.The activity shall initially focus on the system definition considering the passenger satellite and the launcher. Following this a baseline design will be established, breadboarded and tested.NOTE: This activity has been designated as "Priority 2". Priority 2 activities will only be initiated on the explicit request of at least one delegation.

Annex 2Page 484. USER TERMINALSRef. Activity Title Procurement Policy Budget(KEUR)7-.006(06.153.38)Objective:Description:Planned TenderIssueSelf-pointing, Planar Antenna for Television Reception Open Competitive Tender Type: C1 1000 Priority 2 18The objective of this activity is to design, manufacture and test a prototype of a self-pointing planar antenna for Ku-band television reception employing phase steering technology.Estimated Duration(months)A planar phase steered antenna will have several advantages over a parabolic antenna such as: requires no mounting apparatus; can be directly screwed onto a wall; discrete appearance; nomanual pointing; multi satellite scanning ability w/o motor The antenna will in isolation be more expensive than a conventional solution. A market exists considering the following aspects:people not capable/willing to do a relatively complex installation of a parabolic dish requiring installers; people willing to pay extra to have a more discrete antenna; and in some areas it maybe the only possible solution due to local authorities/owner associations.To achieve a phased array antenna with size required for TV reception at acceptable cost, the constraints and opportunities of the operational environment must be fully exploited. Firstly, theantenna will be fixed. It will be located in Europe and will only cover the geostationary arc. Constraining latitude and longitude of the installation and the geostationary coverage to certain,acceptable range, and setting bounds on the wall properties where the antenna will be mounted (south and vertical within certain accuracy/range), a simplification in phase steering can beobtained which can be exploited for implementation and result in reasonable recurring costs. Balancing performance, complexity of implementation and ease of installation will be a majortrade off. Technology investigations are required such as considering utilisation of cheap, existing LNB components and novel phase steering concepts such as variable width/heightwaveguides.NOTE: This activity has been designated as "Priority 2". Priority 2 activities will only be initiated on the explicit request of at least one delegation.

Annex 2Page 49Ref. Activity Title Procurement Policy Budget(KEUR)7-.012(07.153.15)Objective:Description:Planned TenderIssueIntegrated User Terminal for Interactive applications Open Competitive Tender Type: C1 600 Priority 2 12Estimated Duration(months)The objective of this activity is to investigate and demonstrate the technical and economical feasibility of integrating the present IDU and ODU into one integrated unit having a wireless orpower-line interface to the indoor PC for reducing cabling issues.To make the satellite-based interactive services more appealing, the user terminal needs to evolve towards a plug-and-play concept. Some of the drawbacks of current broadcast andinteractive satellite user terminals include cabling issues, unfriendly deployment and limited capability of sharing the same access point among a small community of users. In this activitysome techniques and technologies to cope with these issues are addressed with a reduced impact on the overall terminal cost. Key aspects to be addressed within the design activity shallinclude: 1) integration of the DVB-S2/RCS (i.e. IDU) with WiFi, WiMax or powerline modems within the ODU with limited footprint, 2) more sophisticated ODU control signals (to controlfor example the tuner frequency band, etc). The integration of the DVB-S2/RCS/WiFi or WiMax modems within the ODU eases the terminal installation and allows the sharing of the sameaccess point among a small community of users. There are technical challenges to such an approach. IDU components will need to sustain ODU environmental condition. The antenna willneed to support the additional weight of the terminal, the housing must contend with higher heat dissipation and the EMC environment will be more demanding due to the close integration ofthe electronics. However, the new architecture does not need to adhere to the IFL (inter facility link) interface anymore which may lead to new electrical topologies where cost savings can bemade.The activity will be split in two phases. The first phase will be a study to prove the technical and economical feasibility of the approach as well as to define a standard wireless/powerlineinterface and new functionalities including the control commands for managing these new functionalities. This study shall also identify possible new longer term technology developmentsrequired to cost effectively realise the integrated unit. If such technology is identified, the second phase will be initiated to breadboard this technology to evidence the viability of theapproach. It is emphasised that if no new technology developments are required after phase 1, phase 2 will not be initiated.NOTE: This activity has been designated as "Priority 2". Priority 2 activities will only be initiated on the explicit request of at least one delegation.

Annex 2Page 50Ref. Activity Title Procurement Policy Budget(KEUR)7-.015(09.153.20)Objective:Description:Planned TenderIssueDistributed receive antenna for vehicles Open Competitive Tender Type: C1 500 Priority 2 18To design, manufacture and test a prototype of a receive antenna made of distributed radiators on the vehicle surface for user access to mobile services in L/S band.Estimated Duration(months)Mobile terminal antennas for data applications in the L- and S- frequency bands can be difficult to integrate aesthetically into vehicular designs due to their size and shape. The possibility todistribute radiators (sensors) can provide an extra degree of freedom to ease the integration process and to ensure that the car structure design is not compromised. Applying digital beamforming can offer exactly this. Moreover, distributed radiators combined by a digital beam forming network can provide an attractive solution for medium gain antennas (increasing theantenna aperture) to overcome the multipath and shadowing effects experienced in mobile environments, in particular rural and urban areas.In digital beamforming antennas, each radiator is equipped with a separate LNB, down-conversion, analogue-to-digital converter and some signal processing circuitry. The network combiningthe signal from the various sensors is implemented in digital domain. As such, signal loss over transmission lines is not an issue and the patches can be totally separated from each other(unlike in conventional array antennas). However, care must be taken in this case that grating lobes, and thus interference, do not present any problems for the receive system.This activity will design a medium gain receive antenna operating in either L- or S-band. The radiating elements of the array antenna will be distributed on the available surface and employdigital beam forming. A prototype will be manufactured and tested in a laboratory environment.In the ongoing ARTES 5 activity "Cost optimised high performance active receive phased array antenna for mobile terminals" the radiating elements are within one wavelength of each other,while the radiating elements will be far apart in this activity.NOTE: This activity has been designated as "Priority 2". Priority 2 activities will only be initiated on the explicit request of at least one delegation.

Annex 2Page 51Ref. Activity Title Procurement Policy Budget(KEUR)Planned TenderIssueEstimated Duration(months)7-.016(09.153.43)Objective:Description:COSPAS-SARSAT antennas Open Competitive Tender Type: C1 350 Priority 2 18To design, analyse and implement a breadboard of a body-worn antenna for the COSPAS/SARSAT satellite system.Within a couple of years wearable antennas may find their place in our every day living; they will emerge in various sports and emergency workers’ outfits, military, medical and spaceapplications. The selected application for this particular activity is the COSPAS-SARSAT system where emergency beacons (100 - 400MHz range) are becoming more and more miniaturisedand now reaching a stage where they can be integrated in clothing provided a viable antenna solution exists. COSPAS-SARSAT, initiated in 1982, is an international search-and-rescueprogramme providing service at sea, in the air and on land anywhere on the globe. The system comprises a satellite constellation, orbiting the Earth continuously with the task of listening forsignals emitted by distress beacons.This activity will investigate wearable antenna solutions suitable for the COSPAS-SARSAT system. The wearable antenna shall be body-worn, lightweight and conformal to the body. Thiscan facilitate the hands-free operation of man-satellite communications and satellite search-and-rescue by being integrated in for instance survival suits and inflatable life rafts. Antennabending as well as water exposure, can have dramatic effect on the antenna performance in terms of antenna mistuning on various parameters, such as, gain, impedance matching and crosspolarization. These issues will be dealt with within this activity.The activity will comprise:- preliminary design of a wearable antenna- preliminary tests on materials/processes to verify approach- breadboarding and testing of a wearable antennaThe currently running ARTES 5 activity on wearable antennas considers antennas for L-band integrated in textile. The use of 100MHz to 400 MHz frequencies implies a need for largerantennas than at L-band, thus other techniques are required to make the antennas wearable.NOTE: This activity has been designated as "Priority 2". Priority 2 activities will only be initiated on the explicit request of at least one delegation.

Annex 2Page 52Ref. Activity Title Procurement Policy Budget(KEUR)7-.017(09.153.21)Objective:Description:Planned TenderIssueAntenna radome for SATCOM user mobile terminals Open Competitive Tender Type: C1 400 3Q 2009 18Estimated Duration(months)To identify suitable radome materials for different mobile satellite ground user terminal antennas operating in Ku- or Ka-band. The activity includes the definition, build and testing of arepresentative radome prototype suitable for one type of ground terminal.Satellite communication antennas for ground applications require radomes to protect them from the outdoor environment. Ideally, these radomes are electrically RF transparent not to affectthe antenna radiating performance. In reality, the radomes do contribute to the antenna performance parameters, such as cross-polarisation, sidelobes, beamwidth and boresight pointing. Allthese performance parameters can vary significantly when the antenna beam is steered at low elevation. The challenge lies in limiting any performance degradation caused by the radome butstill fulfilling the other requirements imposed by the operational environment. The land mobile (automotive, train), maritime and aeronautical environment all present different requirements interms of possible shapes, structural strengths and allowable cost of the radome. The operational frequency and bandwidth also impose constraints on the material build-up. In Ku- and Kabandfor instance, water on the radome can significantly influence the RF performance and coatings to limit aggregation of water are of interest. Another issue that needs to be considered isheat dissipation through the radome. An antenna system typically contains a power amplifier that generates heat and which suffers from performance degradation if not allowed to dissipateheat adequately.Currently available radomes have shortcomimgs in one or more of the following aspects: ability to dissipate the heat generated by the transmitter inside the radome, ability to withstand theimpact of being hit by a bird when the vehicle moves at high speed such as a train at 300 km/hour, transparancy depends on the polarisation of the signal.The activity will investigate state-of-the-art materials, multilayer structures, metamaterials and RF techniques to minimize potential performance degradation while trying to reduce cost.Radome materials suitable for all types of user terminals, i.e. car, train, and airplane, will initially be considered through study and material sample realisation and measurement. A prototypemodel will be designed, manufactured and tested for one selected type of user terminal.In this activity, the contractor shall:- Expand and refine requirements for radomes.- Study and identify suitable material technology candidates for antenna radomes for Ku- and Ka-band and for the aeronautical, maritime and land mobile environment.- RF test these candidates at sample level.- Propose best candidates.- Design, manufacture and RF test a prototype radome for a selected environment (e.g. Ku-band maritime).

Annex 2Page 53Ref. Activity Title Procurement Policy Budget(KEUR)7-.018(09.153.21)Objective:Description:Planned TenderIssueCost Effective Satellite Terminals for MESH Overlay Networking Open Competitive Tender Type: C1 1500 3Q 2009 24To design, manufacture and test satellite terminal prototypes capable of star and mesh connectivity over transparent satellite links.Estimated Duration(months)The need for peer-to-peer connectivity of remote satellite terminals is a reality in today’s satellite communications market. In particular, delay sensitive applications such as voicecommunications, collaborative conferencing (audio/video and data), and cellular backhauling are strong cases for adopting a mesh network topology. The use of a single satellite hop toconnect remote terminals also reduces the required transmission bandwidth and lead to savings in operational costs of the satellite networks. Despite these advantages, the market for meshnetworks has not grown in the same proportion as the rest of the SATCOM market. This is mainly attributed to the high cost of mesh satellite terminals and also the lack of cost effectivescalability and flexibility of the current hardware solutions. Furthermore, the combination of link budget constrains and conventional air interface schemes impose additional capital costs dueto a larger antennal size and more powerful RF amplifiersThis activity aims at architectural design and development of cost effective mesh capable satellite terminals, starting with a system study to establish requirements and to investigate potentialtechniques, technologies and architectures to reduce the capital and operational costs of mesh overlay networks. System aspects to be investigated include:- Low-cost/efficient multi-carrier demodulator design;- A thorough trade-off analysis to select efficient solutions for low signalling overhead in a hybrid MESH and star network topology;- The design of network synchronization under different network scenario such as multi-beam or multi-transponder configuration;- Rain mitigation techniques for mesh connection, techniques such as adaptive coding and modulation, as well as data rate adaptation;- Innovative access schemes OFDMA-based, on top of MF-TDMA, for a higher spectral efficiency;- Multi-carrier receiver and/or transmitter capabilities;- Random access scheme on top of DAMA for traffic and signalling;- Applications to mobile application scenarios with consequences to the robustness to the air interface (resilience to Doppler, shadowing events, …);- Efficient framing and L2 encapsulation scheme (e.g constant burst length plus GSE) which also need a flexible turbo code solution (like the turbo codes under consideration forDVB-RCS evolution)This activity shall address these enhancements to the conventional air interface as well as an innovative terminal architecture to improve the overall system efficiency and cost, whilemaintaining a reasonable complexity of the mesh terminal. The functionality and performance of the proposed terminal design shall then be demonstrated using prototypes.The planned activity will be divided into two phases starting with a first phase of system analysis, and trade-offs followed by architectural and detailed design of the terminal prototype. Thedesign of the terminal shall take into account the requirements of small mesh network and the flexibility to scale up to larger networks with hybrid star and mesh connectivity. The results ofthe system analysis and recommended changes to the air interface will be provided to pertinent standardization working groups such as the DVB-RCS Evolution.In the second phase, the implementation of selected techniques shall be carried out as prototypes to demonstrate functional and performance capabilities of the mesh terminals based onlaboratory testing.