VV02 mission - Asi

VEGA : VVO2 Mission 

VEGA-IPT Team 

VV02 Workshop 

10/07/2013 

ESA UNCLASSIFIED – For Official Use

VV02 mission 

1. VEGA background 

2. VEGA Launch System 

a. Ground Segment 

b. Launch Vehicle 

c. VEGA Qualification flight :VV01 mission 

3. VV02 Mission 

4. After VV02 

a. Objectives 

b. Mission description 

c. Evolution of the LV configuration from VV01 

d. VV02 achievements 

VV02 VERTA-1 - Mission: PROBA-V / VNREDSat-1 / ESTCUBE1 10/07/2013 | Slide 2 


VEGA main features 

Vega programs 

• Italy, France, Belgium, Spain, The Netherlands, Switzerland and Sweden participating States to 

the development and exploitation. Germany recently joined the Vega evolution programme 

• Vega Development, P80 and VERTA 

• New programs approved at C/MIN 2012: VECEP and LEAP 

Technologies for VEGA 

• Wide reutilization of existing and proven technologies 

• New key technologies for solid boosters and Thrust Vector Control 

Management of VEGA 

• Development program under ESA management and execution responsibilities, with the support 

of the National Agencies (ASI,CNES) 

• Exploitation phase managed by Arianespace 

Industrial organisation 

• New prime contractors for the launch vehicle (ELV Spa) and the Ground Segment (Vitrociset) in 

Italy with system and management capabilities 

• More than 40 major aerospace companies from 12 countries 

• Use of Ariane industrial background and facilities 

Industrial investment 

• Launcher qualification flight 

• P80 development: Avio investment 



1. Industrial organisation: 

The ramp up phase 

ESA UNCLASSIFIED – For Official Use 

Development lessons learnt 

Build new competences and keep them 

2. Cost and planning: 

Development cost 

Planning 

3. Technical risks 

1. New development 

2. Off the shelf 

4. How to prepare a balanced exploitation 

1. Learning 

2. Recurring cost

2000 

VEGA Development Chronology 

2006: Zefiro 23 test 1 


2003: Development 

Contracts Signature 

2006: P-80 test 1 

2002 


ESA UNCLASSIFIED Program Approval 

– For Official Use 

Start Ground 

Segment work 

at Kourou 

2004 

Launch System 

Preliminary 

Design Review 


Ground Segment 

Design Review 

2006 

2006: Fairing tests 

2011: Combined tests 

Combined tests in Kourou 

2008 

Launch System 

Critical Definition 

Review 

2007: P-80 test 2 

1 st Flight 

2010 

2012 

Launch System 

Qualification Review 


2008: Zefiro 9A test 1 



2010: AVUM tests 

2 nd Flight 

2013


Development lessons learnt 

1. Some of the development main issues: 

1. Zefiro nozzle 

2. Tanks 

3. Flight Software 

4. Separation ½ 

5. Roll attitude Control System 

6. Ground segment 

3. Test as fly, fly as you test 

Subsystem tests 

Systems test.

VEGA Ground Segment 

VEGA Mobile 

Gantry 

VEGA Pad 



VEGA Mast 

Exhausting 

Gases Ducts

Overall Length: ~ 30 m 

Mass at lift-off: ~ 139 ton 



Launch Vehicle 

PLA & VESPA 

PLA & VESPA



The fourth stage: AVUM 

Helium pressurised tanks (GHe): 

88 litres @ 310 bar 

Propellant tanks (NPO L - Russia) 

UDMH: 2 x 142 litres 

NTO: 2 x 142 litres 

Max pressure: 36 bars 

RACS: 2 x 3 thrusters (Aerojet) 

Thrust: 240 N (each) 

N2H4 tank: 39 kg @ 26 bar 

Liquid Propulsion 

module 

(LPS + RACS) 

Main engine: RD-869 (YUZHNOYE - Ukraine) 

Thrust: 2450 N 

Specific impulse: 315.5 s 

Restartable: 5 times 

Gimbal displacement: +/- 10° 

Avionics module



Avionics 

AVUM and Avionic module lay out 

Avionics functions are distributed among Hardware items and 

On-Board Software. They are split into the following three 

subsystems: 

• The GNC - Guidance, Navigation and Control Subsystem 

• The SAS - Safeguard Subsystem 

• The TMS - Telemetry subsystem 

Avionic module (IRS handling)

Payload Composite 



VV01 – 

Single PL 

VV02 – 

Multi PL

VEGA VV01 mission 

VEGA maiden flight was successfully performed on 

February 13 th 2013 

The flight has successfully orbited: 

• LARES Spacecraft (ASI) for 

• 

Relativistic studies 

One microsatellite ALMASpace 1 

and 

• 7 CUBESat in 3 pod as additional 

secondary passengers. 



VV02 mission 



PROBA V VnRedSat- 

1 

Customer ESA Vietnam 

Academy of 

Science and 

Technology 

Mass [Kg] 140 118 1.33 

Dimensions 

[mm] 

765 x 730 x 

840 

Orbit SSO 

(98.73 deg) 

Altitude 

[Km] 

1318 x 

936.57 x 

1185 

SSO 

(98.13 deg) 

826 671 671 

EstCube-1 

Tartu 

University, 

Estonia 

100 x 100 x 

100 

SSO 

(98.13 deg)

VV02 objectives 

1. Demonstrate the multi PL capability, 

2. Long mission duration 

3. Versatility with change of orbits 

4. Complement the VV01 demonstration, covering lack of 

information due to perturbation of the telemetry link, and 

additional information from different mission and configuration. 

5. Demonstrate the PL orbit injection accuracy, and PL comfort. 

6. Qualify in flight FPSA, Vespa, SSIS, 

7. Autonomous on board Localization and Telemetry System based 

on GNSS (passenger demonstration on VV02) 

8. AVUM direct reentry 



VVo2 Mission 1/2 



VVo2 Mission 2/2 



Flight Program Software - FPSA 

• A completely new Flight Program Software and Production facility was 

developed and qualified for VV02 mission, by Italian consortium with the 

involvement of Belgium and Spanish companies 

• Main FPS-A functions are: 

• Flight Management 

• GNC algorithm execution 

• Failure Detection, Isolation and Recovery management 

• Telemetry Generation 

• On-Board computer management 

• The FPS-A product main figures are: 

• Around 17.000 declarative statements 

• Around 80.000 lines (from which 48.000 are code lines) 

• Around 134 files (45 compilation units) 

• Derived from a Requirement Baseline (RB) with roughly 385 requirements 

• Validated against its Technical Specification (around 400 Tests) 

• Qualified against its RB with roughly 50 Tests 



FPSA Independent Software Verification 

and Validation (ISVV) 

• ISVV Activity has been lead by ESA / ESTEC with the support from SENER. 

• Main objectives are: 

• Verification of the Software robustness 

• Identification of hidden faults and vulnerabilities 

• ISVV main tasks have been: 

• FPS-A Independent verification 

• Independent analysis of the FPSA 

Specifications, Design and 

Justification documents 

• Independent analysis of 

the Source Code 

• Identification of critical areas 

• Definition, execution and 

assessment of selected Validation tests 

• Definition, execution and 

assessment of stress tests 

on critical areas 




Qualify in flight Vespa 

Vespa is the optional structure specifically 

developed for making Vega capable of Multiple 

Payload mission. 

Its functions are interface, protect, carry and 

separate one Main Payload + one or more 

Secondary Payload 



Vespa upper part 

Main PL 

Vespa lower part Secondary 

PL


Qualify in flight SSIS 



Lightband Mark II 

Separation system 

Conical Shape Adapter Allowing to integrate on 

VUP small PL separation system


Autonomous on board Localization 

One of the important Passengers of the 

VV02 is the ALTS complementary TLM, 

derived from the LARES one, in charge to: 

• monitor the various phase of flight 

(stages, fairing and Spacecraft 

separations) through 4 different 

videocameras, 

• Acquire the environment levels at VESPA 

interfaces (FAU), 

• To prepare future means to complement 

on ground safety in identifying LV 

behaviour in the “champ proche”, and 

localization in the “far field”. 

• to make available an independent means 

for determine Spacecraft separation 

conditions. 




AVUM direct reentry 

First flight has been performed with 25 

years Re-entry strategy, while the 

VV02 has been asked to be fully 

compliant with direct deorbiting. 

The direct deorbiting poses some 

additional constraint to the mission 

requiring a large oceanic area to the 

footprint, precision in the orbit change 

in order to avoid risk of falling on 

inhabited land or on commercial routes. 

All the required pre flight verification 

activities has been carried out and the 

full process is set up and demonstrated 

in flight through VV02 results 



4 th stage IP and Footprint

VV02 achievements : timeline 

Event VV02 time FMA time VV02 altitude FMA altitude ∆ 

AV5 c/o 8620,276 8623,080 674,976 672,880 2,096 



[s] [s] [km] [km] [km] 

1st stage sep 116,055 115,702 66,040 65,727 0,313 

Z23 ign 116,895 116,532 66,952 66,515 0,436 

2nd stage sep 220,797 219,365 180,517 179,136 1,381 

Z9 ign 236,388 234,939 194,521 193,239 1,282 

HS sep 241,425 240,000 198,687 197,477 1,210 

3rd stage sep 383,546 378,085 263,128 262,460 0,668 

AV1 ign 390,782 385,085 264,025 263,507 0,518 

AV1 c/o 669,865 668,033 288,973 291,683 -2,710 

AV2 ign 3183,455 3182,950 821,267 821,687 -0,420 

AV2 c/o 3273,604 3276,190 824,222 824,303 -0,082 

AV3 ign 3852,079 3851,580 837,318 836,958 0,360 

AV3 c/o 3872,907 3873,540 837,842 837,466 0,376 

AV4 ign 6822,967 6822,660 680,744 679,008 1,736 

AV4 c/o 6886,331 6888,050 681,182 679,663 1,519 

AV5 ign 8524,610 8523,800 669,712 667,689 2,023

VV02 achievements : PL injection accuracy 

Paramete 

rs 

Semimajor 

axis (km) 

Eccentrici 

ty 

Inclinatio 

n (deg) 

VNREDsat 

VNREDSat- 

1 Req 

Prediction 

(before 

separatio 

n) 

PROBA V 



Inertial 

Reference 

System 

Parameters 

Semi-major axis 

(km) 

Proba-V 

Req 

Prediction 

(before 

release) 

Inertial 

Reference 

System 

External 

Means* 

VV02 Pl 

Injection 

Accuracy 

VV02 PL 

Accuracy 

Requireme 

nt (3σ) 

7198.000 7197.442 7197.882 7198.279 -0.279 ±30 

Eccentricity 0.00115 0.00116 0.00124 0.001126 -0.000024 0.005 

Inclination (deg) 98.73 98.730 98.731 98.687 - 0.043 ±0.15 

External 

Means* 

VV02 Pl 

Injection 

Accuracy 


Accuracy 

Requiremen 

t (3σ) 

7046.90 7042.24 7042.24 7041.32 -5.582 ±30 

0.00121 0.00096 0.00106 0.00077 

- 

0.000043 

* Figures based on back propagation at PL separation time of TLE NORAD (10-05-2013) data by STK-9 tool 

0.005 

98.134 98.141 98.140 98.101 - 0.033 ±0.15 

Parameters 

Semi-major 

axis (km) 

Prediction 

based on LV 

data 

Inertial 

Reference 

System 

7042.237 7035.637 

Eccentricity 0.000965 0.00135 

Inclination 

(deg) 

ESTCube 

External 

Means* 

7031.76 

5 

0.00161 

8 


Accuracy 

Requirement 

(3σ) 

±30 

0.005 

98.142 98.139 98.099 ±0.15

After VV02 

1. VEGA has performed successfully its qualification flight (VV01) and its 

first demonstration flight (VERTA1/ VV02, 7 th May 2013) 

2. We shall therefore capitalize on those assets in order to ensure a 

successful exploitation of VEGA with a reliable and affordable VEGA 

launch service. 

3. Next steps are : 

a. Completion of the generic qualification for the other missions 

types 

b. Completion of the VERTA demonstration flights 

c. Maintaining the Launch System Qualification status and 

improvements of the Launch Service through the LEAP (launchers 

Exploitation Accompaniment Programme) 

d. Preparation of the VEGA evolutions through the VECEP 

Programme for an increase of performance and cost reduction

VV02 mission - Asi

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