document title / titre du document TRP W ORK PLAN ... - emits - ESA

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TRP Work Plan 2005-2007 Description of Activities TEC-SB/7935/dc 12/Feb/09 TRP Reference: T601-50MC Advancement in Thermo-Elastic Distortion Verification Methods for spacecraft Title: structures The objectives of the proposed activity are the following: - Improvement of materials modeling, especially composites and other advanced materials. - Improvement of numerical simulation of materials, components and assemblies of structures by using existing FEM software tools, but including in the mathematical models the specific aspects of materials and components. This shall consider non-linear and stochastic analysis. - Application of new measurement and monitoring techniques, such as ESPI (Speckle interferometry), laser radar and optical fibre sensing (Bragg grating), thermography... The activity will consist of two phases: Phase 1 - short review of current state of the art with regard to analysis, control and test methods; - Modeling of composite materials, components, joints and assemblies. Typical hypothesis, such as the linearity of thermal expansion, shall be investigated, as well as the effects of anisotropy and large temperature ranges; - Measurement of material properties on coupons, including expansion coefficients, stiffness, thermal conductivity and all relevant parameters identified previously; - Verification of simulation tools and methods on coupons and joints; - Establishment of measurement uncertainty requirements and stochastic character of simulation tools; - Establish guidelines for predicting thermo-elastic distortions. In addition to methodologies for improved modeling, these guidelines shall also consider making recommendations on the need to perform material and component level tests; Phase 2 - Definition of a breadboard representative of the complexity of a scientific instrument. - Modeling and prediction. - Stochastic (and non-linear) analysis - Definition of test set-up and selection of measurement technique - Correlation Where necessary, updating of guidelines established in Phase-1, and extension of guidelines to include recommendations on performance of system level test verification methods. Deliverables: Design and verification guidelines; test coupons and breadboard; modeling procedures. Current TRL: TRL2 Target TRL: TRL3-4 Application Need/Date: TRL5 by 2010-2012 Application/Mission: Engineering tools applicable to all S/C Contract Duration: 24 months SW Clause : - Dossier0 Ref.: T-543 Consistency with Harmonisation Roadmap and Conclusions: Not directly linked to harmonised technology. TRP Reference: T605-11MC Title: Non-Contact Measurements of Membranes Inflatable Space Structures very often include a stretched membrane. Static and dynamic measurements of such membranes during testing remain a challenge due to detrimental added mass and stiffness of the classical instrumentation. The objective is to develop a non-contact method for measuring static and dynamic shapes of membrane spacecraft structures. This implies the review and evaluation of available methods; the selection and development of an innovative method; the demonstration on a breadboard model. Deliverables: Documentation and breadboard. Current TRL: TRL1 Target TRL: TRL3 Application Need/Date: TRL5 by 2010 Application/Mission: thin membrane structures, including inflatable structures (e.g. schields, booms, solar sail); EO/Sci missions. Contract Duration: 12 months SW Clause : - Dossier0 Ref.: T-7896 Consistency with Harmonisation Roadmap and Conclusions: Page 205 of 227
TRP Work Plan 2005-2007 Description of Activities TEC-SB/7935/dc 12/Feb/09 TRP Reference: T605-12MC Improvement of force limited vibration testing methods for equipment/instrument unit Title: mechanical verification The mechanical vibration testing approaches (sine and random) currently applied to satellite equipment / instrument units are in general very conservative and might result to severe over-testing of the units compared to real flight environments. The reasons for this are the different interface conditions applicable to the system and the test configuration (when the unit is hard-mounted to the shaker table). Consequently these test approaches lead also to over-design of the units and therefore significant mass penalties. Force limited vibration testing has been intensively investigated in NASA since many years. The methods aim at establishing interface force estimates for the case when the unit is mounted on a flexible satellite support structure rather than the shaker and to limit the test input for the unit test to these force estimates. The experiences in force limited vibration testing are still very limited in Europe. Further investigations of this subject should increase the relevant knowledge base and should contribute to the establishment of an ESA mechanical testing handbook covering the specific aspects of force limited vibration testing. The objectives are to investigate the influence of the support structure mechanical impedance on the random vibration environment and the execution of unit random vibration test on electro-dynamic shakers; to identify relevant methods to more accurately derive the interface force limits (e.g. direct measurement at system level, semi-empirical, analytical) and to assess their respective accuracy; to develop simplified but nevertheless adequate models for the simulation of coupled system conditions; to verify the developed approaches by analytical and experimental means (representative of existing equipment structures) and to establish the relevant input for the ESA Mechanical Testing Handbook. Deliverables: Technical notes (incl. identification of methods to more accurately derive the interface force limits, models for the simulation of coupled system conditions, verification of the developed approaches by analytical and experimental means). Current TRL: Target TRL: Application Need/Date: TRL5 (operational method) TRL2 TRL3 by 2008 Application/Mission: Engineering toolsapplicable to all S/C Contract Duration: 18 months SW Clause : - Dossier0 Ref.: T-562 Consistency with Harmonisation Roadmap and Conclusions: TRP Reference: Title: T605-20MC Advancement of Mechanical Verification Methods for non-linear spacecraft structures For the purpose of spacecraft structure design development and verification by analysis the structures are in general a-priori assumed to behave linear. Analytical predictions include static & dynamic analyses at satellite level but also launcher/satellite coupled dynamic loads analyses (CLA) to predict flight loads for specific satellite configurations. However, experience has shown that spacecraft structures can exhibit highly non-linear behaviour (e.g. due to backlash, joint gapping, rattling) and the consequences of their dynamic effects can significantly affect the design verification procedures, in particular: to properly evaluate flights loads with linearised models used in the CLA; the general performance of dynamic verification tests; to demonstrate adequate coverage of non-linear dynamic effects in satellite verification tests. As a result, the presence of such effects in spacecraft structures increases significantly the complexity of the mechanical verification process (analysis and testing).The main objectives of this activity are: to review satellite design and verification test documentation in order to identify relevant structure verification problems related to non-linear dynamic effects; to develop strategies for handling non-linear dynamic effects within linear CLA models and to adequately convert the related CLA predictions into dynamic verification test specifications; to analytically investigate the impact of spacecraft structure non-linearities on the verification test performance (including non-linear dynamic effects resulting from e.g. shaker); to verify the proposed approaches with a bread-board model (using available space hardware as far as possible); and to finally establish guidelines and recommendations for the identification of potential structural non-linearities, the assessment of their effects and how to treat them during the spacecraft structure design and development and the verification test phase. Deliverables: Documentation and breadboard. Current TRL: TRL2 Target TRL: TRL3-4 Application Need/Date: TRL5 by 2010 Application/Mission: Engineering tools applicable to all S/C Contract Duration: 20 months SW Clause : - Dossier0 Ref.: T-543 Consistency with Harmonisation Roadmap and Conclusions: Not directly linked to harmonised technology. Page 206 of 227
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