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Verhaert Innovation Day 2012 –  Jef Van Hove (VERHAERT) - Proba-V satellite structure design & verification structure
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Verhaert Innovation Day 2012 – Jef Van Hove (VERHAERT) - Proba-V satellite structure design & verification structure

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External speaker of Qinetiq at the 9th edition of our Innovation Day on October 26th 2012

External speaker of Qinetiq at the 9th edition of our Innovation Day on October 26th 2012


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  • 1. CONFIDENTIAL PROBA-V satellite structure Jef Van Hove VERHAERT Jef.vanhove@verhaert.comOctober 26th 2012 © Copyright QinetiQ Limited 2010 Slide 1
  • 2. Contents• Introduction to PROBA(-V)• Structural Design Process• Structural verification by test• Integration © Copyright QinetiQ Limited 2010 2
  • 3. PROBA: PRoject for On-Board AutonomyLargely Autonomous during Nominal mission• Navigation (AOCS)• Intern Power en Data Management• Data down-link• User segment access to date via FTPTechnology demonstrationPROBA1: Earth ObservationPROBA2: Sun Observation © Copyright QinetiQ Limited 2010 3
  • 4. PROBA diagram © Copyright QinetiQ Limited 2010 4
  • 5. PROBA-V(egetation) mission• PROBA-V is a “gap-filler” mission for SPOT • Target: Map the Earth’s vegetation every 2 days• Orbit is driven by performance • Global coverage • Minimum Swath width 2250km • LTDN 10:30 - 11:30 Altitude 820 km ± 10 km Eccentricity 0 Inclination : Sun-Synchronic Orbit © Copyright QinetiQ Limited 2010 5
  • 6. Spacecraft System Engineer following ESA ECSS Pre-Phase A: Concept Studies Phase D(4): SAITL Domain of Systems Engineering Mission-Level Objectives + System Demonstration multiple R/A/C concepts + and Validation Mission Validation Plan Phase A: Concept Development Phase D(3): SAITL Single System-level R/A/C Integrate Subsystems and + Trade Studies + System Verify System Performance Verification Plan Phase B: Preliminary Design Phase D(2): SAITL Subsystem-level R/A/C Integrate Components and + Interfacing + complete technology Verify Subsystem Performance + Subsystems Verification Plan Phase C(1): Final Design and Fabrication Phase D(1): SAITL Domain of Engineering Final Detailed Design Verify Component Performance Phase C(2): Final Design and Fabrication Fabric hardware and software Design © Copyright QinetiQ Limited 2010 6
  • 7. System engineering function 1. Input: Mission Other SE Functions: Objectives (Starts Pre- 6. Interfaces Phase A) 5.Validate and Verify 7. Mission Environment 8. Resource Budgets 2. Derived 9. Risk Management 3. Architecture Requirements /Design 10. Configuration Management 11. Reviews 5.Validate and Verify 5.Validate and Verify 4. Concept of Operations Output: Proceed to next Phase, ending at Operations (Phase E) © Copyright QinetiQ Limited 2010 7
  • 8. Mission driven structural requirements PROBA-VDesign• Maximum re-use of PROBA-2• Accommodation of: − Vegetation Instrument − Minimum 2 technology demonstration experiments• Sufficient solar cells for positive power budget• Primary launcher VEGA + three back-ups (volume, mass en CoG)Mechancal/Thermal• Survive the complete mission life-cycle• Primary launcher VEGA + three back-ups (mechanical loads)• Levensduur van 2.5 jaar in-orbit• Redundant or safe-life © Copyright QinetiQ Limited 2010 8
  • 9. Launcher Input © Copyright QinetiQ Limited 2010 9
  • 10. Structure sub-system interfaces © Copyright QinetiQ Limited 2010 10
  • 11. Preliminary Design © Copyright QinetiQ Limited 2010 11
  • 12. Structural Analysis © Copyright QinetiQ Limited 2010 12
  • 13. Structural Analysis © Copyright QinetiQ Limited 2010 13
  • 14. Thermal Analysis © Copyright QinetiQ Limited 2010 14
  • 15. Thermal Analysis © Copyright QinetiQ Limited 2010 15
  • 16. PROBA-V Detailed Design © Copyright QinetiQ Limited 2010 16
  • 17. Verification by Test © Copyright QinetiQ Limited 2010 17
  • 18. Thermal Test Model - integration © Copyright QinetiQ Limited 2010 18
  • 19. Thermal Test © Copyright QinetiQ Limited 2010 19
  • 20. Ombouwen to Structural Test Model © Copyright QinetiQ Limited 2010 20
  • 21. Vibration Test © Copyright QinetiQ Limited 2010 21
  • 22. Vibration Test• Spacecraft structure qualification• Determine test spectra for equipment © Copyright QinetiQ Limited 2010 22
  • 23. Acoustic Test © Copyright QinetiQ Limited 2010 23
  • 24. Shock Test © Copyright QinetiQ Limited 2010 24
  • 25. Flight Model Integration – Solar Array © Copyright QinetiQ Limited 2010 25
  • 26. Flight Model Integration – Equipment Fit-check © Copyright QinetiQ Limited 2010 26
  • 27. Flight Model Integration - Harness © Copyright QinetiQ Limited 2010 27
  • 28. Flight Model Integration - Harness © Copyright QinetiQ Limited 2010 28
  • 29. Flight Model Integration © Copyright QinetiQ Limited 2010 29
  • 30. VERHAERT MASTERS IN INNOVATION® Headquarters Hogenakkerhoekstraat 21 9150 Kruibeke (B) tel +32 (0)3 250 19 00 fax +32 (0)3 254 10 08 ezine@verhaert.com QinetiQ Space nv More at www.verhaert.com www.QinetiQ.be VERHAERT MASTERS IN INNOVATION® Netherlands European Space Innovation Centre Kapteynstraat 1 VERHAERT MASTERS IN INNOVATION® helps companies and governments to innovate. 2201 BB Noordwijk (NL) We design products and systems for organizations looking for new ways to provide value Tel: +31 (0)633 666 828 for their customers. willard.vanderheijden@verhaert.com We are a leading integrated product innovation center; creating technology platforms, More at www.verhaert.com developing new products and business in parallel, hence facilitating new-growth strategies for our clients. © Copyright QinetiQ Limited 2010 Slide 30October 26th 2012 30