CONFIDENTIAL

PROBA-V satellite structure

Jef Van Hove
VERHAERT
Jef.vanhove@verhaert.com

October 26th 2012

© Copyright ...
Contents

• Introduction to PROBA(-V)
• Structural Design Process
• Structural verification by test
• Integration

© Copyr...
PROBA: PRoject for On-Board Autonomy

Largely Autonomous during Nominal mission
• Navigation (AOCS)
• Intern Power en Data...
PROBA diagram

© Copyright QinetiQ Limited 2010

4
PROBA-V(egetation) mission

•

PROBA-V is a “gap-filler” mission for SPOT
•

•

Target: Map the Earth’s vegetation every 2...
Pre-Phase A: Concept Studies
Mission-Level Objectives +
multiple R/A/C concepts +
Mission Validation Plan

Domain of Engin...
System engineering function

1. Input: Mission
Objectives (Starts Pre5.Validate and Verify
Phase A)
2. Derived
Requirement...
Mission driven structural requirements PROBA-V
Design
• Maximum re-use of PROBA-2
• Accommodation of:
− Vegetation Instrum...
Launcher Input

© Copyright QinetiQ Limited 2010

9
Structure sub-system interfaces

© Copyright QinetiQ Limited 2010

10
Preliminary Design

© Copyright QinetiQ Limited 2010

11
Structural Analysis

© Copyright QinetiQ Limited 2010

12
Structural Analysis

© Copyright QinetiQ Limited 2010

13
Thermal Analysis

© Copyright QinetiQ Limited 2010

14
Thermal Analysis

© Copyright QinetiQ Limited 2010

15
PROBA-V Detailed Design

© Copyright QinetiQ Limited 2010

16
Verification by Test

© Copyright QinetiQ Limited 2010

17
Thermal Test Model - integration

© Copyright QinetiQ Limited 2010

18
Thermal Test

© Copyright QinetiQ Limited 2010

19
Ombouwen to Structural Test Model

© Copyright QinetiQ Limited 2010

20
Vibration Test

© Copyright QinetiQ Limited 2010

21
Vibration Test

• Spacecraft structure qualification
• Determine test spectra for equipment

© Copyright QinetiQ Limited 2...
Acoustic Test

© Copyright QinetiQ Limited 2010

23
Shock Test

© Copyright QinetiQ Limited 2010

24
Flight Model Integration – Solar Array

© Copyright QinetiQ Limited 2010

25
Flight Model Integration – Equipment Fit-check

© Copyright QinetiQ Limited 2010

26
Flight Model Integration - Harness

© Copyright QinetiQ Limited 2010

27
Flight Model Integration - Harness

© Copyright QinetiQ Limited 2010

28
Flight Model Integration

© Copyright QinetiQ Limited 2010

29
VERHAERT MASTERS IN INNOVATION®
Headquarters
Hogenakkerhoekstraat 21
9150 Kruibeke (B)
tel +32 (0)3 250 19 00
fax +32 (0)3...
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Innovation day 2012 3. jef van hove - verhaert - 'proba-v satellite structure design & verification structure'

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Innovation day 2012 3. jef van hove - verhaert - 'proba-v satellite structure design & verification structure'

  1. 1. CONFIDENTIAL PROBA-V satellite structure Jef Van Hove VERHAERT Jef.vanhove@verhaert.com October 26th 2012 © Copyright QinetiQ Limited 2010 Slide 1
  2. 2. Contents • Introduction to PROBA(-V) • Structural Design Process • Structural verification by test • Integration © Copyright QinetiQ Limited 2010 2
  3. 3. PROBA: PRoject for On-Board Autonomy Largely Autonomous during Nominal mission • Navigation (AOCS) • Intern Power en Data Management • Data down-link • User segment access to date via FTP Technology demonstration PROBA1: Earth Observation PROBA2: Sun Observation © Copyright QinetiQ Limited 2010 3
  4. 4. PROBA diagram © Copyright QinetiQ Limited 2010 4
  5. 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. 6. Pre-Phase A: Concept Studies Mission-Level Objectives + multiple R/A/C concepts + Mission Validation Plan Domain of Engineering Design Domain of Systems Engineering Spacecraft System Engineer following ESA ECSS Phase D(4): SAITL System Demonstration and Validation Phase A: Concept Development Single System-level R/A/C + Trade Studies + System Verification Plan Phase D(3): SAITL Integrate Subsystems and Verify System Performance Phase B: Preliminary Design Subsystem-level R/A/C + Interfacing + complete technology + Subsystems Verification Plan Phase D(2): SAITL Integrate Components and Verify Subsystem Performance Phase C(1): Final Design and Fabrication Final Detailed Design Phase D(1): SAITL Verify Component Performance Phase C(2): Final Design and Fabrication Fabric hardware and software © Copyright QinetiQ Limited 2010 6
  7. 7. System engineering function 1. Input: Mission Objectives (Starts Pre5.Validate and Verify Phase A) 2. Derived Requirements 3. Architecture /Design 5.Validate and Verify Other SE Functions: 6. Interfaces 7. Mission Environment 8. Resource Budgets 9. Risk Management 10. Configuration Management 11. Reviews 5.Validate and Verify 4. Concept of Operations Output: Proceed to next Phase, ending at Operations (Phase E) © Copyright QinetiQ Limited 2010 7
  8. 8. Mission driven structural requirements PROBA-V Design • 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. 9. Launcher Input © Copyright QinetiQ Limited 2010 9
  10. 10. Structure sub-system interfaces © Copyright QinetiQ Limited 2010 10
  11. 11. Preliminary Design © Copyright QinetiQ Limited 2010 11
  12. 12. Structural Analysis © Copyright QinetiQ Limited 2010 12
  13. 13. Structural Analysis © Copyright QinetiQ Limited 2010 13
  14. 14. Thermal Analysis © Copyright QinetiQ Limited 2010 14
  15. 15. Thermal Analysis © Copyright QinetiQ Limited 2010 15
  16. 16. PROBA-V Detailed Design © Copyright QinetiQ Limited 2010 16
  17. 17. Verification by Test © Copyright QinetiQ Limited 2010 17
  18. 18. Thermal Test Model - integration © Copyright QinetiQ Limited 2010 18
  19. 19. Thermal Test © Copyright QinetiQ Limited 2010 19
  20. 20. Ombouwen to Structural Test Model © Copyright QinetiQ Limited 2010 20
  21. 21. Vibration Test © Copyright QinetiQ Limited 2010 21
  22. 22. Vibration Test • Spacecraft structure qualification • Determine test spectra for equipment © Copyright QinetiQ Limited 2010 22
  23. 23. Acoustic Test © Copyright QinetiQ Limited 2010 23
  24. 24. Shock Test © Copyright QinetiQ Limited 2010 24
  25. 25. Flight Model Integration – Solar Array © Copyright QinetiQ Limited 2010 25
  26. 26. Flight Model Integration – Equipment Fit-check © Copyright QinetiQ Limited 2010 26
  27. 27. Flight Model Integration - Harness © Copyright QinetiQ Limited 2010 27
  28. 28. Flight Model Integration - Harness © Copyright QinetiQ Limited 2010 28
  29. 29. Flight Model Integration © Copyright QinetiQ Limited 2010 29
  30. 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® VERHAERT MASTERS IN INNOVATION® helps companies and governments to innovate. We design products and systems for organizations looking for new ways to provide value for their customers. We are a leading integrated product innovation center; creating technology platforms, developing new products and business in parallel, hence facilitating new-growth strategies for our clients. October 26th 2012 © Copyright QinetiQ Limited 2010 Slide 30 Netherlands European Space Innovation Centre Kapteynstraat 1 2201 BB Noordwijk (NL) Tel: +31 (0)633 666 828 willard.vanderheijden@verhaert.com More at www.verhaert.com 30

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