1. © Copyright QinetiQ Limited 2010
DESIGN & VERIFICATION
PROBA-V SATELLITE STRUCTURE
CONFIDENTIAL
Jef Van Hove
Consultant
Jef.vanhove@verhaert.com

2. © Copyright QinetiQ Limited 2010
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• Introduction to PROBA(-V)
• Structural Design Process
• Structural verification by test
• Integration
Contents

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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
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PROBA diagram
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PROBA-V(egetation) mission
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• 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

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Spacecraft System Engineer following ESA ECSS
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Phase D(3): SAITL
Integrate Subsystems and
Verify System Performance
Phase D(2): SAITL
Integrate Components and
Verify Subsystem Performance
Pre-Phase A: Concept Studies
Mission-Level Objectives +
multiple R/A/C concepts +
Mission Validation Plan
Phase A: Concept Development
Single System-level R/A/C
+ Trade Studies + System
Verification Plan
Phase B: Preliminary Design
Subsystem-level R/A/C
+ Interfacing + complete technology
+ Subsystems Verification Plan
Phase D(4): SAITL
System Demonstration
and Validation
Phase C(2): Final Design and Fabrication
Fabric hardware and software
Phase C(1): Final Design and Fabrication
Final Detailed Design
Phase D(1): SAITL
Verify Component Performance
DomainofEngineering
Design
DomainofSystemsEngineering

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System engineering function
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2. Derived
Requirements
3. Architecture
/Design
4. Concept
of
Operations
1. Input: Mission
Objectives (Starts Pre-
Phase A)
Output: Proceed to
next Phase, ending at
Operations (Phase E)
Other SE Functions:
6. Interfaces
7. Mission Environment
8. Resource Budgets
9. Risk Management
10. Configuration Management
11. Reviews
5.Validate and Verify
5.Validate and Verify
5.Validate and Verify

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Mission driven structural requirements PROBA-V
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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

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Launcher Input
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Structure sub-system interfaces
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Preliminary Design
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Structural Analysis
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Structural Analysis
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Thermal Analysis
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Thermal Analysis
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PROBA-V Detailed Design
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Verification by Test
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Thermal Test Model - integration
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Thermal Test
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Ombouwen to Structural Test Model
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Vibration Test
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Vibration Test
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• Spacecraft structure qualification
• Determine test spectra for equipment

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Acoustic Test
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Shock Test
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Flight Model Integration – Solar Array
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Flight Model Integration – Equipment Fit-check
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Flight Model Integration - Harness
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Flight Model Integration - Harness
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Flight Model Integration
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30. www.QinetiQ.be
© Copyright QinetiQ Limited 2010
QinetiQ Space nv
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October 26th 2012 Slide 31