verhaert innovation day 2012 – jef van hove (verhaert) - proba-v satellite structure design &...

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PROBA-V satellite structure

CONFIDENTIAL

Jef Van Hove

VERHAERT

Jef.vanhove@verhaert.com

October 26th 2012 Slide 1

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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

3

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PROBA diagram

4

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PROBA-V(egetation) mission

5

• 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

6

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

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System engineering function

7

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

8

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

9

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Structure sub-system interfaces

10

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Preliminary Design

11

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Structural Analysis

12

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Structural Analysis

13

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Thermal Analysis

14

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Thermal Analysis

15

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PROBA-V Detailed Design

16

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Verification by Test

17

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Thermal Test Model - integration

18

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Thermal Test

19

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Ombouwen to Structural Test Model

20

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Vibration Test

21

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Vibration Test

22

• Spacecraft structure qualification

• Determine test spectra for equipment

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Acoustic Test

23

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Shock Test

24

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Flight Model Integration – Solar Array

25

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Flight Model Integration – Equipment Fit-check

26

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Flight Model Integration - Harness

27

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Flight Model Integration - Harness

28

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Flight Model Integration

29

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QinetiQ Space nv

30

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October 26th 2012 Slide 30