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PROBA Project for On-board Autonomy

PROBA Project for On-board Autonomy. Verhaert Design and Development nv Hogenakkerhoekstraat 9 B 9150 Kruibeke Tel. 03/250.1 9 . 37 Fax 03/25 4 .1 0 . 08 e-mail : jo.bermyn @ verhaert.com www.verhaert.com. European Space Agency Directorate of Technology and Operations ESTEC

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PROBA Project for On-board Autonomy

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  1. PROBAProject for On-board Autonomy Verhaert Design and Development nv Hogenakkerhoekstraat 9 B 9150 Kruibeke Tel. 03/250.19.37Fax 03/254.10.08 e-mail : jo.bermyn@verhaert.com www.verhaert.com European Space Agency Directorate of Technology and Operations ESTEC The Netherlands e-mail : fteston @etsec.esa.nl

  2. PRoject for On Board Autonomy PROBA Introduction

  3. Customer: ESA Prime Contractor: Verhaert Design & Development (BE) Subcontractors: Spacebel (BE), Space Application Services (BE), Space Systems Finland (Fi), SIL (UK), Universite de Sherbrooke (Can), Officine Galileo (It) Suppliers PROBA: Project Organisation

  4. ESA technology demonstration program Operational Autonomy demonstration Planning-scheduling, resource management, FDIR, On-board Flight Dynamics New Technology Demonstration Powerfull avionics system, ERC32 and DSP, Li-Ion Battery, 3D Package Technology, GPS Attitude Determination Payload Demonstration Main instrument (CHRIS) challenging the autonomy and ACNS SREM, DEBIE, HRC, WAC Internet Access Proba : Mission

  5. Mass : 100 kg Volume : 80cm x 60cm x 60cm Power : 40 to 90 W Compatible with PSLV / ASAP5 High pointing accuracy ACNS Absolute pointing error 150 arcsec Relative pointing error 5 arcsec over 10 sec Proba : Key figures

  6. PROBA Block Diagram

  7. Honeycomb structure Passive thermal control Body mounted solar panels with GaAs cells 28 V regulated power bus, 9 Ah Lithium-Ion battery S-band communication system ( 4kbit/s uplink, 1Mbit/s downlink) ERC-32 based DHS S-band small ground station (2,4 m dish) 3-axis stabilised ACNS 4 reaction wheels 4 magnetotorquers 2 three-axis magnetometers 1 Star Tracker with 2 optical heads 1 Star Tracker as part of CHRIS 1 GPS with 4 antennas PROBA Subsystems

  8. PROBA Accommodation

  9. PROBA flight structure

  10. Low Earth Orbit (LEO) 560x720 km Near polar with an inclination of 97.7 ° Polar Satellite Launch Vehicle (PSLV) Launch by Antrix/ISRO, India Launch site : Shriharikota Scheduled launch 2001 Proba launch / orbit

  11. Dual ERC 32 based avionics for ACNS and DHS/TT&C Payload Computer DSP (21020) for image processing/compression Integrated mass memories (for HK and Science data) Smart Instrumentation points and house keeping bus experiment TT&C in S-band CCSDS PROBA Avionics

  12. Ga As Solar Arrays (90W peak power) 36 Li-ion cells, 9Ah, 25V Central protected power distribution with regulated bus. PROBA Power

  13. ACNS 3-axis control: high accuracy pointing and manoeuvring (absolute pointing accuracy better than 360 arcsec) Gyro-less attitude control Navigation function (autonomous orbit estimation) Guidance function (f.e. Fly By predictions) ACNS automated software generation ACNS Technology demonstrations: Star Tracker Resonating Gyroscope GPS Attitude Determination PROBA ACNS

  14. ACNS Block Diagram PROBA ACNS

  15. GPS receiver Position and velocity determination, Time synchronization with UTC, attitude determination experiment (SSTL) Redundant star tracker with dual head High Accuracy (arcsec range), autonomous attitude determination from “Lost in Space” situation, compatible with tumbling rates of up to 1.2°/sec 4 Miniature Reaction Wheels Storage capacity 0.04 Nms, Momentum 5 mNm 2 Magnetometers 4 Magnetotorquers ACNS Components

  16. Compact High Resolution Imaging Spectrometer 25 m resolution 19 spectral bands (415 - 1050 nm) Bi-directional Reflectance Distribution Function measurements PROBA Payloads

  17. Imaging with CHRIS (BRDF measurements) PROBA Payloads

  18. PROBA Payloads Imaging with CHRIS (BRDF measurements)

  19. High Resolution Camera Panchromatic 10 m ground resolution 3D Packaging Technology CCD PROBA Imagers • Wide Angle Camera • Miniaturised (7x7x6 cm) • CMOS Active Pixel Sensor

  20. SREM Standard Radiation Environment Monitor Objectives: Earth radiations environment Space weather DEBIE Debris In-orbit Evaluator Objectives: Sub-millimeter debris population Knowledge and models PROBA Earth Environment Instruments SREM DEBIE

  21. Earth Environment Instruments PROBA Payloads DEBIE SREM

  22. PROBA Ground Station • S-Band • 2.4 m Transportable Antenna (Redu, BE) • ESOC network compatible: packet TC/TM, SCOS Spacecraft control • Data Distribution via network/web • “Light-out” ground station

  23. PROBA Development • STM – Table model Avionics – PFM • Integrated SVF/SCOS based development (SW, EGSE, spacecraft simulator, operations) • Automated SW generation for ACNS

  24. PROBA Status

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