Slide 1 PROBA Project for On-board Autonomy Verhaert Design and Development nv Hogenakkerhoekstraat 9 B 9150 Kruibeke Tel. 03/ Fax 03/ European Space Agency Directorate of Technology and Operations ESTEC The Netherlands

Slide 2October 2000 PROBA Introduction PRoject for On Board Autonomy

Slide 3October 2000 PROBA: Project Organisation 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

Slide 4October 2000 Proba : Mission 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

Slide 5October 2000 Proba : Key figures 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

Slide 6October 2000 PROBA Block Diagram

Slide 7October 2000 PROBA Subsystems 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

Slide 8October 2000 PROBA Accommodation

Slide 9October 2000 PROBA flight structure

Slide 10October 2000 Proba launch / orbit 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

Slide 11October 2000 PROBA Avionics 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

Slide 12October 2000 PROBA Power Ga As Solar Arrays (90W peak power) 36 Li-ion cells, 9Ah, 25V Central protected power distribution with regulated bus.

Slide 13October 2000 PROBA ACNS 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

Slide 14October 2000 PROBA ACNS ACNS Block Diagram

Slide 15October 2000 ACNS Components 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

Slide 16October 2000 PROBA Payloads Compact High Resolution Imaging Spectrometer –25 m resolution –19 spectral bands ( nm) –Bi-directional Reflectance Distribution Function measurements

Slide 17October 2000 PROBA Payloads Imaging with CHRIS (BRDF measurements)

Slide 18October 2000 PROBA Payloads Imaging with CHRIS (BRDF measurements)

Slide 19October 2000 PROBA Imagers High Resolution Camera Panchromatic 10 m ground resolution 3D Packaging Technology CCD Wide Angle Camera Miniaturised (7x7x6 cm) CMOS Active Pixel Sensor

Slide 20October 2000 PROBA Earth Environment Instruments SREM Standard Radiation Environment Monitor Objectives: –Earth radiations environment –Space weather DEBIE Debris In-orbit Evaluator Objectives: –Sub-millimeter debris population –Knowledge and models SREM DEBIE

Slide 21October 2000 PROBA Payloads Earth Environment Instruments SREM DEBIE

Slide 22October 2000 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

Slide 23October 2000 PROBA Development STM – Table model Avionics – PFM Integrated SVF/SCOS based development (SW, EGSE, spacecraft simulator, operations) Automated SW generation for ACNS

Slide 24October 2000 PROBA Status