Slide 1
PROBAProject for On-board Autonomy
Verhaert Design and Development nv
Hogenakkerhoekstraat 9
B 9150 Kruibeke
Tel. 03/250.19.37 Fax 03/254.10.08
e-mail : [email protected]
www.verhaert.com
European Space Agency
Directorate of Technology and Operations
ESTEC
The Netherlands
e-mail : fteston @etsec.esa.nl
October 2000 Slide 2
PROBA Introduction
PRoject for On Board Autonomy
October 2000 Slide 3
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
October 2000 Slide 4
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
October 2000 Slide 5
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
October 2000 Slide 6
PROBA Block Diagram
DHS
AOCS I/F
Reaction Wheels (4)
Magnetometers (2)
Magnetotorquers (4)
PCS
GPS Receiver
Star Tracker (2)
Head
Head
Receivers (2)Transmitters
(2)
SREM
DEBIE
PPU
CHRIS
Imagers
Other Payloads
BatterySolar Array
Power line
Digital Control line
October 2000 Slide 7
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
October 2000 Slide 8
PROBA Accommodation
October 2000 Slide 9
PROBA flight structure
October 2000 Slide 10
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
October 2000 Slide 11
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
October 2000 Slide 12
PROBA Power
• Ga As Solar Arrays (90W peak power)• 36 Li-ion cells, 9Ah, 25V • Central protected power
distribution with regulated
bus.
October 2000 Slide 13
PROBA ACNS
ACNS Software - Navigation - Guidance - Control
Reaction Wheels (4)
Magnetometers (2)
Magneto-torquers (4)
GPS Receiver
Star Tracker (2)
Head
Head
Star Tracker(payload)
Resonating gyroscope
• 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
October 2000 Slide 14
PROBA ACNS
• ACNS Block Diagram
October 2000 Slide 15
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
October 2000 Slide 16
PROBA Payloads
• Compact High Resolution Imaging Spectrometer– 25 m resolution– 19 spectral bands (415 - 1050 nm) – Bi-directional Reflectance Distribution Function measurements
October 2000 Slide 17
PROBA Payloads
Imaging with CHRIS (BRDF measurements)
19 km
Beginimaging
Endimaging
Line of sightof imager
Image 2Image 4Image 5 Image 1Image 3
1
23
45678
9
10
October 2000 Slide 18
PROBA Payloads
Imaging with CHRIS (BRDF measurements)
October 2000 Slide 19
PROBA Imagers
• High Resolution Camera• Panchromatic • 10 m ground resolution• 3D Packaging Technology CCD
•Wide Angle Camera• Miniaturised (7x7x6 cm) • CMOS Active Pixel Sensor
October 2000 Slide 20
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
October 2000 Slide 21
PROBA Payloads
• Earth Environment Instruments
SREM
DEBIE
October 2000 Slide 22
PROBA Ground Station
S/C
PGS AGS
End User
WWWServer
MCS
Mission
INTERNET
TM/TCTM
ACS
ArchivesArchives
UserRequests
Repor tsNoti¼cations
End User
• 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
October 2000 Slide 23
PROBA Development
• STM – Table model Avionics – PFM
• Integrated SVF/SCOS based development (SW, EGSE, spacecraft simulator, operations)
• Automated SW generation for ACNS
October 2000 Slide 24
PROBA Status
Top Related