Ghalam KazSTSAT

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First results and next steps in Kazakhstan
Earth Observation missions in cooperation
with SSTL
M.Moldabekov (1), M.Nurguzhin (2), V.Ten (3), S.Murushkin (3), H.Lambert (3),
A.da Silva Curiel (4), D.King (4), H.Kadhem (4), G.Taylor (4), M. Sweeting (4)
(1) Kazcosmos, Republic of Kazakhstan
(2) KGS, Republic of Kazakstan
(3) Ghalam LLP, Republic of Kazakhstan
(4) SSTL, United Kingdom
April 22nd 2015
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Contents
 Background
 KazEOSat-2 specifications
 KazEOSat-2 status
 KazSTSAT programme
 KazSTSAT specifications
 KazSTSAT status
 Conclusion
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Background
 The cooperation between the SSTL, KGS, and Ghalam companies
started with the KazEOSat-2 mission currently in the final phases
of commissioning
 The follow-up programme is carried out by a joint British-Kazakh
project team, and is focused on technology demonstration along
with provision of wide-swath multi-spectral imagery
 This KazSTSAT spacecraft will feature a brand new avionics suite
and a number of technology demonstration units provided by
Ghalam.
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KazEOSat-2 specifications
 Based on the flight proven SSTL-150 platform
 RapidEye heritage baseline
 Identical payload (5 channel MSI)
 Enhanced agility with the introduction of new 100SP wheels
 2x data rate enabled with new a new high-speed data recorder
and X-band antenna pointing mechnisms
 Better geolocation accuracy with new Rigel-L star trackers
 Increased power capabilities with triple-junction solar cells
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KazEOSat-2 specifications
Parameter
Launch
Operational lifetime, years
Weight, kg
Orbit
LTAN
GSD, m
Spectral channels
Swath, km
Daily coverage km2
Downlink rate, Mbps
Agility
Delta-V capacity m/sec
Value
June 2014 (Dnepr)
7
180
630 km SSO
10:30
6.5
5 (blue, green, red, red-edge & NIR)
77
1,000,000
160
up to 35° off-nadir angle,
60° slew in 90 seconds
> 30
© Ghalam- This document can not be reproduced, copied or communicated to third parties without written authorization
KazEOSat-2 specifications
 Based on the flight proven SSTL-150 platform
 RapidEye heritage baseline
 Identical payload (5 channel MSI)
 Enhanced agility with the introduction of new 100SP wheels
 2x data rate enabled with new a new high-speed data recorder
and X-band antenna pointing mechnisms
 Better geolocation accuracy with new Rigel-L star trackers
 Increased power capabilities with triple-junction solar cells
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KazEOSat-2 status
 In-orbit acceptance review next week
 Maximum throughput scenario has been verified in orbit
 MTF and SNR measured for all channels
 MTF > 16%
 SNR > 100
 Agile modes tested – one pass stereo and area imaging
 Geolocation verified
 Power profiles are in line with the predictions
 Reaction wheel failure
 Despite a reaction wheel failure the mission is still compliant
with the system level technical requirements due to
“redundancy for full performance” design philosophy
 Investigation ruled out all viable causes of the failure
including Single event effects and mechanical problems
 Random component failure
© Ghalam- This document can not be reproduced, copied or communicated to third parties without written authorization
© Ghalam- This document can not be reproduced, copied or communicated to third parties without written authorization
© Ghalam- This document can not be reproduced, copied or communicated to third parties without written authorization
© Ghalam- This document can not be reproduced, copied or communicated to third parties without written authorization
KazSTSAT programme
 This spacecraft is jointly developed by a team comprising
of Ghalam (a joint venture between KGS and Airbus
Defence and Space) and SSTL engineers
 The KazSTSAT will be the first implementation of the new
SSTL-X50 platform family using a next generation
“Fireworks” avionics suite, and will carry
 a wide swath multispectral imager (SLIM-6-22) as a main
payload
 a new technology demonstration on-board computer (OBC
ARM)
 Below-Diffraction Limit imager experiment
 A heritage Airbus designed Sun sensor (BASS 17) will also be
installed on the spacecraft for flight approval of the
manufacturing process in Kazakhstan.
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KazSTSAT – X50 platform
 FIREWorks modules
 Heritage SSTL modules
 BCM
 OBC750
 PDM
 S-band Tx/Rx
 AIM (ADCS interface
module)
 CAN bridge
 SGR-07 GPS receiver
 PIU
 Rigel-L star tracker
 X50 specific development
 Structure
 Propulsion subsystem
 X-band TX (80Mbps)
 10SP-M3 wheels,
Magnetometers,
Magnetorquers, Sun
Sensors, S-band and
GPS antennas
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KazSTSAT – X50 platform
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KazSTSAT specifications
Parameter
Launch
Operational lifetime, years
Weight, kg
Orbit
LTDN
GSD, m
Spectral channels
Swath, km
Daily coverage, km2
Downlink rate, Mbps
Agility
Delta-V capacity, m/s
Value
H2 2016 (Dnepr)
5
110
580 km SSO
10:30
18.5
6 (coastal UV, blue, green, red, rededge, NIR)
300
3,600,000
80
up to 30° off-nadir angle,
60° slew in 100 seconds
> 16
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KazSTSAT Status
 End of Phase C
 CDR in May
 Start of AIT in August
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Conclusion
 KazEOSat-2 is at the end of commissioning
 Despite a few delays for technical and administrative
reasons the mission is progressing towards the In-Orbit
Acceptance Review
 The reaction wheel failure does not look like systemic
and does not reduce any of the mission performances
 KazSTSAT is a unique experience because…
 Joint British-Kazakh (50/50%) team working on the
project
 A platform designed from scratch, and carrying
experimental payloads
 Higher than usual risk profile that is considered
acceptable for a non-operational mission that is
expected to benefit future missions in terms of
extended capabilities
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Thank you