MYRIADE and MYRIADE Evolutions Programs - Cnes
MYRIADE and MYRIADE Evolutions Programs - Cnes
MYRIADE and MYRIADE Evolutions Programs - Cnes
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4S Symposium, Portoroz, June 2012 : Myriade <strong>Evolutions</strong><br />
4S Symposium,<br />
Portoroz, Slovenia<br />
June 2012<br />
<strong>MYRIADE</strong> <strong>and</strong><br />
<strong>MYRIADE</strong> <strong>Evolutions</strong><br />
<strong>Programs</strong><br />
Paul Rodrigues,<br />
4th June 2012<br />
CNES<br />
DCT/PO/FS
SUMMARY<br />
4S Symposium, Portoroz, June 2012 : Myriade <strong>Evolutions</strong><br />
SUMMARY<br />
1. <strong>MYRIADE</strong> 1st generation<br />
2. <strong>MYRIADE</strong> <strong>Evolutions</strong>
Launch mass : 130 kg launch mass<br />
3<br />
4S Symposium, Portoroz, June 2012 : Myriade <strong>Evolutions</strong><br />
<strong>MYRIADE</strong> 1 st generation :<br />
Main Characteristics<br />
Compatibility with : ARIANE 5, Soyuz, Dniepr, PSLV, …<br />
50 kg - 60 W offered to payload ( 13h LTAN )<br />
Plateforme : 60 cm x 60 cm x 60 cm, 65 Kg<br />
Compatibilty with GTO <strong>and</strong> Sun Synchronous orbits (all LTAN)<br />
Providing high performances for this class of satellites :<br />
Star Tracker <strong>and</strong> gyrometers : 0,02 degres precision pointing<br />
Mission data management :<br />
Up to 32 Gbits storage capacity,<br />
16 to 60 Mbps using X b<strong>and</strong> transmisssion<br />
One axis drive mechanism for Solar Array<br />
In orbit lifetime : 3 years specified (> 6 ans in fact)<br />
Normalized interfaces between platform <strong>and</strong> payload :<br />
Mechanical, electrical, comm<strong>and</strong> <strong>and</strong> control<br />
Minimize efforts ifor mission development<br />
A stabilized industrial organisation :<br />
Parternish agreement with Thales Alenia Space <strong>and</strong> Astrium<br />
Long Term Agreements with equipement providers<br />
TARANIS views
4<br />
Same board to ground interface<br />
Same network of small S B<strong>and</strong><br />
earth terminals (TTCET): ICONES<br />
Same ground control center<br />
Normalized interfaces between<br />
control center <strong>and</strong> mission center<br />
“working hours” operations<br />
4S Symposium, Portoroz, June 2012 : Myriade <strong>Evolutions</strong><br />
<strong>MYRIADE</strong> 1 st generation :<br />
Myriade : a platform st<strong>and</strong>ard but also a system concept<br />
St<strong>and</strong>ardized satellite simulator for system validation. Capability to add payload simulatio<br />
System interfaces st<strong>and</strong>ard shared with Proteus product lines (5 Mini satellites)
5<br />
DEMETER<br />
PARASOL<br />
ESSAIM<br />
ELISA<br />
<strong>MYRIADE</strong> 1 st Generation : 15 years history<br />
2004 2005 2006 2007 2008 2009 2010 2011 2012 2013 2014 2015 2016 2017 2018 2019 2020<br />
DEMETER<br />
ESSAIM (4 satellites)<br />
PARASOL<br />
SPIRALE SPIRALE (2 satellites)<br />
PICARD<br />
ALSAT 2A<br />
ALSAT 2B<br />
SSOT<br />
VNRedSAT<br />
TARANIS<br />
MicroScope<br />
MERLIN<br />
Scientific Missions<br />
French Defence Mission<br />
Industrial Exports<br />
<br />
5 Myriade Satellites<br />
launched with Helios 1B<br />
( ARIANE 5)<br />
4S Symposium, Portoroz, June 2012 : Myriade <strong>Evolutions</strong><br />
PICARD<br />
ALSAT 2A<br />
PORTOROZ - 4S<br />
ELISA (4 satellites)<br />
SSOT<br />
VNRedSAT<br />
TARANIS<br />
MicroScope<br />
5 Myriade Satellites<br />
launched with Pleiade 1A<br />
( Soyuz Kourou)<br />
ALSAT 2B<br />
MERLIN : 1st MYRADE<br />
EVOLUTION MISSION ----><br />
end 2021
6<br />
<strong>MYRIADE</strong> <strong>Evolutions</strong> : the new generation<br />
Why a new generation :<br />
To deal with obsolescence problems for equipement units designed 10 years ago<br />
Optimize the design for new lanchers offer ( Soyuz ASAP internal <strong>and</strong> external<br />
position, VEGA, <strong>and</strong> end of AR5 auxiliary position offer for LEO )<br />
To deal with French Law for Space Operations (Space Debris Mitigation) <strong>and</strong><br />
European REACH regulation<br />
Propose a st<strong>and</strong>ard platform solution for upcoming mission requiring more on<br />
board resources:<br />
Earth Monitoring : Merlin (Methane measurement), MicroCarb (CO2 measurement)<br />
Earth Observation<br />
Space an Sun observation (from LEO)<br />
Defence<br />
Comply with ISIS st<strong>and</strong>ard (Ground to Sat IF) applicable for new CNES missions :<br />
Packet Utilization St<strong>and</strong>ard from ECSS<br />
« Private » services for guidance, autonomy<br />
Share common Comm<strong>and</strong> <strong>and</strong> Control Center<br />
Share common S <strong>and</strong> X b<strong>and</strong> ground station network<br />
4S Symposium, Portoroz, June 2012 : Myriade <strong>Evolutions</strong>
7<br />
PayloadMeanPower (W)<br />
180<br />
160<br />
140<br />
120<br />
100<br />
80<br />
60<br />
40<br />
20<br />
0<br />
Typical Payload Mass <strong>and</strong> Power Needs<br />
4S Symposium, Portoroz, June 2012 : Myriade <strong>Evolutions</strong><br />
<strong>MYRIADE</strong> Payloads Mass / Mean Power Domain<br />
TOPASE<br />
CLOUDICE<br />
0 20 40 60 80 100 120 140<br />
Payload Mass (kg)<br />
MERLIN 6h<br />
<strong>MYRIADE</strong> Ev<br />
ASAP max<br />
MERLIN 6h max?<br />
PICARD 6h<br />
HYPXSIM TARANIS<br />
<strong>MYRIADE</strong><br />
PICARD 6h<br />
HYPXSIM TARANIS<br />
<strong>MYRIADE</strong><br />
MICROCARB<br />
Initial Max<br />
HYPEX Obs Terre NG<br />
MISTIGRI<br />
PARASOL<br />
ELISA<br />
TYREX<br />
PF TARANIS<br />
PARASOL<br />
ELISA<br />
TYREX<br />
PF TARANIS<br />
Capa<br />
ESSAIM<br />
Réactive PF PICARD PF <strong>MYRIADE</strong><br />
ALSAT -SSOT<br />
DEMETER<br />
Initiale<br />
<strong>MYRIADE</strong> Ev<br />
autre lanceur max<br />
PF <strong>MYRIADE</strong><br />
<strong>Evolutions</strong>
8<br />
<strong>MYRIADE</strong> <strong>Evolutions</strong> : main requirements<br />
General Requirements :<br />
Orbits : 500 to 800 kms, Inclination > 45 degres<br />
In orbit Lifetime : 5 to 7 years<br />
Reliability > 0,6 at 5 years with full performances<br />
Availabity > 0,9<br />
Agility : 0,5 deg /sec<br />
Services to payload <strong>and</strong> mission (typical values):<br />
Mass :<br />
Data Storage : > 512 Gbits,<br />
70 Kg to 120 kg depending on launcher<br />
160 Mbit/sec input<br />
• Power (orbital mean value) :<br />
100 W at 12h LTAN,<br />
130 W at 6h LTAN<br />
Volume :<br />
Plate : 600mm x 800mm<br />
High : 420 mm ( Soyuz external ) or<br />
820 mm ( Soyuz internal )<br />
4S Symposium, Portoroz, June 2012 : Myriade <strong>Evolutions</strong><br />
Data downlink : 180 Mbits/sec BER 10 -9<br />
Geo-Localization: 100 to 200 m (3σ)<br />
Datation : 6 µs
Avionics :<br />
9<br />
<strong>MYRIADE</strong> <strong>Evolutions</strong> : Platform Main Technical Characteristics<br />
CPU Board based specific ASIC including T805<br />
Tank :7 Kg to 10 Kg hydrazine, 22 to 5 bars<br />
instruction set, floating point unit, TM/TC functions,<br />
4 x 1 Newton thursters, Isp # 210 sec<br />
Processor Interface Controlers for I/O with platform<br />
Hydrazine baselined but possible change to LMP103S<br />
equipement units<br />
depending on REACH decision <strong>and</strong> performances<br />
Oslink, RS422, 1553B, Spacewire for Interfaces<br />
De presurisation system for end of life<br />
with payload<br />
Attitude <strong>and</strong> Orbit Control :<br />
Up to 4 Mass Memory Modules : 4 x 512 Gbits<br />
Star Tracker : 1 or 2 Optical Heads,<br />
TC Authentication based on CCSDS st<strong>and</strong>ard<br />
Gyrostellar or gyroless possible configurations,<br />
4 reaction wheels (1 Nms) in tetrahedral configuration<br />
1,3 m2 Solar Array, XTJ solar cells<br />
GPS in the guidance loop<br />
Solar Array Drive méchanism : up to 13 A<br />
Radiofrequency :CCSDS compliant<br />
Battery :700 Wh (BOL)<br />
S B<strong>and</strong> : TM 625 Kbits/s,QPSK, Reed Solomon<br />
Decentralized heaters management (BRIO System)<br />
TC 32 Kbits/s biphase PCM/PM<br />
Electrical isolation of battery at end of life<br />
2 Omni directional antenna<br />
B<strong>and</strong>e X Telemetry : 180 Mbits/s, OQPSK, RS<br />
On going development with Arianespace <strong>and</strong> RUAG<br />
Possible 2 x 180 Mbits/s by cross polarisation<br />
(Sweden) : Φ 610 mm, for up to 300 Kg satellite<br />
Link budgets with 5dB margins for S+X 5,4 m ground<br />
stations<br />
Power :<br />
Launcher Interface Ring:<br />
4S Symposium, Portoroz, June 2012 : Myriade <strong>Evolutions</strong><br />
Propulsion :
S B<strong>and</strong>Rx/Tx<br />
OBC<br />
PCDU)<br />
10<br />
X<br />
Z<br />
Y<br />
Mass<br />
Memory<br />
Star Tracker<br />
4S Symposium, Portoroz, June 2012 : Myriade <strong>Evolutions</strong><br />
<strong>MYRIADE</strong> <strong>Evolutions</strong> : general layout<br />
X B<strong>and</strong> Tx GNSS Rx<br />
Magnetorquer<br />
Reaction<br />
Wheels<br />
Propulsion.<br />
Battery<br />
Gyrometer<br />
Payload<br />
View under fairing Soyuz<br />
ASAP external position<br />
Solar<br />
Array<br />
10
11<br />
4S Symposium, Portoroz, June 2012 : Myriade <strong>Evolutions</strong><br />
<strong>MYRIADE</strong> <strong>Evolutions</strong> : planning<br />
2011 2012 2013 2014 2015<br />
Phase A<br />
Phase B<br />
PORTOROZ - 4S<br />
Equipement Selection :<br />
Phase C/D<br />
• Invitation to Tender published 3rd quarter 2012<br />
• Request for Proposal : 4th quarter 2012<br />
Flight Models delivery<br />
Merlin P/F AIT<br />
2016 2017<br />
Merlin PF+<br />
P/L AIT
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