MYRIADE and MYRIADE Evolutions Programs - Cnes

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