1. Update of the French activities relevant to ILWS
Jean-Yves Prado, CNES

2. Status of CNES projects
PICARD
Phase C/D in progress
Launch planned for june 2009
Science Workshop at Yale in March, next in Toronto in July
TARANIS
Phase B will end in september
NASA funding for JHU/APL XGRE inst through SMEX/MoO AO- No information
Launch expected for
SMESE
Phase A ended in May ’08
Well attended Science Workshop in Paris last March
Next step to be discussed during CNES ‘SPC’ this week – 4 options presented
Launch objective
ALL BASED ON MYRIADE PLATEFORMES
ILWS Prague, June, 2008

3. PICARD SCIENTIFIC PRODUCTS in orbit:
- Diameter, limb shape and asphericity in the continuum
- TSI (x2)
- 5 spectral channels (215,393, 535, 607, 782 nm)
- Activity (images at 215 nm and Ca II)=> space weather
- Solar oscillations
from the ground :
- diameter, limb shape and asphericity,
- local atmosphere turbulence
ILWS Prague, June, 2008

4. THE PICARD SPACECRAFT SOVAP PREMOS2 SODISM
ILWS Prague, June, 2008

5. TARANIS OBJECTIVES Description
- characterization of the sprites and associated emissions, measurements of their occurrence frequency and of their distribution at the scale of the earth. (caméras, EM waves, X and  spectra, high energy electrons)
- study of the effects of the magnetic latitude and volcanic activity
Implied mechanisms
- determination of the nature of the triggering phenomena (cosmic radiation)
- determination of the source mechanisms (EM waves, X and  spectra, high energy electrons)
- study of the nature of the explosive dissipation of energy in the ionosphere and magnetosphere (EM waves, X and  spectra, high energy electrons)
Global impact
- determination of the effects on the upper atmosphere, ionosphere and magnetosphere (EM waves, high energy electrons, associated ground based measurements, other satellites)
- evaluation of the coupling atmosphere -  ionosphere - magnetosphere and inter-planetary medium
ILWS Prague, June, 2008

6. Dedicated to understanding
TARANIS
Dedicated to understanding
Atmosphere/ionosphere/magnetosphere
coupling (sprites, elves, blue jets…)
Microcameras + photometer -MCM- CEA (+JP)
EM measurements -IEM- LPCE (+PL,TCH)
X-gamma Detector -XGD- JHU/APL (USA), DNSC (DK)
Detector of high Energy ElectronsCESR (+TCH)
Quasi Sun Synchronous Orbit (2hrs LT drift/year)
Phase B to end in September
XGRE funding from NASA yet not known
Launch >2011
ILWS Prague, June, 2008

7. SMESE General View
LYOT
DESIR
HEBS
ILWS Prague, June, 2008

8. SMESE payload required performances
Wavelength/
Energy
Field of View
Spatial resolution
Cadence
LYOT :
La imager
121.6 nm
Full Disk
1.1 arcsec
10 s
LYOT :
La coronagraph
5*5 solar radii
2.3 arcsec
20 s
DESIR :
Infra-red Telescope
35 ≤ 1 ≤ 80 microns
100≤ 2 ≤ 250 microns
50 arcsec at 35 microns
100 ms
HEBS
10-500keV
200keV-10MeV
10MeV-600MeV
Full disk
1 s, down to 32 ms
ILWS Prague, June, 2008

9. SMESE Firsts
First combined imaging (disk, corona) in Ly  with high time resolution and sensitivity to trace the development of CMEs in the low corona + first polarimetric corona measurements,
First ever measurements of solar flares in the far infrared, key range for relativistic leptons and chromospheric plasma heated during flares,
First hard X-ray/gamma ray spectrometry at the highest energies ever attained with a solar-dedicated instrument, to study the most energetic electrons and nuclear processes in the Sun’s atmosphere.
Interest for Radiobiology
ILWS Prague, June, 2008

10. Mission sequence
PICARD
SMESE
TARANIS
ILWS Prague, June, 2008

11. Others Operational coordination between DEMETER and C/NOFS
STEREO Space Weather beacon Ground Station operational since Feb.
Operational coordination between DEMETER and C/NOFS
Radiation monitors onboard SAC-C, SAC-D, JASON 2
ILWS Prague, June, 2008

12. ILWS Prague, June, 2008

13. More than 20 spacecraft based on the same bus and systems
MYRIADE SERIES
More than 20 spacecraft based on the same bus and systems
in flight or in preparation
Bus waiting row
60x60x50 cm bus
S-Band TTC (Kiruna/Toulouse)
ILWS Prague, June, 2008

14. MYRIADE CAPACITY Orbit inclination > 20°
Altitude km< >1000km
DNEPR launcher as the reference
Geocentric, inertial, solar or along the velocity vector pointing
Pointing precision of 0.1 ° (actuation), ° (knowledge)
Attitude control system in nominal mode uses a stellar sensor, four reaction wheels and three magnetic torquers
up to 80 kg mass allocation to the P/L (when no propulsion/TM-X)
Power available to the P/L > 60w (highly orbit dependant)
Mass memory 16 Gbits
S-Band 400 kb/s as baseline
ILWS Prague, June, 2008

15. MYRIADE OPTIONS propulsion DV ~80 m/s (DEMETER, TARANIS…)
X-Band telemetry (>a few Gbits/day)
TM rate Mb/s depending on the ground station G/T
additional sun pointing device (PICARD, LYOT/SMESE)
quick deorbit kit under study
ILWS Prague, June, 2008

16. A few examples of the MYRIADE versatility
DEMETER, TARANIS waves and particle instruments
PARASOL Lidar for atmospheric science
PICARD, SMESE Solar observation
MICROSCOPE Fundamental physics
ARGOS Localization
ESSAIM, SPIRALE, ELINT Defense …
commercial availability of the bus (ASTRIUM, AAS)
DNEPR launch
ARIANE 5 launch
ILWS Prague, June, 2008

17. FURTHER INTERNATIONAL COOPERATION
Earth Observation as a paradigm?
a unique object, many possible instruments
curiosity driven science in competitition with monitoring science
shift from mammoth s/c (ENVISAT…) to series of small specialized satellites
A Solar Train?
ILWS Prague, June, 2008