Update of the French activitiesrelevant to ILWS

Jean-Yves Prado, CNES

ILWS Prague, 11-12 June, 2008 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 2011-12

■ 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 2012-2013

■ ALL BASED ON MYRIADE PLATEFORMES

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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

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THE PICARD SPACECRAFT

PREMOS2

SOVAP

SODISM

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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

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TARANIS

• Dedicated to understandingAtmosphere/ionosphere/magnetospherecoupling (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

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SMESE General View

DESIR

LYOT

HEBS

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SMESE payload required performances

Wavelength/Energy

Field of View

Spatial resolution

Cadence

LYOT : L imager

121.6 nm Full Disk 1.1 arcsec 10 s

LYOT :L coronagraph

121.6 nm 5*5 solar radii

2.3 arcsec 20 s

DESIR :Infra-red Telescope

35 ≤ 1 ≤ 80 microns

100≤ 2 ≤ 250 microns

Full Disk 50 arcsec at 35 microns

100 ms

HEBS 10-500keV200keV-10MeV10MeV-600MeV

Full Disk Full disk 1 s, down to 32 ms

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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

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PICARD SMESE

Mission sequence

TARANIS

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Others

• 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

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MYRIADE SERIES

• More than 20 spacecraft based on the same bus and systems in flight or in preparation

60x60x50 cm bus

S-Band TTC (Kiruna/Toulouse)

Bus waiting row

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MYRIADE CAPACITY

■ Orbit inclination > 20°■ Altitude 600km< >1000km■ DNEPR launcher as the reference

■ Geocentric, inertial, solar or along the velocity vector pointing■ Pointing precision of 0.1 ° (actuation), 5.10-3° (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

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MYRIADE OPTIONS

■ propulsion V ~80 m/s (DEMETER, TARANIS…)

■ X-Band telemetry (>a few Gbits/day) TM rate 16-50 Mb/s depending on the ground station G/T

■ additional sun pointing device (PICARD, LYOT/SMESE)

■ quick deorbit kit under study

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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

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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?

FURTHER INTERNATIONAL COOPERATION