Picard (satellite)
| Mission type | Solar research |
|---|---|
| Operator | CNES |
| COSPAR ID | 2010-028A |
| SATCAT no. | 36598 |
| Spacecraft properties | |
| Bus | Myriade |
| Start of mission | |
| Launch date | 15 June 2010, 14:42:21 UTC |
| Rocket | Dnepr |
| Launch site | Dombarovsky 370/13 |
| Contractor | ISC Kosmotras |
| End of mission | |
| Last contact | 4 April 2014 UTC |
| Orbital parameters | |
| Reference system | Geocentric |
| Regime | Low Earth |
PICARD is a satellite dedicated to the simultaneous measurement of the absolute total and spectral solar irradiance, the diameter and solar shape, and to the Sun's interior probing by the helioseismology method. These measurements obtained throughout the mission allow study of their variations as a function of solar activity. It launched, along with the Prisma spacecraft, on June 15, 2010 on a Dnepr launcher from Dombarovskiy Cosmodrome, near Yasny, Russia. The mission, originally planned for two years, ended on April 4, 2014.
The objectives of the PICARD mission are to improve our knowledge of:
The PICARD mission was named after the French astronomer of the 17th century Jean Picard (1620–1682) who achieved the first accurate measurements of the solar diameter. These measurements are especially important as they were made during a period when the solar activity was minimum characterized by a sun nearly without sunspots between 1645 and 1710. This period was found by Gustav Spörer using sunspots observations gathered in Europe and this period is now named Maunder minimum. By comparing the diameter during the Maunder minimum and the diameter when the sun was active a variation has been found, leading to the still-unanswered question, "Are diameter and activity linked?" During this period in Europe, there was an unusually cold climate.
PICARD used the Myriade microsatellite platform, developed by CNES to use as much as possible common equipment. This platform was designed for a total mass of about 120 kg mass at launch. Its attitude in space is maintained by using a star sensor, solar sensors, a magnetometer, gyrometers, several magnetic rods and reaction wheels. If an orbit control and orbit manoeuvres are needed, a hydrazine system may be used. The on-board management is centralised, and uses a 10 MIPS microprocessor T805. A mass memory is available for the data storage. The telemetry and telecommand used the CCSDS standard.
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