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- ASPICS 2 - Formation Flying for Solar Physics

- ASPICS 2 - Formation Flying for Solar Physics.

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- ASPICS 2 - Formation Flying for Solar Physics

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  1. - ASPICS 2 -Formation Flying for Solar Physics ASPICS 2 : A Solar Physics Missionto observe the solar corona between 1.02 and 3.2 solar radius, both continuum & emission lines thanks to an interferometer. Formation Flying allows to observe the corona down to the solar limb and at a very low level of scattered light thanks to the distance between the 2 S/C of the formation ( around 100m). OCCULTING SPACECRAFT Attitude : +/- 1 deg CORONAGRAPH SPACECRAFT Attitude : +/-30 arc sec 100 m +/- 0.5m Study Leader : P. Duchon, CIC Team Leader : E. Hinglais, System : R. Clédassou, Schedule : September 5th 2005 to October 4th 2005 Main conclusion : The satellites are different and specialized. The Coronagraph mass is around 265 kg (including 30 kg payload). The Occulter mass is roughly 125 kg (with 20% system margin). Feasible in less than 5 years. Low level redundancy philosophy (ie. Myriade). Currently developed FF Flying techniques & technologies are well fitted. Numerous equipments from CNES Micro & Mini Sat. Science mission : 6 months mini RELATIVE LATERAL POSITION : +/-7 mm Study context and objectives ASPICS 2 is part of a joint activity between CNES/DCT & ESA/ESTEC in the frame of PROBA-3 programme . The study objective was the operational validation of CNES concurrent Engineering Facility (named CIC).

  2. The 2 S/C on the launcher 440 Kg - ASPICS 2 – (With CIC)Spacecrafts & Launch : Final configuration Spacecraft parameters • High Elliptic Orbit ~ 400 Km / 71000 / 65 or 93 deg • RF Metrology for localization and collision avoidance. • Optical Metrology for accurate lateral relative position measurement: 0.15mm (transversal) • Coronagraph S/C : Cold gas (FF) & Hydrazine (orbit) • Occulter S/C: hydrazine & Wheels Satellites Launch capability : Dnepr ST-2, Soyuz 2.1.a or 2.1.b in lower place together with a co-passenger

  3. ASPICS 2 –Synthesis Conclusion R & D Links • Dedicated to the payload • Coronagraph Interferometer optimization • Attitude stability study and test (< 1 arc sec during 1 s) • Formation Flying: • in line with current work : • RF metrology development. • Lateral sensor • Detail study 6 d.o.f. by cold gas… • gyro stellar filter performances • Strong points: • Small satellites class mission (125 Kg + 265 kg) leading to a cheap launch • Feasible in less than 5 years, • Simple operations, • No technological gap with respect to currently developed FF techniques & technologies, • Numerous of-the-shelf equipment. … AND therefore • a minimized mission cost • Weak points • study results need consolidation, • Attitude stability study & payload design, • risk due to low redundancy philosophy with regard to costs.

  4. - ASPICS II -Parameters & Scenarios MISSION SPACECRAFTs & FF ORBIT LAUNCHER Satellites : 100 – 250kg Science Ariane 5 Solar Corona : min = 1.01 to 1.03 Rs Max = 2.5 to 3.2 Rs • Common for each scenario : • Maximal heritage on other PFs • off the shelf harware • asymmetrical Formation Flying • FF on Coronagraph • Occulter on natural orbit • payload on Coronagraph • design to cost Passenger GTO ISL Distance : ~100 m Soyuz 2.1.a 2.1.b Visible : 1 Fabry-Perot interferometer ONE DAY 300 / 71 000 km • Open : • Recurrence of the satellites • “Only Cold Gas or with Hydrazine • Payload uncoupled with respect to the PFs or embedded into the PFs’ Dnepr Observation 6 hto 12 h / orbit ~6 images / 15 mn

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