Method of controlling the attitude of satellites,...

Details Method of controlling the attitude of satellites,... Method of controlling the attitude of satellites,...

2004-10-29

2010-02-16

Mansen, Michael R (Department: 3644)

Aeronautics and astronautics

Spacecraft

Attitude control

C701S013000

Reexamination Certificate

active

07661627

ABSTRACT:
A method of controlling the attitude of a satellite (1) including two gyrodynes (3,4) and a third main actuator (2) which delivers torques at least along the Z axis. The method includes: fixing the gimbal axes, A1and A2, of the gyrodynes (3, 4) parallel to Z; setting a non-zero bias (α) between the angular momentum vectors (Formula I) of the gyrodynes; using the measurements provided by the sensors on board the satellite to estimate the kinematic and dynamic variables necessary in order to control the attitude of the satellite (1); calculating set variables in order to the objectives assigned to the satellite (1) attitude control system; and using the deviations between the estimated variables and the set variables to calculate control orders and to send same to the main actuators (2, 3, 4).

REFERENCES:
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patent: 2 786 283 (1998-11-01), None
Three Dimensional Reorientation of a Spacecraft Containing a Single Reaction Wheel and a Single Movable Appendage. Chunlei Rui, N. Harris McClamroch, Anthony M Bloch. Proceedings of the 36th Conference on Decision and Control. Dec. 1997.
French Preliminary Search Report FR 0312914; report dated Jun. 11, 2004.
International Search Report PCT/FR2004/002800; report dated Mar. 16, 2005.

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