SATELLITE ROLL AND YAW ATTITUDE CONTROL METHOD
 Inventor: Patrick Flament, Le Cannet, France
 Assignee: Aerospatiale Societe Nationale Industrielle, Paris, France
 Appl. No.: 619,548
 Filed: Nov. 29, 1990
 Foreign Application Priority Data
Nov. 29, 1989 [FR] France 89-15732
 Int. Cl.s B64G 1/36
 U.S. CI 244/168; 244/165;
 Field of Search 244/164, 165, 168, 158 R
 References Cited
U.S. PATENT DOCUMENTS
4,230.294 10/1980 Pistiner 244/165 X
4,260,942 4/1981 Fleming 244/165
4,325,124 8/1982 Renner 244/164 X
4,732,354 3/1988 Lievre 244/168 X
4,767.084 8/1988 Chan et al 244/164
4,949,922 8/1990 Rosen 244/168
FOREIGN PATENT DOCUMENTS
0295978 12/1988 European Pat. Off. .
2522614 3/1982 France .
2531547 8/1982 France .
Primary Examiner—Jesus D. Sotelo
Assistant Examiner—Christopher P. Ellis
A method to control the attitude in roll (X) and in yaw (Z) of a satellite including two solar generator panels adapted to be oriented independently of each other about a pitch axis. In a preliminary stage: two geometrical axes x and z are selected in the plane of the roll and yaw axes, there being associated with the z axis a tolerable command torque error much lower than for the x axis, and a correlation law is established between satellite panel depointing angles ys and ys and possible command torques due to solar radiation pressure. Then cyclically while the satellite performs its orbit: a theoretical attitude correction torque in the plane of the roll and yaw axes is calculated, a possible torque is identified having on the z axis, a component substantially identical to that of the theoretical torque, and on the x axis, a component as close as possible to the theoretical torque component, and there are applied to the panels the depointing angles associated with the possible torque in accordance with the correlation law.