PROCEDE DE CONTROLE D'ATTITUDE EN ROULIS ET EN LACET D'UN SATELLITE.

摘要

For the control of the attitude in roll (X) and in yaw (Z) of a satellite (1) comprising two solar generator wings (4,5) which are steerable independently of one another around a pitch axis: … &cirf& in advance: two geometric axes x and z are chosen in the plane of the axes of roll and of yaw, with the z axis being associated a tolerable steering couple error much smaller than for the x axis and a correlation law is established between the pointing error angles gamma N and gamma S of the wings of the satellite and of the control couples achievable as a result of the presence of the pressure of solar radiation, &cirf& then, cyclically, while the satellite describes its orbit: a possible theoretical attitude correction couple is calculated in the plane of the axes of roll and of yaw, an achievable couple is identified having, with respect to the z axis, a component substantially identical to that of the theoretical couple and, with respect to the x axis, a component as close as possible to the component of the theoretical couple, and the pointing error angles associated by the correlation law with this achievable couple are applied to the wings. … …IMAGE…