초록 ▼

An arrangement for attitude control and stabilization of a three-axis stabilized, bias momentum spacecraft which is equipped with a spin wheel arrangement that is capable of generating an angular momentum vector in a predeterminable direction, as well as control torques about all three axes of a spa

An arrangement for attitude control and stabilization of a three-axis stabilized, bias momentum spacecraft which is equipped with a spin wheel arrangement that is capable of generating an angular momentum vector in a predeterminable direction, as well as control torques about all three axes of a spacecraft fixed system of coordinates, independently of one another. The control arrangement is equipped with an attitude sensor, which measures the attitude deviation about a first lateral axis (roll axis) oriented perpendicularly to the predetermined direction, with actuators for generating external control torques. A decoupling controller uses the deviations signal (roll angle phi) and takes into account the magnitude of the angular momentum generated by the spin wheel momentum arrangement, to provide a control signal which causes unidirectional decoupling of the roll dynamics from the yaw dynamics, for the spin wheel arrangement for generating a control torque about a second lateral axis (yaw axis) which is orthogonal to the predeterminable direction and to the first lateral axis.

대표청구항 ▼

[ We claim:] [1.] Arrangement for the attitude control and stabilization of a three-axis-stabilized, bias momentum spacecraft which is equipped with a spin wheel arrangement which is capable of generating an angular momentum vector in a predeterminable direction (pitch axis) as well as control torqu

[ We claim:] [1.] Arrangement for the attitude control and stabilization of a three-axis-stabilized, bias momentum spacecraft which is equipped with a spin wheel arrangement which is capable of generating an angular momentum vector in a predeterminable direction (pitch axis) as well as control torques about all three axes of a spacecraft-fixed system of coordinates independently of one another, and is equipped with an attitude sensor which measures the attitude deviation about a first lateral axis (roll axis) oriented perpendicularly to the predeterminable direction, and with actuators for generating external control torques, characterized by a decoupling controller which, using the deviation signal (roll angle .phi.) and taking into account the magnitude h.sub.y of the angular momentum generated by the spin wheel arrangement, provides a control signal, which causes the unidirectional decoupling of the roll dynamics from the yaw dynamics, for the spin wheel arrangement for generating a control torque EQU T.sub.WZD =H.sub.z with H.sub.z .ident.-h.sub.y .phi. ut a second lateral axis (yaw axis) which is orthogonal to the predeterminable direction and to the first lateral axis.