Patent ID: 6032903
Filing Date: 2000-03-07
Classification: B64G

Abstract:
A method for controlling rotation rate and attitude of a satellite which is subjected to disturbance torques, the method employing cooperative thruster and wheel systems and comprising the steps of:commanding at least one parameter of a desired satellite rotation rate parameter, a desired satellite attitude parameter and a desired angular acceleration parameter;comparing said commanded parameters with sensed rotation parameters of said satellite to generate at least one error signal of an attitude error signal, a rotation rate error signal and an angular acceleration error signal;generating an estimate of said disturbance torques;in response to said generated error signal and said disturbance torques estimate, applying thruster correction torques to said satellite to reduce said error signal; andin response to said disturbance torques estimate, applying wheel correction torques to said satellite to reduce the magnitude of said thruster correction torques and thereby reduce the use of thruster fuel.