G - Physics – 05 – D
Patent
G - Physics
05
D
G05D 1/08 (2006.01) B64G 1/24 (2006.01) B64G 1/38 (2006.01) B64G 1/36 (2006.01)
Patent
CA 2041857
ATTITUDE CONTROL SYSTEM FOR MOMENTUM-BIASED SPACECRAFT ABSTRACT OF THE DISCLOSURE An attitude and nutation control system (30) for a momentum-biased vehicle (19) having roll, pitch, and yaw axes which employs a normal mode estimator (32) which predicts steady-state values for roll attitude, roll rate, and yaw rate. The normal mode estimator (32) receives instantaneous roll attitude information from an earth sensor (34) and optionally receives roll and/or yaw rate information from roll gyro (35a) and yaw gyro (35b). A logic circuit (36) coupled to the normal mode estimator (32) generates correction signals when the steady state values for roll attitude, roll rate, and yaw rate are outside predetermined limits. A plurality of thrusters (14a-d) produce torque for bringing the steady-state values for roll attitude, roll rate, and yaw rate within predetermined limits. A sample/hold-off control circuit (68) samples correction signals between thruster activations while a optimal thruster selection logic (70) employs a linear program to compute torques associated with changes in the correction signals for use by the normal mode estimator (32), as well as activating selected thrusters (14a-d).
Hughes Electronics Corporation
Sim & Mcburney
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