Aeronautics and astronautics – Spacecraft – Attitude control
Patent
1990-06-07
1992-03-24
Peters, Jr., Joseph F.
Aeronautics and astronautics
Spacecraft
Attitude control
244171, 244172, B64C 120
Patent
active
050980416
ABSTRACT:
An attitude and nutation control system (30) for a momentum-biased vehicle (10) 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 (14 a-d).
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Denson-Low Wanda K.
Hughes Aircraft Company
Mitchell Steven M.
Mojica Virna Lissi
Peters Jr. Joseph F.
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