Swidler Berlin Shereff Friedman, LLP
Gyroless control system for zero-momentum three-axis stabilized spacecraft
A method for maintaining three axis control of a geosynchronous spacecraft without body rate measurements using reaction wheel assemblies. Earth sensor assembly angle measurements are utilized for high-bandwidth roll and pitch control. A positive pitch momentum bias is stored in the reaction wheel assemblies. A gyroscopic feedforward torque is applied to rotate reaction wheel assembly momentum in a yaw/roll plane of the spacecraft at orbit rate. A dynamic mode that couples yaw and roll axes and that results from applying the gyroscopic feedforward torque and the high-bandwidth roll control is damped based on earth sensor assembly roll measurements.
Lockheed Martin Corporation
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inventional inventional additional inventional
Neil Evan Harald Santosh Xipu
Goodzeit Weigl Ratan Li