An approach to on-board sampled data estimation and control of the attitude motion of maneuvering spacecraft is presented. Algorithms for model following control of attitude maneuvers; estimation of spacecraft state (attitude, angular velocity, disturbance, torque); and optical-inertial attitude determination, with estimation of gyro parameters (drift rate bias, scale factor error) were developed. The algorithms were validated in single-axis software simulations of an attitude control system of the type used in the Infrared Astronomical Satellite. The control system comprises a strapdown rate-integrating gyro and a slit-type star sensor for optical-inertial attitude sensing, a reaction wheel actuator, and a digital on-board computer. The truth models for simulation of the hardware components are discussed.
Application of Model Following Control and Estimation Techniques to Attitude Control of Maneuvering Spacecraft. Part 1. Theory and Simulation Results
1982
122 pages
Report
Keine Angabe
Englisch
Spacecraft Trajectories & Flight Mechanics , Control simulation , Data sampling , Satellite attitude control , Spacecraft maneuvers , Algorithms , Airborne/spaceborne computers , Guidance sensors , Gyroscopes , Infrared astronomy satellite , Kalman filters , Reaction wheels , Strapdown inertial guidance , Foreign technology