Space vehicle orbital trajectory control - is performed by integrating gyroscopes system w.r.t. inertial attitude memory for roll pitch and yaw

摘要

A space vehicle on an orbital trajectory is controlled in attitude before ejection into a geostationary orbit. The control system controls in pitch yaw and roll w.r.t. an inertial attitude memory. An attitude control system comprises three integrating gyroscopes (14x, y, z) for roll pitch and yaw attitudes. The gyro outputs are filtered (17) and applied to logic threshold circuits (18) prior to application to control circuits (20) for thrust output tubes (19, 24, 25) which rotate the vehicle as required. A register (28) output control torque motors (26, 27) on roll and pitch gyros after reception of remote control signals which are received (29) and validated (30) in conjunction with output from a solar sensor (30).