Orbiting satellite attitude control system - corrects roll, yaw and pitch from angular displacement measurements and gyroscopic electronic feedback

摘要

The device enables the attitude to be corrected w.r.t. to the axes of roll (x), yaw (y) and pitch (z). Inertial flywheels (15, 16) symmetrically disposed about the roll axis impose a moment along the yaw axis. External torques may be provided by reaction jets (26, 32). Electronic control of correction mechanisms acts upon signals from angular displacement detectors (11, 12) tachometric flywheel revolution counters, and tele-commands from earth. Low power stored-programme logic circuits produce flywheel motor speed commands based on calculations including constant, derivative and integral terms contained in equations of spacecraft stability. Constant or periodically varying correction terms derived from earth signals are superposed on calculated terms. The system can also be used in a mode governed by angle amplitude correction by telecommunication in an antenna alignment arrangement.