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Space vehicle orbital trajectory control - is performed by integrating gyroscopes system w.r.t. inertial attitude memory for roll pitch and yaw
Space vehicle orbital trajectory control - is performed by integrating gyroscopes system w.r.t. inertial attitude memory for roll pitch and yaw
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机译:航天器的轨道轨迹控制-通过集成陀螺仪系统w.r.t.惯性姿态存储器,用于侧倾和偏航
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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).
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