公开(公告)号：US3866025A

公开(公告)日：1975-02-11

申请号：US34177573

申请日：1973-03-15

Applicant: RCA CORP

Inventor： CAVANAGH JOHN DENIS

IPC: B64G1/26 ,  G05D1/10

CPC classification number: B64G1/26

Abstract: A system wherein orbit-adjust thrusters of a Pitch Momentum Bias spacecraft are used to perform both orbital inclination adjustment and roll and/or yaw attitude control. A strapdown inertial reference system comprising two rate gyros is operated in conjunction with an on-board computer to derive the shortest angle through which the total angular momentum vector of the spacecraft must be rotated to bring it into alignment with the orbit normal vector and the ideal torque to produce this rotation of the total angular momentum vector. The computer is then operated to select a combination of orbit adjust thrusters which produce a torque which best approximates the ideal torque and to control their firing to achieve the alignment of the total angular momentum vector with the orbit normal vector. Thereafter, the computer is operated to select the combination of orbit adjust thrusters which produce a torque to reduce the roll and/or yaw angular attitude error rates of the spacecraft. In one operation, both orbit inclination adjustment and attitude control are performed simultaneously.

Abstract translation: 使用俯仰动量偏移航天器的轨道调整推进器进行轨道倾斜调节和侧倾和/或偏航姿态控制的系统。 包括两个速率陀螺仪的​​捷联惯性参考系统与车载计算机一起运行以得出最短角度，通过该最短角度，航天器的总角动量向量必须旋转以使其与轨道法向量和理想 扭矩产生总角动量矢量的这种旋转。 然后操作计算机以选择轨道调整推进器的组合，其产生最接近理想转矩的扭矩并且控制其点火以实现总角动量向量与轨道法线向量的对准。 此后，操作计算机以选择产生扭矩的轨道调整推进器的组合，以减小航天器的滚动和/或偏航角姿态误差率。 在一个操作中，同时执行轨道倾斜调节和姿态控制。