航天器快速姿态机动的力矩陀螺控制

SGCMG Steering Law Design for Agility Spacecraft Reorientation

考虑一类要求快速、连续的姿态机动控制任务,设计了大角度姿态机动的力矩陀螺操纵律。针对陀螺群构型非奇异情况,考虑陀螺框架角速度上限要求,设计了基于∞范数的力矩陀螺操纵律。为了实现快速的姿态机动衔接,提出了基于参考构型的方法,并通过引入零运动实现。设计了力矩陀螺操纵律的求解算法,给出了参考构型法的解析解。仿真结果表明,该操纵律可适用于快速、连续的姿态机动控制。

SGCMG steering logic for a series of agility attitude maneuvers was studied. The main innovation lies in the design of a ∞ norm-based steering logic and a reference-based null motion. ∞ norm-hased control law was applied to restrict gimbal angle rates within limits. An algorithm for computing torque-producing ∞ norm-based ginabal rates was developed. A reference-based null-motion approach was designed to improve SGCMG configuration in the end of maneuver. Both of these designs are applicable to nonsingular state. A simulation example is presented, illustrating the performance for a minimally-redundaat parallel-mounted array. Novel steering logic is simple and is adapted to real time controller.