摘要
针对卫星控制力矩陀螺姿态控制系统中存在构型冗余复杂、体积重量大等问题,提出了一种新型三自由度球形动量交换装置以降低控制系统冗余并提高系统集成度。分析并建立了上述装置的动力学和电气模型,证明了其应用于卫星姿态机动的可行性;由于装置转子的偏转角度有限,传统反馈姿态控制律无法克服倾角饱和引起的奇异问题,提出采用一种具有n级分步的欧拉轴Bang-Bang增量机动控制策略。Simulink仿真结果表明,改进控制策略能够克服球形转子倾斜范围的限制,单个装置能够实现卫星大角度姿态机动控制。
Multi - DOF electromagnetic momentum exchange actuators can effectively reduce the weight, volume and power consumption of the spacecraft attitude control system. To reduce system redundancy, a new 3 - DOF spherical momentum exchange actuator is proposed. The dynamic equations of motion and electrical model are devel- oped. Analysis shows that it has the potential to perform three - axis attitude control. Due to the limited rotor tilt range, a Bang - Bang incremental maneuver strategy with n - step switch is adopted. Simulation results validate the effectiveness of the proposed strategy, and confirm the device＇s potential to provide three - axis control for satellites.
出处
《计算机仿真》
CSCD
北大核心
2016年第4期58-62,共5页
Computer Simulation
基金
天津大学自主创新基金项目(1405)
关键词
姿态机动
动量反应球
增量机动
数字仿真
Attitude maneuver
Spherical actuator
Incremental maneuver
Numerical simulation
