基于Simulink/Stateflow的小卫星姿态控制模块设计与仿真研究

Simulink/Stateflow Based Attitude Control Block Design and Simulation of Small Satellite

针对小卫星在轨自主运行的需要,对其姿态控制模块进行设计与仿真研究,其中使用修正罗德里格参数描述卫星姿态运动并进行姿态控制律设计,使用Stateflow设计了六种姿态控制模式及其转换逻辑并结合Simulink搭建了姿态控制仿真系统。根据对地定向模式、目标指向模式、闲置模式的时序指令进行了姿态控制仿真分析,三种模式下姿态均收敛,说明了姿态控制律设计和姿态控制模式之间转换逻辑设计的正确性。

According to demands of autonomous operation of small satellite on orbit, the design and simulation of attitude control block was researched on, satellite attitude motion and builded attitude control law were described by modified rodrigues parameters, six kinds of attitude control mode and it＇ s transform logic were designed usiug stateflow, and attitude control simulation system was alse constructed using simulink. Attitude control simulation analysis was carried on time sequence commands of nadir pointing mode, target pointing mode and idle mode, and the attitude convergence result was achieved, which indicated that the design of attitude control law and transform logic among attitude control modes was correct.