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某型号微小卫星的有效载荷为三线阵CCD相机 ,因此对于姿态控制系统有相当高的要求 :对地定向三轴稳定指向精度优于 0 .3°,稳定度优于 0 .0 0 1(°) /s。针对该要求进行了控制系统设计 ,并在单轴气浮转台的基础上 ,根据国内现有硬件情况进行了半物理仿真验证。结果表明 :所设计的控制器原理简单、易于实现且具有较好的鲁棒性 ,满足总体提出的设计要求。同时证明 ,国内现有的光纤陀螺和反作用飞轮等硬件的性能指标均可满足某型号微小卫星姿态控制系统的要求。
The payload of a certain type of micro-satellite is a three-line CCD camera, so there is a very high demand for attitude control system: the directional three-axis directional stability to ground is better than 0.3 ° and the stability is better than 0.010 ° ) / s. According to the requirements of the control system design, and on the basis of the single-axis air flotation turntable, according to the current hardware conditions in China conducted a semi-physical simulation. The results show that the designed controller is simple in principle, easy to implement and has good robustness and meets the overall design requirements. At the same time, it is proved that the performance indexes of the existing hardware such as fiber optic gyroscope and reaction flywheel can meet the requirements of a certain type of micro-satellite attitude control system.