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针对利用反作用飞轮作为执行机构的微小卫星姿态控制系统,详细讨论了基于dSPACE实时仿真机、单轴气浮转台、星载计算机及陀螺和反作用飞轮实物的卫星姿态控制系统半物理仿真的方案设计;并利用该系统对仅用反作用飞轮的卫星姿态大角度机动控制模式进行了半物理仿真验证。仿真结果表明根据陀螺和反作用飞轮现有精度,设计的大角度姿态机动控制算法能够满足分系统技术要求,同时验证了半物理仿真系统方案设计合理、可靠。
Aimed at the microsatellite attitude control system using reaction flywheel as actuator, the scheme design of semi-physical simulation of satellite attitude control system based on dSPACE real-time simulator, single-axis air-floating turntable, spaceborne computer, gyro and reaction flywheel is discussed in detail. The semi-physical simulation of the satellite attitude maneuvering control mode using only reaction flywheel was carried out by using this system. The simulation results show that the designed large-angle attitude maneuver control algorithm can meet the technical requirements of subsystems according to the current accuracy of gyroscope and reaction flywheel. At the same time, it is verified that the design of semi-physical simulation system is reasonable and reliable.