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航天器姿态控制系统需要特殊的运行环境,在地面很难考核,这给系统可靠性带来一定的风险。针对微纳卫星的特点,设计并研制了一套面向微纳卫星的姿态确定与控制半实物仿真系统。该系统通过数字化模型模拟卫星姿态轨道运动、敏感器模型产生敏感器测量数据、执行器模型生成控制力矩、敏感器模拟器实现通信协议,最终实现姿态控制系统的全系统仿真。这套系统可以接入卫星控制系统回路,实现对姿控系统软件、硬件的考核,同时验证算法的性能。基于该系统,对天拓三号卫星姿控系统进行地面半实物仿真,并对比在轨试验数据,结果表明系统设计合理,仿真结果可信。
Spacecraft attitude control system requires a special operating environment, difficult to assess the ground, which brings certain risks to system reliability. According to the characteristics of the micro-nano satellite, a set of semi-physical simulation system for attitude determination and control is designed and developed. The system simulates the orbital movement of the satellite through a digital model, the sensor model generates the sensor measurement data, the actuator model generates the control torque, the sensor simulator realizes the communication protocol, and finally realizes the system-wide simulation of the attitude control system. The system can access the satellite control system loop to achieve posture control system software and hardware assessment, while verifying the performance of the algorithm. Based on this system, the ground-based semi-physical simulation of the Tien Tau III satellite attitude control system is carried out, and the in-orbit test data are compared. The results show that the system is reasonable in design and the simulation results are credible.