The control, technology of wheel state feedback is the. leading topic of the actuator in the satellite attitude control system.
飞轮状态反馈控制技术是当前卫星姿控系统执行部件的前沿课题。
The fault simulation of satellite attitude control system is crucial for research and experimental verification on optimizing configuration, fault diagnosis, reconstruction of control system.
进行卫星姿态控制系统故障模拟，对控制系统优化配置、故障诊断、系统重构技术研究与实验验证具有重要作用。
Reaction wheel is an important executive component of satellite attitude control system, and the improvement of flywheel system is spurred by high performance satellite attitude control system.
反作用飞轮是卫星姿态控制系统的重要执行元件，提高飞轮系统的性能对卫星姿态控制系统具有重要意义。
A momentum wheel control system is widely used for the attitude control of satellite.
在人造卫星的姿态控制中，广泛地采用偏置动量轮控制系统。
At last, the hardware in the loop simulation system for three-axis stabilized satellite attitude control based on PC, with reaction wheel and gyro in the loop is designed.
最后，该文设计了一个基于PC机的三轴稳定卫星姿态控制硬件在回路仿真系统，将反作用飞轮、陀螺等实物接入仿真系统。
This article analyzes the status change in the attitude control system when faults appear based on one polar orbit satellite, and provides a method to decide faulty component.
以某极轨对地观测卫星为背景，分析了姿态控制系统中单机部件出现故障时，系统将会出现的状态变化情况，找出故障部件的判定方法；
The proposed results are useful to the attitude dynamic analysis and control system design for not only the spacecraft with large rotation parts, but also the agile small satellite.
所得结果不仅适用于具有大型运动部件的航天器的姿态动力学分析及控制系统设计，也适用于灵敏小卫星的相应研究。
Simulation results show that the control performance of the satellite attitude system is improved, and the difficulties of traditional PID parameter regulation can be avoided by this method.
仿真结果表明，使用遗传算法pid参数自整定方法，对卫星的姿态系统具有较好的控制性能，并且克服了传统PID调参困难的缺点。
And in the midcourse velocity correction segment, effects on the state error propagation caused by attitude errors and control system performance of the chasing satellite were studied.
在中途速度修正段，分析了追踪航天器姿态误差和控制系统性能误差对状态误差传播的影响。
And in the midcourse velocity correction segment, effects on the state error propagation caused by attitude errors and control system performance of the chasing satellite were studied.
在中途速度修正段，分析了追踪航天器姿态误差和控制系统性能误差对状态误差传播的影响。
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