作为一种高精度的执行机构，反作用飞轮已广泛应用于卫星姿态控制系统中。
As a kind of high accuracy executive machine, reaction wheel has been extensively applied to the attitude control system (ACS) of satellites.
将所得结果应用于卫星姿态控制系统的设计，以解决对模型进行线性化处理时产生的误差。
The proposed method is applied to satellite attitude controller design to cope with the errors arising while linearization procedure.
动量轮作为卫星姿态控制系统的关键执行部件，对其故障检测对维持卫星的正常运行具有重要意义。
Momentum wheel is a key actuator of the attitude controlling system of a satellite. Thus, it is very meaningful to accomplish its fault detection to maintain the working order of the satellite.
提出了一种基于最小二乘支持向量机(LSSVM)非线性观测器的卫星姿态控制系统故障诊断方法。
A fault diagnosis method for satellite attitude control systems is presented based on least squares support vector machine (LSSVM).
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。
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。
Reaction wheel is one of the main disturbance sources that affect the precision of attitude control system of spacecraft.
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。
The fault simulation of satellite attitude control system is crucial for research and experimental verification on optimizing configuration, fault diagnosis, reconstruction of control system.
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。
A momentum wheel control system is widely used for the attitude control of 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。
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.
在现代卫星的姿态控制系统中，反作用轮得到了广泛应用。
Reaction wheels are widely used in the modern spacecraft attitude control systems.
星模拟器是卫星控制系统中姿态测量关键部件——星敏感器的一项重要地面试验设备。
The star simulator instrument is an important test equipment on the ground of star sensitivity instrument which is a stance test key component in planet control system.
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；
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.
本论文分别以三轴稳定刚性卫星姿态控制和带太阳帆板的三轴稳定卫星姿态控制为研究对象，建立了控制系统数学模型。
Models of the three-axis stabilized Attitude Control Systems of a rigid satellite and a flexible satellite with a pair of solar arrays are set up.
仿真结果表明，该方案可以保证卫星的姿态控制精度、结构振动抑制和控制系统鲁棒性。
Simulation results show that the presented control can ensure the precision of the attitude control performance, suppression of the structure vibrations and robustness of the control system.
仿真结果表明，该方案可以保证卫星的姿态控制精度、结构振动抑制和控制系统鲁棒性。
Simulation results show that the presented control can ensure the precision of the attitude control performance, suppression of the structure vibrations and robustness of the control system.
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