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.
本文讨论了这种姿态控制系统的设计方法和动力学性能。
The design procedure and dynamic behavior of this system are discussed.
姿态控制系统(acs)软体负责维护航空器的姿态。
The attitude Control System (ACS) software is responsible for maintaining the attitude of the spacecraft.
作为应用实例，分析了在飞行姿态控制系统中的应用。
As an application example, its application to flight attitude control system is analysed.
文中给出了一个弹性飞行器的姿态控制系统作为设计举例。
An example of an attitude control system of a bending vehicle is given.
用这种方案设计的姿态控制系统有非常好的灵活性。
The attitude control system designed with this concept has better flexibility.
姿态控制推力器(act)是飞行器控制系统的执行部件。
The attitude control thruster (ACT) is the control component of the flight vehicle.
研究偏置动量姿态控制系统中的集成能量与姿态控制问题。
The integrated power and attitude control for a bias momentum attitude control system is investigated.
拦截器姿态控制系统是一个非线性控制系统。
Interceptor attitude control system is a nonlinear control system.
拦截器姿态控制系统是一个非线性控制系统。
Interceptor attitude control system is a nonlinear control system.
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