复杂充液航天器的晃动及其对控制系统的影响是当前空间高技术的重要问题。
Sloshing of Complex Liquid-filled spacecraft and its influence on the control systems are the recently significant problem in the space technology.
可以说大至航天器、飞机、军舰，小到车床、电视、手机都有嵌入式控制系统的用武之地。
From spacecrafts airplanes, warships to lathes, televisions, cellphones, applications of embedded control system are very broad.
充液航天器内部液体晃动及其对控制系统的影响，是当前国内外航天高技术研究的重要课题，也是一个比较复杂的问题。
The problem for fuel sloshing in the space vehicles and its influence on the control systems are important and complex in the space science technology.
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.
反作用轮是影响航天器姿态控制系统精度的主要扰动源之一。
Reaction wheel is one of the main disturbance sources that affect the precision of attitude control system of spacecraft.
反作用轮是影响航天器姿态控制系统精度的主要扰动源之一。
Reaction wheel is one of the main disturbance sources for the attitude control system accuracy of spacecraft.
本文首先介绍了逆系统方法的基本思想，然后将其用于航天器非线性姿态控制系统的设计中。
In this paper, the basic theory of the inverse system method is introduced, and is used in the design of a spacecraft attitude control system.
针对现代航天器对控制任务的需求特点，基于航天器对象特征模型知识描述，提出了具有多层结构的智能自适应控制系统概念。
According to the requirements of modern spacecraft control, this paper presents a hierarchical intelligent adaptive control system based on the description of plant feature model knowledge.
研究搭载在空间站或其他近地轨道航天器上的空间模块化机械手系统的容错控制系统。
This paper studies a fault-tolerant control system for a space modular manipulator system mounted on space station or other spacecrafts such as satellites, located in low earth orbit.
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.
因而航天器的控制系统、状态估计系统将会受到航天器惯性参数变化的影响。
Hence spacecraft control, state estimation systems are affected by the variations of the spacecraft's inertia parameters.
研究航天器集成能量与姿态控制系统中飞轮的控制律。
Research on Distributed Interactive Simulation Method of Missiles Attitude Control System;
研究航天器集成能量与姿态控制系统中飞轮的控制律。
Research on Distributed Interactive Simulation Method of Missiles Attitude Control System;
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