航天器控制系统

该框架可适用于不同的航天器控制系统。

This framework can be suited for various spacecraft control systems .

面向航天器控制系统故障诊断的实时专家系统通用框架

A General Framework Oriented Real-Time Fault Diagnosis Expert System for Spacecraft Control System

高可靠性设计是现代航天器控制系统设计的关键问题，而容错技术是可靠性设计的主要方面。

High dependability design is the key issue of modern spacecraft control system .

挠性航天器控制系统的最优综合

The optimal synthesis of flexible spacecraft control systems

基于时间逻辑的航天器控制系统故障诊断的深层知识表示方法

A Representation of Deep Knowledge Based on Time Logic in Fault Diagnosis of Spacecraft Control System

最后还探讨了大型复合航天器控制系统设计中必须注意的一些工程实际问题。

At last , several noticeable engineering problems in control system design of LCS are discussed .

航天器应急控制系统丙烯腈装置应急控制技术研究与应用

Spacecraft hazard contro Research and Application of Emergency Control Technology on Acrylonitrile Unit

考虑转动和挠性附件的航天器姿态控制系统建模与仿真

Modeling and Simulation for Spacecraft Attitude Control System Considering Rotational and Flexible Accessories

基于小波分析的航天器姿态控制系统故障诊断方法研究

Research on Wavelet Analysis Based Fault Diagnosis for Attitude Control Subsystem of Spacecraft

液体晃动能影响航天器姿态控制系统的稳定性。

Liquid slosh can cause the instability of a spacecraft attitude control system .

柔性充液航天器喷气控制系统稳定性分析

Stability analysis of JET-CONTROLLED system for flexible liquid-filled spacecraft

航天器姿态控制系统的退步控制设计方法

Spacecraft Attitude Control System Design via Backstepping Method

航天业务环境模拟装置载人航天器环境控制系统

ABES ( Aerospace Business Environment Simulator ) environmental control system for manned space vehicle

载人航天器环境控制系统

Environmental control system for manned space vehicle

短时记忆算法的出现，为航天器姿态控制系统提供了更简易且性能更优秀的控制方法。

The emergence of memory algorithm for satellite attitude control system provides a more simple control method .

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 .

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 .

故障诊断技术在确保系统可靠性和安全性方面起着至关重要的作用，特别是在航天器姿态控制系统中。

Fault diagnostic technology is essential to ensure the reliability and safety of system , Especially in the spacecraft attitude control system .

为满足航天器姿态控制系统仿真的需要，利用面向对象建模方法，设计了受控航天器的通用仿真框架。

Using object-oriented modeling method , a general simulation frame is designed in order to meet the needs of the attitude control system simulation for spacecraft .

在挠性航天器姿态控制系统的设计过程中，引入协同学的思想，提出了姿态控制系统的分散协同控制结构，分析了具体的设计方案和实现过程中的关键技术。

The attitude control system with the decentralized cooperative architecture was proposed . The primary scheme and crucial techniques in the design process have been discussed .

总之，文章较深入的研究了航天器姿态控制系统，基于短时记忆的航天器姿态控制对一般航天器姿态控制系统控制设计及实现具有很好的指导意义。

In short , the article more in-depth study of the satellite attitude control system , memory algorithm for satellite attitude control of spacecraft attitude control system control the general design and realization of a good guide .

挠性航天器姿态控制系统是一个多输入多输出、耦合的不确定非线性系统，为了完成姿态控制任务，要求所设计的控制规律具有较高的鲁棒性以及参数自适应能力。

Attitude control system of spacecraft is a coupling and uncertain nonlinear system with multi-input and multi-output . In order to accomplish the attitude control missions , the control law should have robust capability to attenuate disturbances and be able to adapt to parameters .

并将模糊控制器与PID控制器的动态特性进行了比较，证实了模糊控制器较PID控制器有更好的动态控制特性和鲁棒性，特别适合在航天器发射场控制系统中应用。

The comparison between fuzzy controller and PID controller proves that the former is better than the latter in respect of dynamic properties and robustness . And therefore it is exceptionally applicable to the control system of spacecraft launch complex .

航天器主动热控制系统辐射散热的半物理仿真

Semi-physical Simulation of Radiation for Active Thermal Control System of Spacecraft

载人航天器座舱大气控制系统优化设计方法的探讨

Inquiry of Optimal Design Method for Atmosphere Control System in Manned Space Vehicle Cabin

地球敏感器作为一种重要的姿态确定传感器，已经被广泛应用于卫星等航天器的姿态控制系统中。

Earth sensor , as an important attitude determination sensor , has been widely used in attitude determination system of micro-satellites and other aircrafts .

航天器的姿态控制系统是整个航天器系统中的一个非常重要的子系统，其设计的好坏直接影响到航天器总体下达的性能指标能否满足。

The spacecraft attitude control system is a very important subsystem of the whole spacecraft system , the design of which impacts on satisfaction of holistic performance index directly .

航天器的姿态控制系统通常采用控制力矩陀螺作为它的执行机构，控制力矩陀螺控制方法研究将为航天器姿态控制提供必要的理论基础。

Control Moment Gyroscope is a commonly used controller in an attitude control system of spacecraft , Control methods research of control moment gyroscope have provided necessary theoretical basis for developing attitude control system of spacecraft .

精密滚珠丝杠副因其优异的直线传动性能，一直是航天器电动伺服控制系统中重要的传动定位元件，因此开展针对航天工况下精密滚珠丝杠副的承载性能研究是非常必要的。

Because of its excellent linear transmission performance , precision ball screw has been one of important linear transmission elements in the spacecraft electric servo control systems , so the study of the bearing captivity under spaceflight conditions is very necessary .

本文结合实际项目航天器用蓄电池充电控制系统，详细阐述了基于MCS一51单片机的蓄电池充电控制器以及结合CAN总线的上位机远程监控系统。

Combined with a practical program Charging Control System of Storage Cells Used in Space-shuttles , this paper elaborates an MCS-51-based charging controller and CAN-based long-distance monitoring system .