航天器姿态控制

采用平行构型变速控制力矩陀螺群的航天器姿态控制

Spacecraft attitude control using parallel-gimbaled variable speed control moment gyros group

四元数的核心矩阵及其在航天器姿态控制中的应用

Kernel matrix of quaternion and its application in spacecraft attitude control

近期在航天器姿态控制问题中使用Rodrigues参数的报道也引起注意。

Recently the application of Rodrigues parameters in the attitude control of spacecraft attracts some attention .

基于Fliess泛函展开式的航天器姿态控制

Attitude Control of Spacecraft via Fliess Functional Expansion

基于正实性方法的挠性航天器姿态控制设计

Flexible Spacecraft Attitude Control Design Based on Positive Real Method

基于轨道机动的航天器姿态控制技术评估分析

Evaluation Analysis on Control Technique of Attitude Based on Spacecraft Orbit Maneuver

航天器姿态控制的正规矩阵方法研究

Research on Normal Matrix Methodology of Attitude Control for Spacecraft

基于逆系统方法与内模原理的航天器姿态控制

Spacecraft attitude control based on inverse system and internal model

基于滑模变结构的航天器姿态控制方法研究

Research on Method of Spacecraft Attitude Control Based on Sliding Variable Structure

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 .

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

一种无角速度信息的挠性航天器姿态控制方法

A Velocity-Free Attitude Controller of Flexible Spacecraft

以太阳帆板展开过程中航天器姿态控制为例，作了计算机仿真。

Satellite attitude control during deployment solar panels as an example , simulation on computer is performed .

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 .

该控制器有效地提高了航天器姿态控制的鲁棒性和适应性。

Nonlinear robust decentralized controller can effectively improve robustness and adaptability of the spacecraft attitude control systems .

航天器姿态控制执行机构

Attitude control actuator 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 .

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 .

在航天器姿态控制领域，模糊控制技术作为一种辅助控制方法得到越来越多的关注。

In the field of spacecraft attitude control , the controllers based on fuzzy logic have received increasing attentions as auxiliary control strategies .

大角度机动作为现代航天器姿态控制关键技术之一，一直为航天控制领域关注。

The large angle maneuver is one of the key technologies for spacecraft attitude control , which has been the focus of attention .

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 .

基于旋转群代数，以航天器姿态控制研究为背景，提出了四元数的核心矩阵的概念。

A concept of kernel matrix of quaternion is proposed , which is based on rotation group algebra and with spacecraft attitude control as its background .

研究了基于时间尺度分离和滑动模态的航天器姿态控制问题。

A two-loop sliding mode controller is achieved , with the outer loop tracking the given attitude angles and the inner loop tracking the designed angular velocities .

自20世纪50年代以来，随着航天技术的迅猛发展，挠性航天器姿态控制问题得到了密切的关注和广泛的研究。

With the development of aerospace technology , attitude control problem of flexible spacecraft has received considerable attention and comprehensive investigation ever since the fifties of the last century .

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 .

最后对带有太阳帆板展开的航天器姿态控制进行了仿真研究，结果初步表明本智能自适应控制方法的有效性。

Finally , the intelligent adaptive control method is applied to attitude control of a type spacecraft with deploying the solar panels . The simulation result shows that the intelligent adaptive control method presented is effective and feasible .

主要完成以下几个方面的工作：针对存在惯量参数不确定、外干扰力矩的挠性航天器姿态控制问题，提出一种动态输出反馈鲁棒姿态控制方案。

The main contents of this dissertation are as follows : A robust control scheme based on dynamic output feedback control is proposed for the attitude control problem of a flexible spacecraft in the presence of parametric uncertainty , external disturbances .