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挠性空间飞行器
相关语句
  flexible spacecraft
     ANALYSIS OF STABILITY OF LQG MODAL CONTROL SYSTEMS FOR FLEXIBLE SPACECRAFT
     挠性空间飞行器LQG模态控制系统的稳定性分析
短句来源
     Dynamics and Control Research of a Simulation Device for Flexible Spacecraft
     挠性空间飞行器仿真装置的动力学与控制研究
短句来源
     The paper studies the problems about the observability and controlability for implementing the computer control of flexible spacecraft, the selection of sampling frequency and the processing of high-order mode.
     本文研究了实现挠性空间飞行器计算机控制的可观测性和可控制性问题,以及采样频率的选择及高阶模态的处理问题。
短句来源
     SOME PROBLEMS ON COMPUTER CONTROL OF FLEXIBLE SPACECRAFT
     挠性空间飞行器计算机控制的一些问题
短句来源
     STABILITY ROBUSTNESS ANALYSIS OF ATTITUDE CONTROL SYSTEM OF A FLEXIBLE SPACECRAFT IN TIME DOMAIN
     挠性空间飞行器姿态控制系统的时间域鲁棒稳定性分析
短句来源
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  “挠性空间飞行器”译为未确定词的双语例句
     THE APPLICATION OF DIGRAPH THEORY TO THE STRUCTURE ANALYSIS OF FLEXIBLE SPACE VEHICLES
     用有向图理论分析挠性空间飞行器结构
短句来源
  相似匹配句对
     DYNAMICS OF FLEXIBLE SPACECRAFT
     挠性空间飞行器动力学
短句来源
     SOME PROBLEMS ON COMPUTER CONTROL OF FLEXIBLE SPACECRAFT
     挠性空间飞行器计算机控制的一些问题
短句来源
     Development of the Flexible Drill Stem
     挠性钻杆的研制
短句来源
     Flexible Copper Clad Laminate
     挠性覆铜板
短句来源
     The Property of the Technology of Spacecraft Failure Diagnosis
     空间飞行器故障诊断技术的特点
短句来源
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  flexible spacecraft
Studying Stability of the Flexible Spacecraft with a Discrete Control System
      
Methods of Estimating the Envelope of Elastic Oscillations of the Flexible Spacecraft
      
A problem concerned with studying of dynamics of angular motion of large space structures and flexible spacecraft was considered.
      
Fuzzy logic-based design of the generalized adaptation algorithm for the discrete control system of flexible spacecraft
      
Results of modeling a flexible spacecraft with adaptive control system were presented.
      
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The digraph theory is applied to analyze the structure of flexible space vehicles. A method is given for selecting the opltimal structure of state vector, so that the high-order matrix of system is reduced to block triangular form. It is convenient to analyze the problems of system decoupling, modal coordinate truncation, controllability and ober-vability.

本文应用有向图理论,分析挠性空间飞行器结构,给出选择状态向量的最佳结构方法,把系统的高阶矩阵简化成块三角型矩阵,从而便于分析系统的解耦、模态座标的截断和能控能观等问题。

In this paper the dynamics and the control problem of flexible spacecraft with solar arrays are investigated. A mathematical model is built by partial differential equaions and the finite element method, Then the transfer function is derived through the finding of eigenvalues and modal gains of the system,After that a PID controller is designed, and the reduction of the high order of the mathematical model is discussed, Finally an optimization method—the Powell method—is used for the controller, and a numerical...

In this paper the dynamics and the control problem of flexible spacecraft with solar arrays are investigated. A mathematical model is built by partial differential equaions and the finite element method, Then the transfer function is derived through the finding of eigenvalues and modal gains of the system,After that a PID controller is designed, and the reduction of the high order of the mathematical model is discussed, Finally an optimization method—the Powell method—is used for the controller, and a numerical example is given. Accordingly some useful conclusions are drawn from the investigation.

本文研究具有太阳帆板的挠性空间飞行器的动力学与控制问题。对于用偏微分方程或有限元法建立的数学模型,通过求取系统的特征值和模态增益,给出其传递函数,然后设计了具有比例—微分—积分形式的控制器,并进行了稳定性分析。初步探讨了高阶数字模型的降阶问题。最后,应用最优化方法申的Powell方法,对控制器参数进行了最优化设计,并给出了一个计算实例。从而得到一些有益的结论。

In this paper, the small-loop theorem and functional analysis are used to analyse the stability of LQG modal control systems of flexible spacecraft, and a sufficient condition for control systems to keep in stability under influence of residual modal is given, and the estimation of errors diviated from the ideal output under influence of residual modal is also presented.

本文利用反馈系统的小回路增益定理和泛函分析方法,对挠性空间飞行器LQG模态控制系统的稳定性进行了分析,给出了系统在剩余模态影响下保持稳定的充份条件,同时给出了系统输出在剩余模态影响下偏离理想输出值的误差估计。

 
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