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空间飞行器动力学
相关语句
  “空间飞行器动力学”译为未确定词的双语例句
     ON DYNAMIC FEEDBACK LINEARIZATION OF SPACECRAFT DYNAMICAL MODELS
     空间飞行器动力学模型的动态反馈线性化
短句来源
     DYNAMICS OF FLEXIBLE SPACECRAFT
     挠性空间飞行器动力学
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
     DOCKING DYNAMICS OF A SPACECRAFT
     空间飞行器对接动力学研究
短句来源
     Dynamics of Enzyme Catalysis
     酶催化动力学
短句来源
     Dynamics of Rational Functions
     有理函数的动力学
短句来源
     ATTITUDE IDENTIFICATION OF SPACECRAFT
     空间飞行器的姿态识别
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  dynamics of spacecraft
Combined equations of motion for description of dynamics of spacecraft docking using the pin-cone system
      
The aim is to provide an introduction to the rigid body dynamics of spacecraft.
      


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。

Because the dynamics' property of the flexible spacecraft with large solar panels is very complex, decoupling method is adopted to study the stability of the attitude control system for single axis through suitable assumption. The system PID parameters are designed using polar assignment according to rigid satellite. Then with root locus method, the sufficient condition is determined that the system designed by rigid satellite parameter ensures the stability of flexible spacecraft control system. The relation...

Because the dynamics' property of the flexible spacecraft with large solar panels is very complex, decoupling method is adopted to study the stability of the attitude control system for single axis through suitable assumption. The system PID parameters are designed using polar assignment according to rigid satellite. Then with root locus method, the sufficient condition is determined that the system designed by rigid satellite parameter ensures the stability of flexible spacecraft control system. The relation among parameters is derived and the stability of single axis flexible spacecraft attitude control system is studied. At last, the system performance is verified by simulation.\;

针对带有大型太阳帆板的挠性空间飞行器动力学特性十分复杂的特点 ,通过合理的假设 ,采用单轴解耦分析姿态控制系统稳定性问题。采用极点配置法 ,按照刚体卫星设计系统PID参数 ,利用根轨迹 ,确定按刚体卫星参数设计的系统能使挠性空间飞行器控制系统具有渐近稳定性的充分条件 ;推导系统参数间的关系式 ,分析挠性空间飞行器主轴姿态控制系统稳定性问题。最后 ,通过仿真验证了系统的性能。

This paper is concerned with attitude control for large angle rapid maneuver of spacecraft, and discusses a kind of forecast algorithm without control. By using strong tracking filter(STF),it discusses a kind of forecast-tracking control algorithm for attitude maneuver of spacecraft, based on dynamics model of spacecraft. At the same time, it is discovered that attitude converges very fast, when exponent decay rate changes with attitude error of spacecraft. And the simulation using MATLAB fuzzy controller is...

This paper is concerned with attitude control for large angle rapid maneuver of spacecraft, and discusses a kind of forecast algorithm without control. By using strong tracking filter(STF),it discusses a kind of forecast-tracking control algorithm for attitude maneuver of spacecraft, based on dynamics model of spacecraft. At the same time, it is discovered that attitude converges very fast, when exponent decay rate changes with attitude error of spacecraft. And the simulation using MATLAB fuzzy controller is also discussed. The result shows that forecast-tracking control algorithm is valuable.

该文主要针对空间飞行器大角度机动调整的姿态控制方面的问题 ,从空间飞行器的动力学模型出发 ,讨论了利用强跟踪滤波进行无控预报的预测技术 ,以及以此预报信息对空间飞行器大角度机动调整进行姿态解耦的控制技术。同时 ,在预测控制中发现 :姿态角跟踪路径的指数衰减因子随着其偏差不同及时调整时 ,控制系统收敛较快。因此 ,进一步讨论了利用MATLAB模糊控制器来调整预测控制的指数衰减因子的模糊预测控制方法。通过仿真计算 ,该方法具有收敛快 ,稳定性高等特点

 
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