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空间飞行器姿态控制
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  spacecraft attitude control
     Spacecraft Attitude Control Based on Fuzzy Variable Structure
     基于模糊变结构的空间飞行器姿态控制
短句来源
     Research and Design of a Spacecraft Attitude Control Simulator System
     空间飞行器姿态控制仿真试验平台系统研究与设计
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     Spacecraft Attitude Control Based on Quaternion
     基于四元数的空间飞行器姿态控制
  “空间飞行器姿态控制”译为未确定词的双语例句
     Design and Robust Analysis for Spacecraft Attitude Controller
     空间飞行器姿态控制设计和鲁棒性分析
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     Attitude Control of Spacecraft using Nonlinear Model Predictive Control
     一种空间飞行器姿态控制非线性模型的预测控制新算法
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     THE QUATERNION METHOD UTILIZED IN ATTITUDE CONTROL OF SPACE VEHICLE
     空间飞行器姿态控制的四元数法
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     Control law design for space vehicle attitude system
     空间飞行器姿态控制律设计
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     Research on magnetic bearing flywheels for attitude control of spacecraft
     空间飞行器姿态控制用磁轴承飞轮研究
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  相似匹配句对
     Spacecraft Attitude Control Based on Quaternion
     基于四元数的空间飞行器姿态控制
     Control law design for space vehicle attitude system
     空间飞行器姿态控制律设计
短句来源
     THE QUATERNION METHOD UTILIZED IN ATTITUDE CONTROL OF SPACE VEHICLE
     空间飞行器姿态控制的四元数法
短句来源
     Design and Robust Analysis for Spacecraft Attitude Controller
     空间飞行器姿态控制设计和鲁棒性分析
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     An Investigation on the Law of Attitude Control of Flexible Spacecraft
     挠性空间飞行器姿态控制规律的探讨
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  spacecraft attitude control
A Suggestion of Fractional-Order Controller for Flexible Spacecraft Attitude Control
      
A controller design method for flexible spacecraft attitude control isproposed.
      
Computer simulation of an adaptive spacecraft attitude control system confirms the cjjiciency of the algorithm developed.
      
Next, a nonlinear analysis of the spacecraft attitude control system using MECS is shown.
      
Second, the new approach is applied to the spacecraft attitude control problem.
      
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The attitude of .space vehicles (rocket, airplane; satellite, space shutlle) must be stabilized in the presence of interference moments, and controlled to maintain the desired attitude. All of these tasks concern about the attitude control problem. The attitude of a rigid body can be described by different parameters ,hence it yields different control methods. This paper introduces the quaternion method of attitude control of space vehicles. It also presents the synthesis of the control command and the control...

The attitude of .space vehicles (rocket, airplane; satellite, space shutlle) must be stabilized in the presence of interference moments, and controlled to maintain the desired attitude. All of these tasks concern about the attitude control problem. The attitude of a rigid body can be described by different parameters ,hence it yields different control methods. This paper introduces the quaternion method of attitude control of space vehicles. It also presents the synthesis of the control command and the control stability analysis. In addition the maneuver control of attitude and the updating of trajectory coordinates are discussed in this paper.

空间飞行器(火箭、飞机、人造卫星、航天飞机等)由于受到扰动力矩的作用,须对姿态进行稳定,或者,使其达到预定姿态,这些都涉及姿态的控制问题。刚体的姿态可以用不同的参数来描述,由此可以产生不同的控制方法。本文介绍了空间飞行器姿态控制的四元数法,分析了控制指令的形成及控制的稳定性,并且讨论了姿态机动控制和轨道坐标系修正问题。

Considering the needs of attitude control of the space vehicle and maneuver trace of warheads of missiles, a bipropellant variable-thrust liquid rocket engine has been developed by the 11th research institute.In this qaper,the process of design and research and the performances of the engine are introduced. The engine can use many kinds of propellant, it's thrust can be adjusted from 137.3 to 686.5N continously,the adjustment ratio is 5:1.The step response time of the engine is less than 80 ms,the O/F ratio...

Considering the needs of attitude control of the space vehicle and maneuver trace of warheads of missiles, a bipropellant variable-thrust liquid rocket engine has been developed by the 11th research institute.In this qaper,the process of design and research and the performances of the engine are introduced. The engine can use many kinds of propellant, it's thrust can be adjusted from 137.3 to 686.5N continously,the adjustment ratio is 5:1.The step response time of the engine is less than 80 ms,the O/F ratio error is less than ±5%.

考虑到空间飞行器姿态控制和弹道导弹的多头分导及弹头机动飞行的需要,我们研制了液体双组元可变推力发动机.本文叙述该发动机的研制过程和有关性能.该发动机可使用多种推进剂,推力可在(137.3~686.5)N的范围内连续无级调节,调节比5:1.发动机阶跃响应低于80ms,混合比偏差小于±5%.

The stability robustness of the attitude control system of a flexible spacetrafi in the time domain is investigated. As a result of the effect of the rotation of solar arrays and the variation of rotating speed of the momentum wheels, there is uncertainty in the mathematical model of the system. The uncertainty may be solved by the perturbation method to the motion equations of the dynamic system. The stability robustness criterion in the time domain is given. A numerical example shows the application of this...

The stability robustness of the attitude control system of a flexible spacetrafi in the time domain is investigated. As a result of the effect of the rotation of solar arrays and the variation of rotating speed of the momentum wheels, there is uncertainty in the mathematical model of the system. The uncertainty may be solved by the perturbation method to the motion equations of the dynamic system. The stability robustness criterion in the time domain is given. A numerical example shows the application of this method.

本文研究挠性空间飞行器姿态控制系统的时间域鲁棒稳定性分析,由于太阳帆板的转动和动量轮的转速变化,使飞行器的数学模型具有不确定性。这些不确定性可以归结为对动力学系统运动方程式的摄动。文中导出了鲁棒稳定性判据,并用算例说明其应用。

 
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