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空间飞行器控制
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  spacecraft control
     This thesis presents the feasibility of Nonlinear Model Predictive Control implemented in spacecraft control and the optimality of increasing the control precision and decreasing the fuels expenditure.
     模型预测控制法所能达到的性能和效率也能满足当前和未来空间飞行器控制的要求。
短句来源
     4. Test results to the implementation of MPC for spacecraft control.
     四.验证非线性模型预测控制(NMPC)应用于空间飞行器控制的可行性及其节省燃料和高控制精度的优越性。
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  相似匹配句对
     The Vibration Suppression Control of Flexible Spacecrafts
     柔性空间飞行器的振动抑止控制
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     Spacecraft Nonlinear Variable Structure Control
     空间飞行器的非线性变结构控制
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     Chapter Two An Overview of the Internal Control System of Property Insurance Companies
     财务会计控制
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     Control of Waste Incinerators
     垃圾焚烧炉的控制
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  spacecraft control
Mathematical Modeling of Spacecraft Control Sessions in Unidentified Situations
      
A method of fuzzy logical-linguistic description of the processes of operation of automatic radio electronic systems for spacecraft control in the case of unidentified situations in the ground equipment is presented.
      
An application to the boundary feedback control of a vibrating beam is provided in detail and an application to the stabilization of the NASA Spacecraft Control Laboratory is sketched.
      
Exploiting Unstable Periodic Orbits of a Chaotic Invariant Set for Spacecraft Control
      
The integrated executive enables designers to code knowledge via a combination of procedures and declarative models, yielding a rich modeling capability suitable to the challenges of real spacecraft control.
      
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In this paper the approach of variable structure control strategy (VSCS) is applied to the control problems of large flexible spacecrafts taking the nonlinear forces into consideration. As the "assumed modes method" is employed, the measurement technique for obtaining the mode coordinates is studied. After the analysis of a suggested reaching law, the overall nonlinear feedback control law is established. This reaching law guarantees on one hand an exponential reaching velocity and a finite reaching time by...

In this paper the approach of variable structure control strategy (VSCS) is applied to the control problems of large flexible spacecrafts taking the nonlinear forces into consideration. As the "assumed modes method" is employed, the measurement technique for obtaining the mode coordinates is studied. After the analysis of a suggested reaching law, the overall nonlinear feedback control law is established. This reaching law guarantees on one hand an exponential reaching velocity and a finite reaching time by diminishing the chattering phenomenon on the other hand. It is assumed that the torque may be more adequate than the force used as control actions. Some further efforts are needed as indicated in the conclusion.

本文研究了大型柔性结构空间飞行器的控制问题。采用设定模态法,将系统化为常微分方程组所描述的系统。此系统是非线性的,被控运动是绕中心毂体的转动机动运动,并详细的讨论了变结构控制规律的应用。

he problems of spillover management of flexible spacecraft dynamic output feedback control systems are studied.Parameter optimization and orthogonal subspace methods of allevi-ating spillover of the systems are presented. One robust measure of the control svstems is defined in tenns of closed-loop poles and used to justify the final design。 Through adding constraint to optimal design index,a synthetic method of optimal control system design and spillover allevia-tion is made.Using the method the spillover is...

he problems of spillover management of flexible spacecraft dynamic output feedback control systems are studied.Parameter optimization and orthogonal subspace methods of allevi-ating spillover of the systems are presented. One robust measure of the control svstems is defined in tenns of closed-loop poles and used to justify the final design。 Through adding constraint to optimal design index,a synthetic method of optimal control system design and spillover allevia-tion is made.Using the method the spillover is efficiently alleviated, so the interaction of control-ler and residual modes is redueed and robustness of the control system is improved

研究挠性空间飞行器控制系统鲁棒设计的动态输出反馈控制系统中的“溢出”管制问题,给出了抑制“溢出”的正交空间法和参数优化方法,而且通过在设计指标中引入对“溢出”的管制项,使控制系统最佳设计和“溢出”管制结合起来,达到了减少“溢出”,改善系统鲁棒性的目的。

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。

 
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