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柔性空间飞行器
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  flexible spacecraft
     The flexible spacecraft with elastic appendages is modelled as multibodycluster system. Considering the actual characteristic of slow-relatiVe-motion betweenadjacent bodies, omitting the high order nonlinear terms, employing the D'Alembert'sprinciple in virtual work and using hybrid coordinate, the governing dynamic equationof multibody cluster system is derived.
     将带有弹性附件的柔性空间飞行器模化为多体簇系统,考虑相邻体间相对运动为缓慢的实际特点,在忽略高阶非线性项的情况下,利用D'Alembert虚功原理,采用混合坐标的方法,建立了该多体簇系统的基本动力学方程。
短句来源
  approach to flexible spacecrafts
     A VARIABLE STRUCTURE CONTROL APPROACH TO FLEXIBLE SPACECRAFTS
     柔性空间飞行器的变结构控制
短句来源
  “柔性空间飞行器”译为未确定词的双语例句
     The Vibration Suppression Control of Flexible Spacecrafts
     柔性空间飞行器的振动抑止控制
短句来源
     Research on Dynamic Response and Simulation of Flexible Spacecraft
     柔性空间飞行器姿态动力学响应仿真的研究
短句来源
     Three dimension attitude dynamical model with consideration of bending and torsional deformations of the flexible appendages is derived by using quasi coordinate LaGrange' equations,and attitude kinetic model is described by quaternion.
     建立了柔性空间飞行器三轴耦合姿态动力学模型和四元数姿态运动学模型 ,建模时考虑了帆板的弯曲变形和扭转变形。
短句来源
  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
短句来源
     A VARIABLE STRUCTURE CONTROL APPROACH TO FLEXIBLE SPACECRAFTS
     柔性空间飞行器的变结构控制
短句来源
     Object-Oriented and Program Flexibility
     面向对象程序设计的柔性
短句来源
     The Flexibility of Decision Support Systems
     决策支持系统的柔性
     DYNAMICS OF FLEXIBLE SPACECRAFT
     挠性空间飞行器动力学
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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 flexible spacecraft with elastic appendages is modelled as multibodycluster system. Considering the actual characteristic of slow-relatiVe-motion betweenadjacent bodies, omitting the high order nonlinear terms, employing the D'Alembert'sprinciple in virtual work and using hybrid coordinate, the governing dynamic equationof multibody cluster system is derived. Constrained modality is used to account forlinear elastic deformation of components. Finally, on the basis of aforementioneddynamic equation, using...

The flexible spacecraft with elastic appendages is modelled as multibodycluster system. Considering the actual characteristic of slow-relatiVe-motion betweenadjacent bodies, omitting the high order nonlinear terms, employing the D'Alembert'sprinciple in virtual work and using hybrid coordinate, the governing dynamic equationof multibody cluster system is derived. Constrained modality is used to account forlinear elastic deformation of components. Finally, on the basis of aforementioneddynamic equation, using the state space format, the dynamic response and simulationprogram is worked out. Simulation example is presented by using this program.

将带有弹性附件的柔性空间飞行器模化为多体簇系统,考虑相邻体间相对运动为缓慢的实际特点,在忽略高阶非线性项的情况下,利用D'Alembert虚功原理,采用混合坐标的方法,建立了该多体簇系统的基本动力学方程。其中表示弹性附件的弹性变形的模态是约束模态。以上述方程为基础,采用状态空间求解方法,编制了相应的动力学响应仿真程序;文章最后给出了仿真算例。

Three axis reorientation and Vibration suppression of flexible spacecraft using reaction wheels are investigated.Three dimension attitude dynamical model with consideration of bending and torsional deformations of the flexible appendages is derived by using quasi coordinate LaGrange' equations,and attitude kinetic model is described by quaternion.Based on angular rates and quasi Euler angles,which are derived by using a quaternion matrix transformation,a control law with flexible parameters in the control...

Three axis reorientation and Vibration suppression of flexible spacecraft using reaction wheels are investigated.Three dimension attitude dynamical model with consideration of bending and torsional deformations of the flexible appendages is derived by using quasi coordinate LaGrange' equations,and attitude kinetic model is described by quaternion.Based on angular rates and quasi Euler angles,which are derived by using a quaternion matrix transformation,a control law with flexible parameters in the control gains is presented.Analysis with Lyapunov direct and indirect method indicates that the control law is able not only to stabilize the spacecraft attitude but also to suppress vibtations of the fiexible appendages.Attitude convergence of large angle reorientation is also discussed.Simulation results illustrate that the control law drives the three axis attitudes along a shorter path to the target attutudes and damps out the vibration energy of the flexible appendages.

研究带两帆板航天器的三维再定向与振动抑制问题 ,执行机构为反作用轮。建立了柔性空间飞行器三轴耦合姿态动力学模型和四元数姿态运动学模型 ,建模时考虑了帆板的弯曲变形和扭转变形。采用拟欧拉角及角速度作为反馈信号 ,设计了一种PD控制律。该控制律可以用于对任意目标姿态的再定向而形式保持不变。用Lyapunov方法证明了姿态的渐近稳定性和模态振动的衰减性。非线性闭环系统的仿真结果验证了所设计控制律不仅能够使航天器完成对任意目标姿态的再定向 ,而且能够抑制帆板的弹性振动

 
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