助手标题  
全文文献 工具书 数字 学术定义 翻译助手 学术趋势 更多
查询帮助
意见反馈
   动量管理 的翻译结果: 查询用时:0.352秒
图标索引 在分类学科中查询
所有学科
航空航天科学与工程
更多类别查询

图标索引 历史查询
 

动量管理
相关语句
  momentum management
     Rejection of Cyclic Disturbances for Attitude Control/ Momentum Management System in Space Station
     空间站姿态控制/动量管理系统的周期性扰动抑制
     Nonlinear Approach to Attitude Control and Momentum Management for Space Station
     空间站姿态控制/动量管理的非线性方法
     Adaptive approach to attitude control and momentum management of space station
     空间站姿态控制/动量管理的自适应方法
     Nonlinear strategy can be used in the attitude control/momentum management system of space station since it is nonlinear in essence.
     空间站姿态控制/动量管理系统是一个本质非线性系统,可采用非线性的策略进行控制。
     Therefore, a new nonlinear controller is designed for the extended attitude control/momentum management system after a cyclic-disturbance rejection filter is introduced according to Lyapunov stability theory.
     为此,本文引入了周期性扰动滤波器,根据Lyapunov稳定性理论,对扩展后的姿态控制/动量管理系统设计了新的非线性控制器。
更多       
  “动量管理”译为未确定词的双语例句
     Simulation results of a certain space station indicate that the controller presented above is feasible.
     对空间站姿态控制/动量管理系统的仿真结果表明,该控制器是可行的。
短句来源
     Simulation results of a certain space station indicate that the controller presented above is feasible.
     对空间站姿态控制/动量管理系统的仿真结果表明,上述控制策略是可行的。
     Simulation results of a certain space station indicate that the presented controller is feasible.
     对空间站姿态控制/动量管理系统的仿真结果表明,上述控制策略是可行的.
  相似匹配句对
     The Research on Attitude Control and Momentum Management of the Space Station
     空间站姿态控制和动量管理研究
短句来源
     PHILOSOPHY OF MANAGEMENT
     管理的哲理
短句来源
     global management;
     全球化管理;
短句来源
     Adaptive approach to attitude control and momentum management of space station
     空间站姿态控制/动量管理的自适应方法
查询“动量管理”译词为用户自定义的双语例句

    我想查看译文中含有:的双语例句
例句
为了更好的帮助您理解掌握查询词或其译词在地道英语中的实际用法,我们为您准备了出自英文原文的大量英语例句,供您参考。
  momentum management
On-board autonomous momentum management during cruise relieves Mission Operations from planning, scheduling, and carrying out many manual momentum dumps.
      
Magnetometers and torque rods with redundant windings are used for wheel momentum management.
      
Six 4.4 N thrusters and two 22.2 N thrusters achieve high-acceleration slews, momentum management, and delta-V maneuver pointing control.
      
This is because of the complexity of the momentum management process caused by the EO-1 configuration of three reaction wheels rather than four.
      
The momentum management function generates current commands to the electromagnets based upon a specified momentum management criterion.
      


Single Gimble Control Moment Gyro (SGCMG) is a momentum exchange device of spacecraft, which is suitable for three-axis attitude control and quick movement of large spacecraft. To establish attitude control and momentum management system for large spacecraft by use of SGCMG is one of the items of spacecraft development in our country. Mechanical environment where spacecraft disturbance torque is very small in out space is simulated making use of a three-axis full physics air-bearing table as controlled object....

Single Gimble Control Moment Gyro (SGCMG) is a momentum exchange device of spacecraft, which is suitable for three-axis attitude control and quick movement of large spacecraft. To establish attitude control and momentum management system for large spacecraft by use of SGCMG is one of the items of spacecraft development in our country. Mechanical environment where spacecraft disturbance torque is very small in out space is simulated making use of a three-axis full physics air-bearing table as controlled object. SGCMG attitude control and momentum management system is arranged on the table. The simulation loop functions as the same as the spacecraft control system. With this simulation system, problems as dynamics, momentum exchange, momentum coupling, etc. in the control system were investigated. The experiment proved that this simulation system is capable of simulating space mechanical environment and lays foundations for the research with SGCMG system.

单框架控制力矩陀螺(SGCMG)是一种重要的航天器动量交换装置。用SGCMG作姿控部件的大型航天器姿态控制/动量管理系统是我国未来航天器发展的一个重点研究问题。本文利用三轴全物理仿真气浮台作为控制对象,模拟航天器在外层空间所受扰动力矩很小的力学环境。把SGCMG姿态控制/动量管理系统置于气浮台上,组成与航天器控制系统相同的仿真回路,来研究其动力学、动量交换、动量耦合以及控制系统中尚不清楚的一些问题。实践证明该仿真系统能够很好模拟航天器的力学环境,为SGCMG系统的进一步研究打下了很好的基础。

The physics simulation of large spacecraft Single Gimble Control Moment Gyro attitude control and momentum management system was established, making use of three-axis air-bearing table as spacecraft dynamics simulation object. The mathematics model of SGCMG attitude control and momentum management system was deduced. The physics simulation system was designed and debugged. The problem of SGCMG singularity avoidance, steering law in the condition of SGCMG failure, optimization of momentum management was studied....

The physics simulation of large spacecraft Single Gimble Control Moment Gyro attitude control and momentum management system was established, making use of three-axis air-bearing table as spacecraft dynamics simulation object. The mathematics model of SGCMG attitude control and momentum management system was deduced. The physics simulation system was designed and debugged. The problem of SGCMG singularity avoidance, steering law in the condition of SGCMG failure, optimization of momentum management was studied. The experiment proves system configuration and singularity analysis, steering law design is correct. According to simulation of large spacecraft SGCMG attitude control and momentum management system, The design scenario is valid and the hardware and software of system is reliable.

利用三轴气浮台模拟航天器空间力学环境,进行了单框架控制力矩陀螺(SGCMG)姿态控制/动量管理系统全实物仿真研究。推导了大型航天器姿态控制/动量管理系统数学模型。设计调试了实物仿真系统。研究了单框架控制力矩陀螺奇异回避问题、失效操纵问题和动量管理优化问题。证明了系统构形分析、奇异性分析和操纵律设计的正确性和有效性。通过大型航天器姿态控制/动量管理系统实物仿真,检验了设计方案的可行性和系统硬、软件的可靠性。

Inner moment arisen by control moment gyro (CMG) during attitude control process of space station will cause redistributing and adjusting of angle momentum. This will result in saturation of angle momentum due to accumulation of angle momentum of CMG with time passing. Based on the linearized model of attitude control and momentum management (ACMM),control systems without considering and considering disturbance restrains are constructed respectively. Using internal model control technique actualizes the external...

Inner moment arisen by control moment gyro (CMG) during attitude control process of space station will cause redistributing and adjusting of angle momentum. This will result in saturation of angle momentum due to accumulation of angle momentum of CMG with time passing. Based on the linearized model of attitude control and momentum management (ACMM),control systems without considering and considering disturbance restrains are constructed respectively. Using internal model control technique actualizes the external disturbance torque restrain. Finally, simulation proves its validity.

空间站在利用控制力矩陀螺 (CMG)进行姿态控制的过程中 ,由CMG产生的内力矩使空间站角动量重新调整分配 ,会引起控制力矩陀螺角动量随时间的累积 ,从而导致角动量的饱和。本文在空间站姿态控制与动量管理 (ACMM )线性化模型基础上 ,首先建立了不考虑扰动抑制下的控制系统稳定模型 ,其次分析了考虑扰动抑制下的控制器设计 ,引入线性系统有关理论 ,利用内模原理实现对扰动抑制的鲁棒控制 ,最后通过仿真验证了系统的有效性

 
<< 更多相关文摘    
图标索引 相关查询

 


 
CNKI小工具
在英文学术搜索中查有关动量管理的内容
在知识搜索中查有关动量管理的内容
在数字搜索中查有关动量管理的内容
在概念知识元中查有关动量管理的内容
在学术趋势中查有关动量管理的内容
 
 

CNKI主页设CNKI翻译助手为主页 | 收藏CNKI翻译助手 | 广告服务 | 英文学术搜索
版权图标  2008 CNKI-中国知网
京ICP证040431号 互联网出版许可证 新出网证(京)字008号
北京市公安局海淀分局 备案号:110 1081725
版权图标 2008中国知网(cnki) 中国学术期刊(光盘版)电子杂志社