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空间飞行器姿态
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  spacecraft attitude
     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
     Design and Simulation of Spacecraft Attitude Controller
     空间飞行器姿态控制器设计与仿真
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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
     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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     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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  “空间飞行器姿态”译为未确定词的双语例句
     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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     Star Identification Algorithms and the Aerocraft Attitude Determination Research
     星图识别算法及空间飞行器姿态确定研究
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     The star sensor is a measuring unit used for providing information to the attitude control system on spacecraft .
     星敏感器是为空间飞行器姿态控制系统提供姿态信息的测量系统。
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
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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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  相似匹配句对
     ATTITUDE IDENTIFICATION OF SPACECRAFT
     空间飞行器姿态识别
短句来源
     Spacecraft Attitude Control Based on Quaternion
     基于四元数的空间飞行器姿态控制
     THE POSTURE OF READING
     阅读的姿态
短句来源
     An Attitude to Literary Writing
     写作的姿态
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     The Property of the Technology of Spacecraft Failure Diagnosis
     空间飞行器故障诊断技术的特点
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  spacecraft attitude
Spherical goniometry and spacecraft attitude determination
      
Redundancy of the system with respect to the number of task variables for spacecraft attitude and manipulator end-effector pose is considered.
      
Also, the problem of both spacecraft attitude and end-effector orientation representation is tackled by means of a non-minimal singularity-free representation: the unit quaternion.
      
Marginalized particle filter for spacecraft attitude estimation from vector measurements
      
An algorithm based on the marginalized particle filters (MPF) is given in details in this paper to solve the spacecraft attitude estimation problem: attitude and gyro bias estimation using the biased gyro and vector observations.
      
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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 attitude dynamic equations of spacecraft with a central rigid body and P flexible appendages are derived. Expanding these equations in series by both unconstrained and constrained mode shape functions the state equations in time domain and the inverse transfer function matrix, defined as the relation of augmented attitude angle matrix to control forces or moments in frequency domain are obtained. The relative motion of flexible appendages to central rigid body are considered, too, in derivation. This paper...

The attitude dynamic equations of spacecraft with a central rigid body and P flexible appendages are derived. Expanding these equations in series by both unconstrained and constrained mode shape functions the state equations in time domain and the inverse transfer function matrix, defined as the relation of augmented attitude angle matrix to control forces or moments in frequency domain are obtained. The relative motion of flexible appendages to central rigid body are considered, too, in derivation. This paper gives also two modal identities, one of which can be regarded as the criteria for trunction of higher order equations obtained when the attitude control system is being analyzed.

本文给出了具有中心刚体和P个挠性附件的空间飞行器姿态动力学方程式,并用约束和非约束两种模态展开,得到时域求解的状态方程式和频域中的增广姿态角对控制力矩的逆传递函数阵。推导中考虑了挠性附件对中心刚体的相对运动。本文还给出了两种模态恒等式,其中之一可用来做控制系统分析时截断高阶方程式的截断准则。

 
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