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空间飞行器
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  spacecraft
    ANALYSIS OF STABILITY OF LQG MODAL CONTROL SYSTEMS FOR FLEXIBLE SPACECRAFT
    挠性空间飞行器LQG模态控制系统的稳定性分析
短句来源
    SOME PROBLEMS ON COMPUTER CONTROL OF FLEXIBLE SPACECRAFT
    挠性空间飞行器计算机控制的一些问题
短句来源
    VARIABLE STRUCTURE MODEL-FOLLOWING CONTROL OF SWITCHING ATTITUDE SYSTEM OF SPACECRAFT
    空间飞行器开关姿态系统的变结构模型跟随控制
短句来源
    Dynamics and Control Research of a Simulation Device for Flexible Spacecraft
    挠性空间飞行器仿真装置的动力学与控制研究
短句来源
    ON DYNAMIC FEEDBACK LINEARIZATION OF SPACECRAFT DYNAMICAL MODELS
    空间飞行器动力学模型的动态反馈线性化
短句来源
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  spacecrafts
    MULTIVARIABLE FREQUENCY DOMAIN DESIGN METHOD OF AUTOMATIC DOCKING CONTROL SYSTEM BETWEEN TWO SPACECRAFTS
    空间飞行器自动对接控制系统的多变量频域设计方法
短句来源
    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
    THE DEVELOPMENT AND PROSPECT OF FAILURE DIAGNOSIS TECHNIQUE FOR SPACECRAFTS
    空间飞行器故障诊断技术的发展和展望
短句来源
    Feature Extraction Algorithm for Spacecrafts Based-on Mathematical Morphology
    基于数学形态学的空间飞行器特征提取算法
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    Pursuit-evasion Barrier of Two Spacecrafts Based on the Sightline Coordinate System
    空间飞行器在视线坐标系中的追逃界栅
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  a spacecraft
    Nonlinear Attitude Tracking Control of a Spacecraft with Thrusters Based on Error Quaternions
    喷嘴为执行机构的空间飞行器基于误差四元数的非线性姿态跟踪控制(英文)
短句来源
    DOCKING DYNAMICS OF A SPACECRAFT
    空间飞行器对接动力学研究
短句来源
    The Research on High Attitude Tracking Maneuver of a Spacecraft
    空间飞行器大角度姿态跟踪机动问题研究
短句来源
    Mass Analysis of Condensation-free Walls in a Spacecraft.
    空间飞行器防结露舱壁的轻量化分析
短句来源
    The premature linearization in modeling dynamics of a spacecraft flexible appendage is discussed by using the conventional modeling method, and the method defects are demonstrated that some coupling terms between large overall motion and small deformation are lost.
    论述了采用传统动力学建模方法建立空间飞行器柔性附件动力学方程时过早线性化的问题,揭示了这种方法建立动力学方程的缺陷,即失去了一些重要的刚柔耦合项。
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  “空间飞行器”译为未确定词的双语例句
    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
    A Multivariable Reference Model Feedback Design Method for Automatic Docking System
    空间飞行器自动对接系统的多变量模型参考反馈设计方法
短句来源
    On Practical Compensation for GPS Multi-Path Effect for Space Users
    GPS多路径效应对空间飞行器的影响及补偿
短句来源
    APPLICATION OF GPS IN SPACE RENDEZVOUS AND DOCKING
    GPS在空间飞行器交会中的应用
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    Adaptive Structures——a Technology for Aerospace
    空间飞行器自适应结构技术
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  spacecraft
This collection can be used to test spacecraft production materials, in order to determine their resistance to biodegradation.
      
Studying Stability of the Flexible Spacecraft with a Discrete Control System
      
Stability of the spacecraft was considered with regard for its elastic structural oscillations arising under discrete control.
      
Consideration was given to the possibility of estimating jointly the motion coordinates and parameters of the elastic spacecraft using algorithms based on the discrete Kalman filtering and the theory of testing statistical hypotheses.
      
Design of the Suboptimal Profiled Relay Control of Orientation of the Spacecraft Having Elastic Structural Elements with Regard
      
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  spacecrafts
Anomalous effects in dopant distribution in Ge single crystals grown by the floating zone technique aboard spacecrafts
      
Specific features of Ga-dopant distribution in Ge single crystals grown by the floating zone technique from lightly and heavily Ga-doped Ge melts aboard the Photon spacecrafts have been studied.
      
The mechanisms of the MHD effect on the properties of the grown crystals are discussed as well as the perspectives of performing analogous experiments aboard spacecrafts.
      
Computed γ-ray numbers and spectra are consistent with those of terrestrial γ-ray flashes (TGFs) observed aboard spacecrafts.
      
Experimental studies of the response of midlatitude ionospheric D region to remote launches and flights of spacecrafts using par
      
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  a spacecraft
The variational problem to determine the optimal trajectories of the center of mass of a spacecraft moving in the central Newtonian field with limited power and specific momentum was considered.
      
Investigation of Conditions for Plane Autorotation of a Spacecraft Entering the Atmosphere
      
Determination of an Estimation of Parameters of Motion of a Spacecraft on the Stage of Its Descent on the Basis of Integration o
      
The Electric Potential of a Spacecraft Injecting an Electron Beam into the Earth's Ionosphere
      
The Use of Quaternions in the Optimal Control Problems of Motion of the Center of Mass of a Spacecraft in a Newtonian Gravitatio
      
更多          


In this paper, the fluit cycle and heat transfer process for an axially grooved heat pipe are analysed; and the performance test data for several extruded axially grooved aluminum alloy heat pipes, where ammonia, nitrogen, acetone were used as working fluids are also presented. The test data are compared with the theory prediction. The film coefficients of evaporator and condenser were measured. The empirical formula has been derived for the evaporator film coefficient of heat pipes where ammonia is used as...

In this paper, the fluit cycle and heat transfer process for an axially grooved heat pipe are analysed; and the performance test data for several extruded axially grooved aluminum alloy heat pipes, where ammonia, nitrogen, acetone were used as working fluids are also presented. The test data are compared with the theory prediction. The film coefficients of evaporator and condenser were measured. The empirical formula has been derived for the evaporator film coefficient of heat pipes where ammonia is used as working fluid. The heat pipe applications for spacecraft are described. The test performance for circumferentially grooved artery heat pipes and cold gas reservoir variable conductance heat pipe which consist of an axially grooved tube are briefly described. The engineering design method of VCHP was given.

本文对轴向槽道热管的流体循环及传热过程进行了分析,介绍了几种不同尺寸的挤压铝合金轴向槽道热管在以氨、氮、丙酮为工质时的性能试验数据,并与理论值进行了比较,测定了蒸发段及冷凝段膜系数,并导出了计算氨为工质时的蒸发段膜系数的经验公武,介绍了此种热管在空间飞行器上的应用情况,文中对周向槽道热管及轴向槽道管组成的冷贮气室可交热导热管的性能试验作了简单的论述,给出了可变热导热管的设计方法。

A Simple form unretarted orbit of space vehicles under the first order perturbation of the oblateness of the earth is obtained in this paper. A group of new canonical varables i s introduced first. With the construction of the perturbation equation of the intermediary, the first order solution is derived conveniently. As an application example of the theory, Lambert's algrithm is generalized to include the oblateness effeacts. At last, for ballistic vehicle, the result of this paper is compared with that of...

A Simple form unretarted orbit of space vehicles under the first order perturbation of the oblateness of the earth is obtained in this paper. A group of new canonical varables i s introduced first. With the construction of the perturbation equation of the intermediary, the first order solution is derived conveniently. As an application example of the theory, Lambert's algrithm is generalized to include the oblateness effeacts. At last, for ballistic vehicle, the result of this paper is compared with that of numerical integration and calculated result of two-body orbit. The comparison indicates that the accuracy in this paper ishigher.The theory of the present paper has no orbit inclination limitation, and it includes all first order terms. It may be used in guidance, onboard orbit computation, and short term forecast of satellite orbit.

本文求得了空间飞行器在地球扁率摄动作用下简单形式的一阶解。首先引入了一组由轨道根数与坐标组成的新的正则变量,求出了中间轨道,建立起中间轨道的正则摄动方程,进而求出了一阶解。作为应用举例,将Lambert定理推广到包含扁率一阶摄动的情形。最后就弹道飞行器轨道,将本文结果与数值积分和二体轨道计算结果进行了比较,表明本文结果有较高精度。 本文结果无轨道倾角限制,包含了全部一阶摄动作用。可直接用于制导,实时轨道计算,卫星轨道短期预报等。

In this paper the dynamics and the control problem of flexible spacecraft with solar arrays are investigated. A mathematical model is built by partial differential equaions and the finite element method, Then the transfer function is derived through the finding of eigenvalues and modal gains of the system,After that a PID controller is designed, and the reduction of the high order of the mathematical model is discussed, Finally an optimization method—the Powell method—is used for the controller, and a numerical...

In this paper the dynamics and the control problem of flexible spacecraft with solar arrays are investigated. A mathematical model is built by partial differential equaions and the finite element method, Then the transfer function is derived through the finding of eigenvalues and modal gains of the system,After that a PID controller is designed, and the reduction of the high order of the mathematical model is discussed, Finally an optimization method—the Powell method—is used for the controller, and a numerical example is given. Accordingly some useful conclusions are drawn from the investigation.

本文研究具有太阳帆板的挠性空间飞行器的动力学与控制问题。对于用偏微分方程或有限元法建立的数学模型,通过求取系统的特征值和模态增益,给出其传递函数,然后设计了具有比例—微分—积分形式的控制器,并进行了稳定性分析。初步探讨了高阶数字模型的降阶问题。最后,应用最优化方法申的Powell方法,对控制器参数进行了最优化设计,并给出了一个计算实例。从而得到一些有益的结论。

 
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