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空间飞行器
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  spacecraft
     This paper discusses the technology for the SPF of the TB2(Ti-5Mo-5V-8Cr-3Al) titanium alloy in corrugated plate (t=0.25mm) anelement of spacecraft structure. The paper includes the discussion of theparameters of forming process and experimental equipment.
     论述了TB2(Ti-5Mo-5V-8Cr-3Al)钛合金的超塑性成形在空间飞行器结构件—波纹板(厚0.25mm)制造上的应用技术,内容包括成形工艺参数和试验装置。
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     Spacecraft Integrated Attitude Determination Based on GPS/IMU/Sun Sensor
     基于GPS/IMU/太阳敏感器的空间飞行器组合姿态确定
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     Working on the spacecraft simulation system and its user interface, mainly on orbit dynamics model and its implementation.
     参加空间飞行器总体仿真系统及其演示环境系统设计实现工作,主要进行轨道动力学建模、轨道动力学模块的实现工作。
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     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
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     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
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  spacecrafts
     CO_2 coherent laser radar sensor for the rendezvous and docking of two spacecrafts
     用于空间飞行器交会对接的CO_2相干激光雷达
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     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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     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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     The simulation results show that under the noise level of 0.03 pixels error the calibration accuracy of 1 arc-second can be obtained by the scheme and it can meet the demand of high-accuracy attitude-measurement of modern space spacecrafts.
     仿真结果表明在 0.03 像素误差的噪声水平下该方案能够达到 1″精度,可以满足现代空间飞行器的高精度姿态测量要求。
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     To solve the nonlinear attitude control problem of a class of spacecrafts, the strongly coupled dynamics model is decomposed into some subsystems and the coupling between the subsystems, unmodelled dynamics and exterior disturbances are regarded as the uncertainty of the system.
     针对一类空间飞行器的非线性姿态控制问题 ,首先通过变换将其强耦合模型分解成若干个子系统 ,把各子系统之间的耦合、未建模动态和外界扰动视为系统的不确定性。
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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)
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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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     A spacecraft attitude control problem is given to demonstrate the effectiveness of the method.
     将本文结论应用于一空间飞行器的姿态跟踪控制问题 ,仿真结果表明了该设计方法的有效性
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     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
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     However, launching a spacecraft is a high-cost, high-risk venture.
     然而,空间飞行器的发射是一项高投入、高风险的任务。
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  “空间飞行器”译为未确定词的双语例句
     Nonlinear Trajectory Tracking Control of Under-actuated VTOL Aircraft
     欠驱动VTOL空间飞行器系统的非线性跟踪控制
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     The dynamic fault diagnosis and process of a sensor on the tracing vehicle in the rendezvous docking of two aerocrafts are discussed based on filtering especially in the case of small maximum maneuver index.
     针对两个空间飞行器交会对接过程中追踪飞行器上的各单个测量传感器,探讨了其基于滤波方法的动态过程故障诊断及相应的处理,并特别针对目标相对于传感器的最大机动指数较低的情况,分析了相应的故障诊断及处理方法。
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
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     Analysis of Flexible Test and Launch Technology of Near Space Aerocraft
     近空间飞行器机动发射及测试技术分析
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     Unscented Kalman Filter for Bearing-only Ranging of Space Targets
     Unscented Kalman滤波在空间飞行器被动测距中的应用
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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
      
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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。

Similarity criteria for thermal scale modeling of spacecraft with radiation-conduction system is presented briefly. Design, construction and tests for thermal scale models of three satellites with passive thermal control are reported. The results of the tests are compared with prototypes. The results showed that thermal scale modeling may be one of the mediums of spacecraft thermal design. It can decreases the amount of work of thermal analysis and thermal vacuum test of prototype, so that the developing period...

Similarity criteria for thermal scale modeling of spacecraft with radiation-conduction system is presented briefly. Design, construction and tests for thermal scale models of three satellites with passive thermal control are reported. The results of the tests are compared with prototypes. The results showed that thermal scale modeling may be one of the mediums of spacecraft thermal design. It can decreases the amount of work of thermal analysis and thermal vacuum test of prototype, so that the developing period and cost of satellite will be reduced.

简要介绍了辐射-导热系统空间飞行器热比例模化的相似准则.报道了使用被动温控方式的三个人造地球卫星热比例模型的设计、制作和实验;实验结果与原型进行了比较.其结果表明:热比例模型工作可以作为空间飞行器热设计的一种手段,以减少热分析和原型热真空实验的工作量,从而降低研制成本,缩短研制周期.

In this paper it is proposed that space electronics covers the fields of radio electronic technics for the tracking and control of the artificial satillites and spacecrafts, for the observation of the earth by satellites, for the exploration of deep space, for satellite communications and broadcasting, and for the uti-lization of satellites for position fixing of moving objects. Some outstanding achievements of space electronic systems are cited in this paper, and the features special to space-electronics are...

In this paper it is proposed that space electronics covers the fields of radio electronic technics for the tracking and control of the artificial satillites and spacecrafts, for the observation of the earth by satellites, for the exploration of deep space, for satellite communications and broadcasting, and for the uti-lization of satellites for position fixing of moving objects. Some outstanding achievements of space electronic systems are cited in this paper, and the features special to space-electronics are stated and analysed. The development of space-electronics in our country is briefly described. Finally the future prospects of space electronics are concisely discussed.

本文把空间电子学归纳为对卫星和空间飞行器实现跟踪控制,利用卫星观测地球、深空探测、卫星通信广播以及利用卫星对地球上运动物体的定位等方面的无线电电子技术。文中举出了一些近年来较为突出的空间电子系统的成就,分析了空间电子学的特点,还简略地介绍了我国的发展概况。最后简要地展望了未来的发展。

 
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