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    A VARIABLE STRUCTURE CONTROL APPROACH TO FLEXIBLE SPACECRAFTS
    柔性空间飞行器的变结构控制
    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
    The Vibration Suppression Control of Flexible Spacecrafts
    柔性空间飞行器的振动抑止控制
    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
    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
    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
    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
    Because the second generation star sensor has no attitude accumulation error, high pointing accuracy, fast fault-comeback ability, and completely self-determination guidance capability, it draws lots of attention. It is becoming the prior choice of the attitude measurement instruments for the current spacecrafts and the future ones.
    第二代CCD星敏感器由于无姿态累计误差、指向精度高、快速的故障恢复能力和具有完全自主的导航能力而受到人们的关注,成为当前和未来空间飞行器的首选姿态测量仪器。
    Since 1950s, VSC was increasingly applied into many industrial domains, such as motors and power systems, spacecrafts, robots, chemical engineering and so forth.
    从50年代产生至今,变结构控制越来越多地被应用到电机与电力系统、空间飞行器、机器人、化工等领域。
    Then, for Remote Agent in "Deep Space One", which is the first intelligent autonomous control system operating in the spacecrafts, the configuration, function, system architecture and realization of Remote Agent are analyzed and discussed respectively. The fundamental ideas, the technology points to be solved, and the concerned realization for the intelligent autonomous control of spacecraft and its propulsion system are obtained and summarized.
    随后,针对“Remote Agent”智能自治控制系统,通过对其结构、功能、系统构成和应用实现等方面的剖析,总结出对空间飞行器及推进系统进行智能自治控制的基本思路、需要解决的技术难点及其相关的实现问题。
    Now, flywheels systems are elected as the actuators of attitude control system with high precision for most spacecrafts.
    目前空间飞行器的高精度姿态控制系统大多采用飞轮系统。
    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.
    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。
    In this paper the approach of variable structure control strategy (VSCS) is applied to the control problems of large flexible spacecrafts taking the nonlinear forces into consideration.
    本文研究了大型柔性结构空间飞行器的控制问题。
    This paper gives a multivariable reference model feedback design method for automatic docking system of two spacecrafts using the multivariable frequency domain theory, starting from the flight characteristics of the final approach phase during RVD between two spacecrafts in space.
    本文从两空间飞行器交会对接过程最后接近阶段的飞行特性出发,利用多变量频域理论,给出了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.
    The natural space radiation environment and the basic mechanisms of radiation effects are two most important issues relating to the research of radiation hardening techonology of spacecrafts. In this paper, some of the general properties of natural space radiation environment are summerized, the basic mechanisms of radiation effects are anylized briefly, and the emphasis of present research relating to the radiation hardening techonology of spacecrafts is pointed out.
    天然空间辐射环境与辐射效应基本机制是空间飞行器抗辐射加固研究中的两个关键问题, 本文总结了天然空间辐射环境的总体性质, 并对辐射效应基本机制进行了简要的分析, 指出了目前空间飞行器抗辐射加固研究的重点。
    In the light of more and more titanium alloy material being used to produce important components of spacecrafts and problems existing in traditional jointing process,a fully shielded welding equipment has been developed.
    针对空间飞行器越来越广泛地使用钛合金材料及材料在传统焊接加工中存在的问题,研制了惰性气体整体保护焊接设备。
    First, the feedback Linearization problem is solved to the given system by the differential geometry method . Then, the variable structure control with sliding modes is designed to guarantee the existence of stable sliding modes, which the output tracking to a giver motion is achieved. Finally, the method is applied to the problem of attitude tracking control of spacecrafts.
    首先利用微分几何方法对给定系统进行反馈线性化处理,然后设计滑模变结构控制,以保证系统存在稳定的滑动模态,实现对给定运动的输出跟踪,最后将本文方法应用于空间飞行器的姿态跟踪控制问题,仿真结果证实了方法的有效性.
    This paper deals with the large angle attitude maneuver control of spacecrafts.
    本文研究空间飞行器大角度姿态机动的控制问题。
    Because of violent temperature variations on the external surface of spacecrafts,the structural assembly exposed in space has a lot thermal deformation so that the pointing accuracy of the sensors mounted the assembly will drop evidently.
    外热流环境的变化会引起空间飞行器表面温度的剧烈变动 ,使裸露在外空间的结构组件产生较大的热变形 ,从而影响结构及相关敏感器的指向精度。
    When used in spacecrafts, carbon fiber/epoxy resin is affected severely by many factors of space environment, especially the atomic oxygen effect. Experiments were constructed to investigate the atomic oxygen erosion effect of this material with a ground based simulation facility, and as a function of temperature change.
    碳纤维 /环氧树脂用在空间飞行器上时 ,面临着空间环境中各种因素特别是原子氧效应的影响 ,因而在地面模拟设备中对这种材料进行了原子氧剥蚀效应试验研究 ,并且考察了温度变化的影响 .
 

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