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飞行模式
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  flight mode
     This paper designs an attitude decoupling control law for small satellite in large-angle biased flight mode about roll axis of zero-momentum system via reaction wheels.
     研究了采用反作用飞轮为执行机构的整星零动量卫星绕X轴大角度偏置飞行模式的姿态解耦控制问题。
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     This filter can be used in navi gation, antenna tracking, and telemetry data processing systems to improve the l ocating accuracy and to realize the flight mode auto judgment.
     本方法可用于导航控制、天线跟踪和遥测数据处理等系统中 ,可以提高定位的准确性 ,并进行飞行模式的自动判决
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  fly modes
     The hardware architecture of the attitude control system,the fly modes of satellite and their control strategy,the architecture and layout design of the satellite keeping system,the interface of the attitude control system and the satellite keeping system are discussed here.
     对姿控系统的硬件组成、卫星的飞行模式和控制策略、星务管理软件的体系结构和总体设计思想、姿控软件和星务管理软件的接口设计等内容做了重点讨论。
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  “飞行模式”译为未确定词的双语例句
     At last ,RD and BP algorithm application characteristics in Bistatic SAR are discussed and the simulation experiments under parallel model were taken.
     最后研究了在双站平行飞行模式下的RD算法及BP算法,并用该算法进行了点目标仿真,分析了这两种算法在双站SAR成像中的应用特点。
短句来源
     In this paper, the multi-target data fusion system based on radar network is studied, and two algorithms of data association, i.e. Nearest neighbor and PDA, respectively for the centralized processing and distributed processing of data fusion system are analyzed. The simulations prove the effectiveness of these algorithms.
     研究了多目标情况下的雷达组网数据融合问题 ,讨论了数据关联的最近邻法和概率数据关联 (PDA)这两种算法 ,针对雷达组网数据融合的分布式与集中式两种系统结构分别提出了一种算法 ,并同时应用数据关联和数据融合算法针对 4个目标的平行编队、交叉飞行、平行转弯飞行模式进行了蒙特卡罗仿真 ,证明了算法的有效性。
短句来源
     Flight path data was loaded on spot, and the flight orbit was revised in real time, remote measurement and control signal was sent out.
     现场装定飞行模式航迹数据,实时修正飞行轨迹,定时发送遥测、控制信号。
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     The effect of aircraft-to-sonobuoy range, the frequency of measurement, and changes in altitude are also analyzed.
     仿真表明,对于给定的飞行模式和飞机参数,该算法可以成功地估计浮标的位置,并且分析了飞机与浮标的距离、测量频率和飞行高度对定位的影响。
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     Then the first modal vibration of the system was selected by cross feedback,and the flapping-wing micro air vehicle realized different flying modes by adjusting system parameters.
     在此基础上,利用交叉反馈选择出系统的第一阶模态振动,并调节各参数使扑翼飞行器实现不同的飞行模式
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  相似匹配句对
     S Mode Transponders Enter into Application Stage
     S模式应答机在飞行中的应用
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     Normal Mode
     简正模式
短句来源
     Software Pattern Reuse
     模式复用
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     The Flying Box
     飞行的箱子
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     Fly in Midnight
     午夜飞行
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  flight mode
Inertial Flight Mode and Semiconductor Segregation Patterns
      
In this work, a 2D time-dependent Bridgman model has been used to analyze the impact of the inertial flight mode on the resulting crystal dopant homogeneity.
      
BRIMS is designed to produce data spanning a Q range from 0.0025 to 0.7??-1 in a single measurement by simultaneously using neutrons with wavelengths from 1 to 14.5?? in a time-of-flight mode.
      
The intriguing question of relating the processes of natural selection for a given species in evolving a particular wing shape and flight mode that must be conducive to its continued survival remains open for much further research and study.
      
Although the system behav ior is predicted more precisely using the modified wire equation, it has only minor effects in the free-flight mode.
      
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  fly modes
The top down 2D view and fly modes may promote the user to see the big picture and learn to see the whole environment.
      


This paper designs an attitude decoupling control law for small satellite in large-angle biased flight mode about roll axis of zero-momentum system via reaction wheels.Attitude kinematics equations and dynamics equations are established firstly in this paper,then a nonlinear item is introduced in the controller to linearize the attitude dynamics equations, and then a state feedback decoupling law and a pole assignment law are designed for the linearized model.At last,a numerical simulation example is given.

研究了采用反作用飞轮为执行机构的整星零动量卫星绕X轴大角度偏置飞行模式的姿态解耦控制问题。首先给出卫星姿态运动学和动力学模型,然后在控制作用中引入非线性项对姿态动力学模型线性化,进一步对线性模型进行状态反馈解耦和极点配置。最后,给出了数学仿真算例和仿真结果。

An integrative design of attitude control and satellite keeping system are introduced.In this case,the number of on board computers can be reduced,the real time characteristic of the information process can be enhanced,and the advantage of the light,small and low cost of the small satellite can also be realized.The hardware architecture of the attitude control system,the fly modes of satellite and their control strategy,the architecture and layout design of the satellite keeping system,the interface of the attitude...

An integrative design of attitude control and satellite keeping system are introduced.In this case,the number of on board computers can be reduced,the real time characteristic of the information process can be enhanced,and the advantage of the light,small and low cost of the small satellite can also be realized.The hardware architecture of the attitude control system,the fly modes of satellite and their control strategy,the architecture and layout design of the satellite keeping system,the interface of the attitude control system and the satellite keeping system are discussed here.

介绍一种将姿控系统和星务管理系统融为一体的设计思想 ,它节约了星载机资源 ,提高了系统信息处理的实时性 ,很好地体现了小卫星的质量轻、体积小、成本低的优势。对姿控系统的硬件组成、卫星的飞行模式和控制策略、星务管理软件的体系结构和总体设计思想、姿控软件和星务管理软件的接口设计等内容做了重点讨论。

This paper deals with gyro less attitude determination algorithms using data from continuously running magnetometers, earth sensors and sun sensors for three axis stabilized satellite during normal operation. Based on EKF technique, an attitude estimator is designed which adopts the quaternion representation and Gauss Markov process. Simulation results show that precise attitude estimation or correction to satisfy with the need of control resolution of satellites can be achieved using the attitude determination...

This paper deals with gyro less attitude determination algorithms using data from continuously running magnetometers, earth sensors and sun sensors for three axis stabilized satellite during normal operation. Based on EKF technique, an attitude estimator is designed which adopts the quaternion representation and Gauss Markov process. Simulation results show that precise attitude estimation or correction to satisfy with the need of control resolution of satellites can be achieved using the attitude determination algorithm derived in this paper.

针对三轴稳定卫星进行了正常飞行模式下无陀螺姿态确定算法研究 ,采用磁强计、地球敏感器和太阳敏感器组合获得姿态数据 ,利用四元数法和高斯 -马尔可夫过程建立了姿态确定估计器算法模型。通过数学仿真证明 ,此姿态确定算法能够对星体姿态进行较精确的估计或校正 ,满足卫星控制精度要求。

 
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