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orbit target
相关语句
  相似匹配句对
     N TARGET
     命中目标
短句来源
     GUIDANCE ORBIT OF TARGET INTERCEPTING AND SIMULATION
     目标拦截的导引方法与仿真模拟
短句来源
     ISAR Echo Simulation and Imaging of the Target in Orbit
     轨道飞行目标的雷达回波模拟及成像
短句来源
     principle and target;
     原则和目标;
短句来源
     ORBIT OF LIGHT
     光的轨迹
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This paper summarizes and analyzes new development in flight simulation technique and it's application in the recent decennary. These new developments include: simulation computer, motion simulator in multidegree of freedom, whole-orbit target simulatior, artificial intelligence and virtual reality technique, etc. The applications inspacecrafts are: attitude control simulation in high-accurate long-life satellite, simulation of large flexible and multibody structure, simulation of RDV (Rendezvous and Docking),...

This paper summarizes and analyzes new development in flight simulation technique and it's application in the recent decennary. These new developments include: simulation computer, motion simulator in multidegree of freedom, whole-orbit target simulatior, artificial intelligence and virtual reality technique, etc. The applications inspacecrafts are: attitude control simulation in high-accurate long-life satellite, simulation of large flexible and multibody structure, simulation of RDV (Rendezvous and Docking), simulation of spacecraft reentry and real-time fault analysis and countermeasure.

本文综述和分析近十年来飞行仿真技术新的发展及其在航天器中的应用、这些新技术包括:仿真机,多自由度运动模拟器,全轨道目标模拟器,人工智能和虚拟现实技术等。在航天器具体应用方面包括:高精度长寿命卫星姿态控制仿真、挠性和多体的大型结构仿真、交会对接仿真、飞行器再入和实时故障分析和对策仿真等。

The full paper begins with a detailed analysis of the shortcomings of the traditional methods of orbit interception with finite thrust.We aim to overcome these shortcomings with GA.GA is an adaptive optimization technology.It has the advantages of general-utility,robustness and global optimization.In the full paper,we describe our GA method in detail;here we give only a briefing.In this paper,through building the mathematical model of orbit interception of the space flight vehicle with finite thrust,we...

The full paper begins with a detailed analysis of the shortcomings of the traditional methods of orbit interception with finite thrust.We aim to overcome these shortcomings with GA.GA is an adaptive optimization technology.It has the advantages of general-utility,robustness and global optimization.In the full paper,we describe our GA method in detail;here we give only a briefing.In this paper,through building the mathematical model of orbit interception of the space flight vehicle with finite thrust,we optimize the parameters of orbit interception with GA.In this study,we choose minimum fuel consumption as the optimization objective.In order to deal with the problem of orbit interception with many constraints,the penalty function is introduced into the GA.Then the GA's running parameters are adjusted dynamically for developing the convergence performance.In our simulation,we selected the thrust's direction,thrust's working time and the engine's fuel consumption rate as the parameters of GA optimization.Through the simulation of intercepting a Low-Earth-Orbit target,we found a minimum fuel consumption orbit under the constraints of a miss distance of 10 m.

遗传算法是一种具有通用性、鲁棒性及全局最优性等优点的自适应优化技术。文中建立了空间飞行器的有限推力轨道拦截数学模型,并以空间飞行器燃料消耗最小为优化目标函数,运用遗传算法对空间飞行器的拦截变轨参数进行了优化设计。为了解决轨道拦截这一多约束优化问题,在遗传算法中引入了罚函数方法,并通过动态改变算法参数来改进优化的收敛性。在对低地球轨道目标的拦截仿真中,选择发动机燃料质量秒耗量、推力作用方向和作用时间为优化参数,仿真结果证明了该方法在带约束有限推力轨道拦截优化中的有效性。

In certain time,orbit perturbation equations can be written in form of ordinary differential equations.Based on the perturbation equations,optimization of station keeping maneuver parameters can be described as a two point boundary value problem.The traditional way to solve this problem is to change it into initial value problem,and force the parameters to match the requirements in one boundary.In fact,this method has weakened constrains in the integral process,and the precision requirements of station-keeping.Compared...

In certain time,orbit perturbation equations can be written in form of ordinary differential equations.Based on the perturbation equations,optimization of station keeping maneuver parameters can be described as a two point boundary value problem.The traditional way to solve this problem is to change it into initial value problem,and force the parameters to match the requirements in one boundary.In fact,this method has weakened constrains in the integral process,and the precision requirements of station-keeping.Compared with the tradition method whose orbit targets a single right ascend node of a specified revolution,a "tight" manner strategy developed in this paper expands the targets to a set of checking points with respect to a predefined osculating reference trajectory in a number of revolutions.With this maneuver strategy,the satellite will be able to maintain precisely its orbit in an "error tube" as least as possible.

在指定时间内,轨道摄动方程的状态变化可以用柯西标准型的常微分方程表述。基于摄动方程,轨道的修正控制参数的计算问题可以表示为指定区间两点边值问题的参数优化问题。传统的参数计算方法本质上是将边值问题转化为初值问题,强制在一个边界点上满足边值条件,弱化了积分区域中的约束条件,造成不适应多约束条件下的轨道保持。基于基准轨道的多节点轨道控制方法在积分区域内的一组约束条件下,建立基于多约束条件方程的有限差分方程,与传统的升交点重合法相比,该算法将约束条件由目标圈目标升交点扩展到点火圈与目标圈之间所有圈的卫星位置参数约束,从而确定控制量将卫星轨道始终保持在偏差管道内,最大限度的满足对卫星轨道保持的要求。

 
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