orbit transfer

Optimization of system and mission ( orbit transfer and north-south station keeping) based on genetic algorithm ( GA) about GEO satellite using Arcjet propulsion sysytem has been probed.

采用遗传算法（GA）对Arcjet用于GEO卫星的变轨与南北位置保持（NSSK）进行了任务和系统优化计算分析。

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The numerical simulation of satellite orbit transfer is implemented.

针对某一卫星轨道转移进行了数字仿真。

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Optimal Control for Minimizing Energy or Fuel in Finite-thrust Orbit Transfer

有限推力能量、燃料最优轨道转移控制

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At last, engineering method of impulse orbit transfer of constellation is discussed, and further references for project application and study are given.

最后，探讨了星座脉冲式变轨的工程实现途径，为工程应用和研究提供参考。

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Automatic Fast Orbit Transfer Control Based on Model Prediction

基于模型预测的轨道自主快速大机动控制

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Reliable on-board launch ability is the precondition of executing the task of OTV ( Orbit Transfer Vehicle), which is a maneuvering platform.

OTV作为一种空间机动平台，可靠的在轨发射能力是实现其任务使命的重要前提条件。

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Optimal time control of low-thrust orbit transfer for making three-statellite constellation

形成三星星座的小推力变轨的时间最短控制

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The optimal control equations based on kinematic variables can get its analytic solution of space orbit transfer and can get the analytic solution when considering the Earth's oblateness.

采用运动学变量建立的最优控制方程可以得到空间转移轨道的解析解，且在考虑地球扁率摄动时也能得到解析解。

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An Orbit Transfer Method for Concomitant Satellite Approaching and Flying-around

伴随卫星接近绕飞的轨道控制方法研究

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As a result, the research of constrained optimal orbit transfer is of great significance and many researchers put their attention on orbits maneuvers with constraints.

因此有约束的轨道机动问题成为了众多学者关心的问题，有着极其重要的研究价值。

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In view of the uncertainty of thrust acceleration, enormous error occurs in tracking and navigating maneuvering target during orbit transfer process.

轨道机动控制过程中，推力加速度的不确定性是机动目标运动的主项摄动。

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When launching constellation, because of the limit of rocket launching accuracy, satellites can not be launched with rocket to make constellation, orbit transfer is necessary.

该文针对三星星座，进行星座发射中的最优脉冲式变轨研究。

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After constructing the model of motion of the target and the kinetic kill vehicle ( KKV), constraints of interception were analyzed and the computing method of orbit transfer was also derived.

针对拦截器对抗多目标攻击的特点，建立了对抗多目标的大气层外动能拦截器末制导仿真模型，并对仿真模型进行了验模分析和仿真计算。

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In the paper, considering three satellite constellation, optimal time control of orbit transfer with constant value, continue working and Newton grade thrust is studied, by means of Minimum Principle in optimal control theory.

本文针对形成三星星座，利用最优控制中的极小值原理，解算了用恒值、连续工作、牛顿级小推力变轨的时间最短控制问题。

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Research of Long-range Orbit Transfer for Space Based Anti-satellite Weapon

一种天基反卫星武器远程变轨方法研究

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Discussion on orbit transfer by a single impulse

关于脉冲式轨道改变的讨论

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Based on relative motion equation of satellite state transferring, analytic solution of two impulse orbit transfer of constellation is derived, which is analytic equation of impulse control variable.

基于卫星相对运动状态转移方程，推导出了星座双脉冲式变轨的理论解，即所要施加的脉冲控制量的解析式；

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The Retarding Effect of An Orbit Transfer by A Single Impulse

卫星脉冲变轨的延迟效应

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In the normal case, the homing orbit transfer is carried out autonomously by using the device on the spacecraft.

正常情况下，寻的段是依靠追踪航天器上的自主设备实现自主变轨。

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By means of genetic algorithm, control variables of two impulse orbit transfer are optimized, and optimal time of orbit transfer to minimize total impulse is got.

利用遗传算法，对双脉冲式变轨的脉冲控制量进行了优化计算，求得了使总变轨脉冲最小的最优变轨时间。

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In this case, the study of orbit transfer insertion error becomes very complicated.

在这种情况下，轨道转移入轨误差的研究变得较为复杂。

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Robust Attitude Control of Flexible Liquid Spacecraft under Fast Orbit Transfer

轨道快速机动期间的姿态鲁棒稳定控制方法研究

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RQP Based Finite Thrust Apogee Orbit Transfer with Minimum Fuel

基于递推二次规划算法的燃料最优有限推力远地点变轨

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However, failure may occur during the autonomous orbit transfer.

然而自主变轨有时可能发生故障，称为自主故障。

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When the failure occurs, the orbit transfer task has to be accomplished by the engineers on land with the help of grand devices.

当发生自主故障时，需要转由地面继续完成变轨任务。

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Application and analysis of formation satellites cluster orbit transfer based on genetic algorithm

遗传算法在编队卫星群轨道机动中的应用分析

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Finite multiple burn orbit transfer error analysis via covariance matrix

利用协方差矩阵研究有限多次点火时轨道转移误差

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A study of minimum-fuel coplanar orbit transfer with a fixed thrust

最少燃料消耗的固定推力共面轨道变轨研究

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Optimum Orbit Transfer and Rendezvous of Spacecraft

航天器轨道转移与交会最优控制研究

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Simulation results are employed to illustrate that the algorithm developed here can track and position maneuvering target in real time during orbit transfer process.

给出了扩展卡尔曼滤波实时估计增广状态向量的算法，仿真分析证明所述算法稳定、收敛，对机动目标具有较高的定位精度。

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