地月转移轨道

月球探测器地月转移轨道测控技术仿真研究

A Simulation Research on Measurement and Control Technology of Earth-Moon Transfer Orbit of Lunar Probe

嫦娥三号已经按照计划进入了近地点高度200公里、远地点高度约38万公里的地月转移轨道。

The probe entered the earth-moon transfer orbit as scheduled , with a perigee of 200 kilometers and apogee of 380,000 kilometers .

使用遗传算法和B平面参数进行月球探测器地月转移轨道设计

Lunar Trajectory Design with GA and B - Plane Parameters

首先就探测器携载GPS接收机用于地月转移轨道近地段定轨的几个问题进行分析；

First the GPS navigation of the lunar probe in the close earth orbit phase is analyzed .

利用简化模型，分析了嫦娥一号飞行器在调相轨道和地月转移轨道的VLBI测角精度。

The precision of CE-1 angle calculation using national VLBI network was analyzed , using a simple Earth rotation model .

通过遗传算法和B平面参数对月球探测器地月转移轨道进行了设计和计算，计算结果表明，结合遗传算法和B平面参数可以很好地解决探月轨道搜索的全局性和快速收敛性问题。

The lunar trajectories are designed and computed by using the method of genetic algorithms and B plane parameters in this paper . The result shows that the iterations of transfer trajectories are wholly and quickly achieved by combining genetic algorithms with B plane parameters .

基于紫外敏感器的地月转移轨道慢旋探测器自主导航算法

Autonomous Navigation Algorithm for Slow-Spin Probe in Earth-Lunar Transfer Orbit Based on Ultraviolet Sensors

相位环地月转移轨道研究

Research on Phasing Loops Earth-to-Moon Transfer Orbit

提出了一种将圆锥曲线拼接法与历表相结合，快速设计月球卫星地月转移轨道的方法。

A fast design method for the lunar satellite transfer trajectory is presented by combining patched conic technique and ephemeris .

采用精确轨道动力学模型，得到了满足共面交会约束的发射窗口，以及地月转移轨道特性。

The launch window meeting the restriction of coplanar rendezvous and the characteristics of trans-lunar trajectory is obtained by precise dynamics model .

另外对特殊的地月转移轨道问题提出新的解决思路、分析其内在规律也很有必要。

In addition , the new ways to solve the problems and the essential laws about the special Earth-to-Moon transfer trajectory need to be provided .

典型的月球探测器飞行轨道包括地球停泊轨道段、地月转移轨道段、月球卫星轨道段和着月轨道段。

A typical orbit of lunar probe includes earth parking orbit segment , earth-moon transfer orbit segment , lunar satellite orbit segment and moon-landing orbit segment .

控制中心周五消息，中国第二颗探月卫星&嫦娥二号，在与运载火箭分离后已成功进入地月转移轨道。

Chang'e-2 , China 's second moon probe , has entered the earth-moon transfer orbit as it separated from the carrier rocket , the control center said Friday .

对月球转移轨道设计过程中涉及到的时间系统和坐标系统进行了介绍；给出了双二体假设下的轨道设计模型；综合考虑各种影响因素，建立了地月转移轨道的完整动力学模型。

The time systems and the coordination systems that refered to the design process of translunar-trajectory were introduced . The simplified model based on the double two-body hypotheses was given .

最后用与地月转移轨道相类似的研究方法建立了返回轨道的数学模型，应用该模型对轨道进行仿真分析并给出算例。

Finally , mathematical model as well as the simulation analysis and the design example of the return trajectory are established by the similar method as that of the Earth-Moon transfer trajectory .

小型月球探测器由地球停泊轨道向地月转移轨道射入时，要求采用自旋稳定来建立发动机的点火姿态。

Spin stability is taken for the small lunar explorer to build up the solid motor firing attitude when it was injected from the Earth berth orbit to the Earth Moon transfer orbit .

发射月球探测器实际上是使探测器与月球交会的问题，由于月球位置的变化，选择不同的交会日期相应的地月转移轨道是不相同的。

To launch a lunar probe is actually a problem of rendezvous between the probe and the Moon . Since the positions of the Moon vary the lunar trajectories are different for different times of rendezvous .

文章分析了月球在一个恒星月内位置变化与相应的地月转移轨道升交点赤经和近地点幅角变化的关系，在这个基础上讨论了发射机会和发射窗口问题。

The relation of the right ascension and argument of perigee of the required orbit with the lunar position is derived within one lunar month . Based on this relationship the launch opportunity and launch window are discussed .

提出了一种改进的地月转移轨道计算模型，改进模型将月球状态信息直接融入解析模型中，经计算对比证明在模型复杂度没有明显变化的前提下提高了模型计算精度。

An improved model for translunar trajectory calculation is proposed , which can merge lunar status information directly into the analytical model . Calculations and comparisons show that calculation accuracy can be improved without obvious change of model complexity .

本文工作的创新点有如下几个：1.基于太阳系小天体运动的轨道理论，对地月转移轨道的类型进行分析，为任务中采用大推力形式的转移轨道给出相应的理论依据。

This paper studies different types of Earth to Moon transfer orbit on the basis of orbit dynamics theory of small bodies in the solar system and provides the theoretical basis of the orbit type selection in practice missions . 2 .

本文建立了月球探测器的地月转移轨道与返回轨道的数学模型，得到了轨道的解析表达式，然后通过数值仿真对轨道的特性进行了分析并给出了具体的设计算例。

In the paper mathematical models of the Earth-Moon transfer trajectory and return trajectory for lunar probe are established , analytic expressions for the trajectory are derived , then characteristics of the trajectory are analysed via numerical simulations , and specific examples are proposed in addition .

地月低能转移轨道设计方法研究

Research on Low Energy Transfer Trajectory Design Method Between Earth and Moon

考虑月球升交点黄经的地月低能转移轨道

Low Energy Transfer Orbit to the Moon Considering Longitude of the Ascending Node of the Moon

提出一种探测器地月空问转移轨道分层次搜索算法，该方法快捷有效，可为探测器轨道设计，特别是深空探测器轨道设计提供参考。

The step by step searching method which is used to obtain the accurate cislunar transfer trajectory is provided . The method is fast and effective , which can provide references to the trajectory design for the probe , especially for the deep-space probe .