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halo轨道
相关语句
  halo orbit
     The L_1 libration point and the halo orbit around the L_2 point in the Earth-Moon system play an important role in exploring the Moon. It can link the Earth with the nearside and farside of the Moon,respectively.
     地-月系统的平动点L1点及L2点的Halo轨道在探月工程中有重要的应用价值,可分别用于地月连续通信覆盖和月球背面的探测。
短句来源
     This paper deals with the problem of entering the L_1 point and the halo orbit of the L_2 point,as well as entering the low orbit around the Moon by means of the Sun's gravitation. Then a low energy lunar transfer orbits is obtained from the two latter entering orbits.
     本文分析了如何利用太阳引力进入地-月系统的L1点及L2点的Halo轨道、以及由Halo轨道进入近月轨道的问题,两者综合起来构成了一条完整的地月低能转移轨道。
短句来源
  halo orbits
     The Application of Libration Points and Halo Orbits in the Earth-Moon System to Space Mission Design
     地-月系平动点及Halo轨道的应用研究
短句来源
     Firstly, the papar introduces the posi tion relation of five libration points and the possible mission around them. Sec ondly, the difference of halo orbits and lissajous orbits, in theory, is compare d . It emphasizes that two orbits are the special solutions to the linearized bia s equations of motion.
     首先介绍了 5个平衡点的位置关系及卫星应用 ,接着从理论上简单比较了Halo轨道和Lissajous轨道的区别 ,指出Halo轨道和Lissajous轨道是线性化偏差方程的特解。
短句来源
  “halo轨道”译为未确定词的双语例句
     Using the orbit maneuver at the place where the two planes and the invariant manifolds intersect,a general method to design low energy lunar landing trajectory was given.
     给出了这两个三体系统Halo轨道不变流形与两轨道面相交处进行小的变轨来设计低成本探月轨道的一般方法.
短句来源
  相似匹配句对
     Track desigh
     轨道设计
短句来源
     The Application of Libration Points and Halo Orbits in the Earth-Moon System to Space Mission Design
     地-月系平动点及Halo轨道的应用研究
短句来源
     Orbit plug valve
     轨道式旋塞阀
短句来源
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  halo orbit
Reconfiguration of formation flying around a halo orbit of the Sun-Earth restricted three body system is investigated with impulse maneuvers.
      
After several deep space orbits (~2 yrs) WIND will eventually be injected into a halo orbit around the Sun-EarthL1 point.
      
This synchronized trajectory describes a 'halo orbit' of the Moon.
      
A translunar communication station is to be kept close to a nominal unstable periodic 'Halo' orbit, visible at all times from Earth.
      
Study of the transfer from the Earth to a halo orbit around the equilibrium pointL1
      
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  halo orbits
The Halo orbits originating in the vicinities of both,L1 andL2 grow larger, but shorter in period, as they shift towards the Moon.
      
(ii) If the nearer primary is much less massive than the further, the thin L1-family and L2-family halo orbits are analyzed to 1st order in these same 4 small quantities with an independent variable related to the one-dimensional approximate motion.
      
A largely numerical study was made of families of three-dimensional, periodic, 'halo' orbits near the collinear libration points in the restricted three-body problem.
      
The approach used in the paper makes use of the hyperbolic character of the halo orbits under consideration.
      
A methodology is developed to design optimal time-free impulsive transfers between three-dimensional halo orbits in the vicinity of the interior L1 libration point of the Sun-Earth/Moon barycenter system.
      
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There are five libration points of circular-restricted three-b ody problem. The L 1 and L 2 libration points in sun-earth system hav e been the focus of recent space studies. Firstly, the papar introduces the posi tion relation of five libration points and the possible mission around them. Sec ondly, the difference of halo orbits and lissajous orbits, in theory, is compare d .It emphasizes that two orbits are the special solutions to the linearized bia s equations of motion. Thirdly, the application...

There are five libration points of circular-restricted three-b ody problem. The L 1 and L 2 libration points in sun-earth system hav e been the focus of recent space studies. Firstly, the papar introduces the posi tion relation of five libration points and the possible mission around them. Sec ondly, the difference of halo orbits and lissajous orbits, in theory, is compare d .It emphasizes that two orbits are the special solutions to the linearized bia s equations of motion. Thirdly, the application of foreign spacecrafts in orbits near the libration points in the sun-earth system is described. Two available manners of transfer trajectory are analyzed.

圆形限制性三体问题中存在 5个动平衡点。其中日 地系统中共线平衡点L1和L2 是近十几年来国外研究热点。首先介绍了 5个平衡点的位置关系及卫星应用 ,接着从理论上简单比较了Halo轨道和Lissajous轨道的区别 ,指出Halo轨道和Lissajous轨道是线性化偏差方程的特解。介绍国外日 地动平衡点卫星应用情况 ,分析了转移轨道的两种可行方式。

The L_1 libration point and the halo orbit around the L_2 point in the Earth-Moon system play an important role in exploring the Moon.It can link the Earth with the nearside and farside of the Moon,respectively.The dynamics of the Earth-Moon system is quite different from the Sun-Earth system especially after a long duration for the gravitational attraction of the Sun.This paper deals with the problem of entering the L_1 point and the halo orbit of the L_2 point,as well as entering the low orbit around the Moon...

The L_1 libration point and the halo orbit around the L_2 point in the Earth-Moon system play an important role in exploring the Moon.It can link the Earth with the nearside and farside of the Moon,respectively.The dynamics of the Earth-Moon system is quite different from the Sun-Earth system especially after a long duration for the gravitational attraction of the Sun.This paper deals with the problem of entering the L_1 point and the halo orbit of the L_2 point,as well as entering the low orbit around the Moon by means of the Sun's gravitation.Then a low energy lunar transfer orbits is obtained from the two latter entering orbits.This study is of high value for orbit design for lunar exploration.

地-月系统的平动点L1点及L2点的Halo轨道在探月工程中有重要的应用价值,可分别用于地月连续通信覆盖和月球背面的探测。由于在地-月系统中太阳的引力不可忽略,特别是在长时间作用以后,其动力学行为与摄动力较小的日-地系统有明显的不同。本文分析了如何利用太阳引力进入地-月系统的L1点及L2点的Halo轨道、以及由Halo轨道进入近月轨道的问题,两者综合起来构成了一条完整的地月低能转移轨道。研究结果对探月轨道设计有一定的参考价值。

The low-energy lunar landing trajectory design using the invariant manifolds of restricted three body problem is studied. Considering angle between the ecliptic plane and lunar orbit plane,the four body problem of Sun-Earth-Moon-spacecraft was divided into two three body problems,the Sun-Earth-spacecraft in the ecliptic plane and the Earth-Moon-spacecraft in the lunar orbit plane.Using the orbit maneuver at the place where the two planes and the invariant manifolds intersect,a general method to design low energy...

The low-energy lunar landing trajectory design using the invariant manifolds of restricted three body problem is studied. Considering angle between the ecliptic plane and lunar orbit plane,the four body problem of Sun-Earth-Moon-spacecraft was divided into two three body problems,the Sun-Earth-spacecraft in the ecliptic plane and the Earth-Moon-spacecraft in the lunar orbit plane.Using the orbit maneuver at the place where the two planes and the invariant manifolds intersect,a general method to design low energy lunar landing trajectory was given. It is found that this method can save the energy by 20% compared with the traditional Hohmann transfer trajectory. The mechanism of the method that can save energy was investigated in the point of view of energy and the expression of the amount of energy saved is given.In addition,some rules of selecting parameters with respect to orbit design were provided.The method of energy analysis can be extended to energy analysis in deep space orbit design.

研究了基于三体问题的不变流形设计低成本登月轨道的问题.考虑了黄道面和白道面之间夹角不为零的三维情况,将太阳_地球_月亮_卫星组成的四体问题分解成由太阳_地球_卫星和地球_月亮_卫星组成的非共面的两个限制三体问题.给出了这两个三体系统Halo轨道不变流形与两轨道面相交处进行小的变轨来设计低成本探月轨道的一般方法.比较结果表明用该方法设计的轨道比传统的Hohmann变轨节省约20%的燃料.从轨道能量的角度分析了用流形设计轨道比Hohmann变轨节省燃料的原因,并给出了理论表达式.该方法对于深空探测轨道设计的能量分析具有普遍的适用性,可为设计提供一个选择参数的标准.

 
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