限制性三体问题

受摄限制性三体问题平动点线性稳定性的判断条件及在Robe问题的应用

A Criterion for The Linear Stability of Eguilibrium Points in the Perturbed Restricted Three-Body Problem and Applications in Robe Problem

用这些判断条件，讨论了一些阻力对经典限制性三体问题三角平动点线性稳定性的影响，改进了Murray等的一些结果。

By these judging conditions , the effects on the linear stabilities of the triangular libration points in the classic restricted three-body problem with drag are discussed . Some Murray 's results are improved .

关于平面圆型限制性三体问题的LCN的计算

On the computation of LCNs of the planar restricted 3-body problem

圆型限制性三体问题（CRTBP）共线平动点附近存在着大量的周期轨道族。

There are plenty of families of periodic orbits surrounding the collinear libration points in Circular Restricted Three-body Problem ( CRTBP ) model .

用所得到的条件，讨论了任意外力摄动对经典圆型限制性三体问题三角平动点稳定性的影响和惯性阻力摄动对Robe圆型限制性三体问题主要平动点的稳定性的影响。

The effect of an arbitrary external force perturbation upon the stability of equilibrium points in the circular classic restricted three-body problem and the effect of an inertial drag perturbation upon the stabilities of the main equilibrium points in the Robe circular restricted three-body problem are studied by these conditions .

圆型限制性三体问题中双恒星系统的存在性

Existence of double star system in circular restricted three-body problem

辛算法在限制性三体问题数值研究中的应用

Applications of symplectic algorithms to the numerical researches of restricted three - body problem

基于圆型限制性三体问题模型的行星卫星逃逸能量研究

Model . Experimental Investigation on Resistance of Trimaran Study on Escaping Energy in Circular Restricted Three-body Problem

平面圆型限制性三体问题

Plane circular restricted three-body problem

对现有的具有变质量的限制性三体问题运动方程予以修正的证明

The evidence of correction to the existent motive equations with variable mass in restricted three body problem

考虑环影响的平面圆型限制性三体问题的可能运动区域

The Region of Possible Motion of the Planar Circular Restricted Three-Body Problem under the Influence of a Ring

有摄圆型限制性三体问题平动点稳定的充要条件及应用

Sufficient and Necessary Conditions for the Stability of Equilibrium Points in the Perturbed Circular Restricted Three-Body Problem and Applications

利用线性变换来改进空间圆型限制性三体问题的摄动函数展开式的收敛性

Improvement of the convergence of the development of perturbative function in the case of the space circular restrictive problem of three bodies

基于由飞行器、行星及其卫星组成圆型限制性三体问题模型，通过庞加莱映射的方法，研究了飞行器从行星卫星附近逃逸的问题。

Escaping trajectories are investigated using a Poincar é map method in the circular restricted three body problem consisting of spacecraft , planet and moon .

圆型限制性三体问题模型忽略了摄动因素的影响，在很多情况下不能足够准确地描述三体系统的动力学性质。

Since the circular restricted three-body problem model ignores the effect of perturbations , it can not accurately describe the dynamic characters of the three-body system .

本文通过分析卫星在地球和月球引力下的限制性三体问题，建立了系统的微分方程。

Through the analysis of satellite under restrictive three-body problem that considered the gravity of the earth and the moon , differential equations of the system are established .

最后使用两层微分修正方法将圆型限制性三体问题模型下设计的轨道转换到受摄三体问题模型下。

Finally , the two level differential corrections method was proposed to transform the orbit designed under the circular restricted three-body problem model into the perturbed three-body problem model .

主要研究了太阳引力摄动的影响，并基于地-日限制性三体问题和地-日-月四体引力模型分别对太阳引力摄动影响进行了仿真。

The effects of solar gravity perturbation are evaluated as a crucial error of all , which based on the Earth-Sun restricted three-body problem and the Sun-Earth-Moon four-body gravitational model .

以圆型限制性三体问题作为基本模型，采用预估-校正法逼近线性化模型下的目标轨道，给出在轨运行期间的轨控策略亦是可取的，这种控制措施相对而言较简单，容易实现。

Based on the model of circular restricted three body problem , nominal orbit in a linearized model can be approached by prediction-correction method , and the orbital control strategy is relatively simpler and can be easily realized .

给出了受摄限制性三体问题平动点线性稳定性的一些判断条件，条件只与相应的平动点切映像的特征方程系数有关，使用方便。

Some judging conditions for the linear stability of the libration points in the perturbed restricted three-body problem are given . These conditions only depend on the coefficients of the characteristics equations of their tangent maps and are applied expediently .

本文通过对一种简化的椭圆型限制性三体问题对应的受摄理想共振模型的详细讨论，建立了一种用能量关系来判别轨道共振态稳定性的方法。

Based on the detailed discussions on a simplified ideal resonant model with perturbations which corresponds to the elliptic restricted three & body problem , we put forward a discriminating method on stability of orbital resonant states by means of an energy relation in this paper .