轨道半长轴

通过对3种星座构型，6种轨道半长轴，46°~66°之间轨道倾角的对比计算，以回归周期内星座CV值作为指标确定了初选卫星星座。

Through the comparative calculations on three kinds of configuration , six kinds of semi major axis and orbital inclination between 46 ° ~ 66 °, the original configurations are designed based on the constellation CV values in repeat period .

椭圆轨道半长轴为，近地点到远地点。

A The ellipse has a semimajor axis A , - 2a perigee to apogee & is2a .

首先研究了通过改变轨道半长轴调整航天器升交点赤经变化率，进而控制轨道法向振幅的方法；

First , a new method of controlling the swing of orbit normal axis by changing the semi studied ;

地球磁场对带电赤道卫星的轨道半长轴和偏心率的摄动影响

Perturbation effect of the earth ′ s magnetic field on the variation of the semimajor axis and eccentricity of the orbit of a charged equatorial sattellite

给出了由轨道半长轴确定空间两点间圆锥曲线转移轨道的方法，随后给出了一种固定发射时刻和转移时间的情况下利用半长轴迭代的圆锥曲线转移轨道求解算法。

A method determining conic transfer trajectory between two points in space by a fixed semi-major axis was given . An arithmetic solving conic transfer trajectory by iterating semi-major axis with a specified launch time and transfer time was given .

我们知道其相对轨道运动的主要半长轴a和周期p。

The major semiaxis a and p of the relative orbital motion are known .

本文详细分析了轨道长期运行期间，轨道半长轴以及地面轨迹漂移的变化情况，并采取半长轴超调控制的方法，利用自然力的被动控制，来实现较少控制次数。

The thesis analyzed the evolution of semi-major axis and ground track in long term . The method of using over-control was proposed , it can utilize passive control , save fuel and decrease the times of active control .

给出了影响卫星定点捕获所需速度增量的入轨轨道参数和点火姿态等因素，并仿真计算了轨道半长轴、近地点高度、倾角和近地点幅角与速度增量的关系。

The orbit injection parameters and firing attitude that affected velocity increment for orbital acquisition were presented . The relationships between the velocity increment and orbit semimajor axis , perigee altitude , inclination , and perigee argument were simulated .

计算结果表明，潮汐作用使轨道周期较小的Ba星系统的能量减小，所以系统轨道的半长轴和轨道偏心率减小；

The results show that tidal friction diminishes the total energy of binaries systems with shorter orbital periods .

该套软件根据卫星轨道调整前后的轨道参数特点和轨道调整后的星下点轨迹要求，确定机动时间，将调整轨道半长轴与微调星下点轨迹结合起来，在最短时间内完成轨道调整任务。

The software determines maneuver time by considering the adjustment of semi-major axis and ground track .