The spacecraft on highly elliptic orbits fly over thei r apogee in the most part of their cycles, so this kind of orbit is usually appl ied in the satellite communication, the observation of celestial bodies and the exploration of space magnetic fields.

The spacecraft on highly elliptic orbit flies over their apogee in the most part of one period.

Through the analysis on kinematical constraint characters of the launch window for Earth-to-Moon transfer trajectories based on the high elliptical parking orbit,laws of kinematical constraint influence on the launch window are given,and launch opportunities of the lunar probe and the probability to add the launch window are verified.

Relative dynamics and initialization condition for formation flying in elliptical orbits;

The configuration stability of the elliptical orbit satellite constellation requires the stabilization of the ascending node right ascension,the argument of perigee and the mean anomaly at the same time.

A theorem that the elliptical orbit parameters can be acquired by the latitudes and longitudes of flyer which flies around the earth with the gravitation is given and proved.

With the application of quanta general rule and ellipse equation, this paper concludes the relation between ellipse orbit and quantum number.

According to the requirement of application and design of early warning satellite covering with the northern hemisphere of earth,the project of non-isomorphic early warning satellites constellation is put forward using coverage characteristics of ellipse orbit,which is composed of ellipse orbit satellites and equator circle orbit satellites.

Aconcise discussion of elliptic orbit and energy level in hydrogen atom;