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;

The optimal impulse rendezvous based on the criterion of impulse modifying,Lambert optimal rendezvous,the optimal impulse rendezvous solved by numerical methods and the optimal impulse rendezvous based on the theory of optimal rendezvous between neighboring circular orbits are introduced.