In this paper, natural deep space satellite constellations designs in the Earth-Moon system are presented, where the underlying dynamics model is the Elliptic Restricted Three-Body Problem (ERTBP) model. The ERTBP has taken into account the eccentricity of the Earth-Moon system. Therefore, the generated motion will be more realistic than that in the Circular Restricted Three-Body Problem (CRTBP) due to the relatively large eccentricity of the Earth-Moon system (about 0.0554). First, a type of strictly periodic orbit, Multi-revolution Elliptic Halo (ME-Halo) orbit, around the L2 libration point in the Earth-Moon ERTBP is presented, generated through the continuation method starting from the conventional Halo orbits in the CRTBP. It is discovered that there are only a limited number of ME-Halo orbits that are practically useful, which restricts the mission design of a natural satellite constellation. Next, four different types of constellations consisting of the ME-Halo orbit, which are the focus on this paper, are presented and discussed. These configurations exist in the ERTBP and are nonautonomous. At last, the nominal ME-Halo orbit is analyzed with respect to the high-fidelity ephemeris model, which preliminarily validates that the nominal ME-Halo orbit is suitable for deep space constellation design, as it approximates the real Earth-Moon system with good accuracy. The results in this paper provide new natural satellite constellation options in the Earth-Moon system, which have different features through combining various ME-Halo orbits.
All Science Journal Classification (ASJC) codes
- Aerospace Engineering
- Deep space satellite constellation
- Earth-Moon system
- Elliptic restricted three-body problem
- Multi-revolution elliptic Halo orbit