Advances in Astrophysics

Download PDF (554.3 KB) PP. 12 - 24 Pub. Date: February 1, 2017

DOI: 10.22606/adap.2017.21003

• A. Safiya Beevi
  Department of Mathematics, College of Engineering, Thiruvananthapuram - 695016, India
• Ram Krishan Sharma^*
  Department of Aerospace Engineering, Karunya University, Coimbatore - 641114, Tamilnadu, India

The motion of a particle in the restricted three-body problem is explored by treating the more massive primary as an oblate spheroid with its equatorial plane coincident with the plane of motion of the primaries using a perturbation method. Initial conditions for the infinitesimal periodic orbits around the more massive primary are generated and the effect of oblateness on the perigee of these orbits is studied as well. It is observed that when oblateness coefficient is increased, the perigee of the orbit shifts towards both the primaries depending upon the increase in period and mass ratio. It is further noticed that during this transition, for certain periods, the perigee of the orbit remains unaltered with the increase in the oblateness coefficient.

RTBP, Earth-Moon System, series solution, periodic orbit, oblateness effect.

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