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We have studied closed periodic orbits with loops for two systems – Sun – Mars and Sun – Earth systems – using Poincare surface section (PSS) technique. Perturbation due to oblateness for the second primary (Mars or Earth) is taken in to consideration and obtained orbits with loops varying from one to five around both primaries. It is found that the oblateness coefficient A2 and Jacobi constant C has nonnegligible effect on the position of the orbits. The model may be useful for designing space mission for low – energy trajectories. Keywords— restricted three body problem; low energy t ra jec tory des ign; periodic orbits; oblateness; Poincare surface of section

Analysis of Periodic Orbits with Smaller Primary As Oblate Spheroid