Multi-Revolution Optimal Rendezvous with Pertubation Near Elliptical Reference Orbit

For multi-revolution rendezvous near elliptical reference orbit, the singularities of the semi-revolution and complete-revolution rendezvous are eliminated. The semi-revolution and complete-revolution rendezvous schemes are proposed, and an implementable rough-refinement two-step optimization algorithm is proposed to determine the optimal transfer time and two impulses. Based on the optimization process, a differential gradient iteration algorithm is presented to improve the rendezvous accuracy with the orbit perturbation considered. The multi-revolution two-impulse rendezvous optimization algorithm and iteration guidance algorithm can be easily extended to multiple-impulse rendezvous. Simulation examples of rendezvous near elliptical reference orbits with different eccentricities are performed. The results show that the optimization algorithm is accurate and effective, and the iteration algorithm converges rapidly. It is concluded that the optimization algorithm and the iteration guidance algorithm are suitable for perturbed multi-revolution rendezvous near circle reference orbit and arbitrary elliptical reference orbit. Several iterations can make the terminal rendezvous error less than one meter.