Perturbation Correction Calculation Method for Remote Rendezvous between Non-Coplanar Elliptic Orbits

The earth oblateness J2 perturbation effect on the remote rendezvous between non-coplanar elliptic orbits was investigated, and the corresponding perturbation correction calculation method was mainly studied. The differential equation of orbit deviation due to the J2 perturbation was established based on the perturbation theory, and the position error between the perturbed and unperturbed transfer orbits due to the J2 perturbation was obtained through the integral calculation. And then the control strategy by means of correcting the predictive arrival point was put forward to realize the correction of the transfer orbit. A lot of simulations were done to compare the orbit deviation before and after the perturbation correction, and the simulation results indicate that this method, which is simple and easy to be realized without optimization calculation, is efficient to provide a significant increase in accuracy of rendezvous with the effect of perturbation included.