  A novel fast multi-impulse optimization method for long-duration perturbed
orbit rendezvous is proposed. First, based on the analytically estimated
impulses, the terminal rendezvous deviation with precise dynamics model can be
predicted. Then, an analytical correction to the impulses using the deviations
of orbit elements can be calculated based on the analytical J2 perturbed
dynamics equation of a circular orbit. The iteration process repeating
prediction and correction is then designed to quickly obtain a precise solution
and trajectory. The simulation results proved that the iteration method adapts
well to the analytical dynamics and high-precision dynamics. The deviation
could always converge within five iterations.
