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A novel fast multi-impulse optimization method for long-duration perturbedorbit rendezvous is proposed. First, based on the analytically estimatedimpulses, the terminal rendezvous deviation with precise dynamics model can bepredicted. Then, an analytical correction to the impulses using the deviationsof orbit elements can be calculated based on the analytical J2 perturbeddynamics equation of a circular orbit. The iteration process repeatingprediction and correction is then designed to quickly obtain a precise solutionand trajectory. The simulation results proved that the iteration method adaptswell to the analytical dynamics and high-precision dynamics. The deviationcould always converge within five iterations.

Fast Optimization of Impulsive Perturbed Orbit Rendezvous with Finite Iterations