Abstract: The discrepancies between impulsive thrust model and continuous thrust model have greatly limited the application of impulsive strategy on spacecraft rendezvous trajectory engineering. Based on Lambert theorem and genetic algorithm, an optimal impulsive rendezvous trajectory is designed. According to the results, an engineering realization method is implemented via iterative guidance algorithm. The simulation results show that the method is effective.

Key words: orbital rendezvous, impulsive rendezvous, iterative guidance orbital rendezvous, impulsive rendezvous