Interplanetary optimum two-impulse transfer trajectories

The optimum two-impulse transfer trajectory is investigated. Taking the interplanetary mission as the background, the state transition matrix and variational method are utilized, and the analytical partial derivatives of the index with respect to the adjustable variables is inferred. Based on these analytical partial derivatives, a fast optimization algorithm for two impulse transfer trajectory is given out. The problems of slow speed and the uncontrollable precision flaws in the traditional optimization of interplanetary two-impulse transfer trajectory arc solved. At the end, taking the Earth-Mars orbit transfer as an example, the result calculated by the optimization method brought up in this paper is compared with the result computed by the traditional 'pork-chop' figure, and the accuracy and speediness of this algorithm arc validated.