Abstract:

The optimal noncoplanar orbital transfer between geostationary earth orbit (GEO) and low-earth orbit for the orbital transfer vehicle (OTV) is studied, and analytical method and intelligence optimization algorithm are proposed. For the analytical method, the solution of the optimal transfer orbit is fully derived. The conditions which the optimal transfer orbit should be satisfied are given, and the optimal changed inclination due to the first impulse is solved by Newton iteration. The genetic algorithm (GA) is used to solve the optimal transfer orbit, where the optimal solution is composed of deorbit position, reorbit position and transfer time. The steps for GA are given and the demo of orbital transfer is carried out in Satellite Tool Kit (STK). The simulation results show that the Lawden’s first-order optimality condition can be satisfied for both methods.