Hybrid Genetic Algorithm Collocation Method for Trajectory Optimization

A hybrid genetic algorithm collocation method for direct optimization of trajectories is implemented to solve the constrained optimal control problem. The hybrid optimization technique for synthesis of trajectories uses a direct Hermite-Legendre-Gauss-Lobatto (HLGL) collection technique. The minimum-time low-thrust transfer trajectory from a geocentric circular orbit to an aerocentric circular orbit is computed. The initial guesses for the nonlinear programming problem are obtained by searching through the state space for feasible candidate solutions through as genetic algorithm with a shooting method. The results show that the lower and upper bounds on the initial orbit angle for the geocentric segment and the final orbit angle for the aerocentric segment are 0 and 2π rad respectively. The more accurate solution by the HLGL collocation phase shows that the radial velocity of the spacecraft should decrease near the end of the helicopter segment as its position approached Mars.