Design of 3-Impulse Lunar Transfer Orbit Using Real-coded Genetic Algorithm under the Constraint of Argument of Perigee by Launch Vehicle

Abstract

This paper addresses a 3-impulse Lunar transfer orbit design method using a real-coded genetic algorithm (real-coded GA). The real-coded GA is applied to the transfer orbit design taking into account the constraint of argument of perigee induced by a launch vehicle. SLIM is a Lunar lander which is developed in JAXA. SLIM is planned to be launched by the solid motor launch vehicle, Epsilon. Since the third motor of Epsilon employs spin stability, the argument of perigee of the injected orbit is constrained to maximize the launch capability, which makes it difficult to reach Moon directly from the injected orbit. Considering such unique characteristics by the launch vehicle, a mid-course maneuver is applied after the trans-Lunar injection to connect to the lunarcentric orbit. The proposed orbit design method using the real-coded GA generates a suboptimal orbit with sufficiently small computational burden, and can be widely applied to an orbit design including mid-course orbit control maneuvers.