Patent ID: 9284068
Filing Date: 2016-03-15
CPC Classification: B64G

Claim Text:
1. A control system for a hybrid propulsion spacecraft configured for transfer between low earth parking orbit (LEO) and a Lissajous L2 orbit (L2O), the control system comprising: a first control portion communicably connected to a high thrust (HT) engine portion of the hybrid propulsion spacecraft; a second control portion communicably connected to a low thrust high specific impulse (LT-HI) engine portion of the hybrid propulsion spacecraft; and the first and second control portions being configured to control both the HT engine portion and the LT-HI engine portion of the hybrid propulsion spacecraft to provide an optimal LEO to L2O transfer trajectory; wherein the optimal LEO to L2O trajectory includes an optimal LT-HI trajectory portion, selected from a stable manifold trajectory, and an optimal HT trajectory portion, and wherein the LT-HI trajectory portion and HT trajectory portion are configured for providing a combined optimal trajectory along the LEO to L2O transfer trajectory, and are optimized substantially simultaneously.