Design and analysis of direct abort trajectory for a crewed lunar mission based on the quasi-lambert problem

Abstract A direct design method for abort trajectory based on the quasi-lambert problem is proposed. The re-entry constraint analytically addressed via a instead of variables iteration and optimization in past. Then new parameter introduced to determine plane. exact solution determined by differential correction initial solution. Numerical simulation carried out test validity efficiency method. comparison with STK verifies its reliability. Additionally, characteristics their application option strategy different ways are studied. flight time point affect trajectories’ velocity increment latitude landing area.