Performance Analysis of LFV Soft Landing Guidance Method Based on Convex Optimization

This paper analyzed the lunar soft landing guidance performance of lunar maneuvering flying vehicle (LFV) based on convex optimization. To this end, a fuel optimization model for the lunar soft landing phase is firstly established. By using convex optimization theory, it is then transformed into a second-order cone optimization problem, which can be sovled via mature convex optimization tools. Based on this, various factors including landing time, throttle range and initial error, are analyzed to investigate their impacts on the guidance performance. The simulation results indicate that the guidance method based on convex optimization is able to meet mission requirements with any landing accuracy even in large landing time range, various throttle range and large initial error, and thus hold good mission adaptability.