Using Polynomial Optimization to Solve the Fuel-Optimal Linear Impulsive Rendezvous Problem

摘要

THE first space missions involving more than one vehicle (Gemini, Apollo, and Vostok) have highlighted the fact that the space rendezvous between two spacecraft is a technology that raises relevant open control issues. Strictly speaking, the space rendezvous maneuver is an orbital transfer between a passive target and an actuated spacecraft, called the chaser, within a fixed or floating time period. Since the rendezvous maneuver can only be performed within a certain period of time while using as little fuel as possible to extend the chaser lifetime, we mainly focus on the so-called time-fixed fuel-optimal rendezvous problem [1,2].