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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 timefixed fuel-optimal rendezvous problem [1, 2].