<p>This paper develops a systematic phased proximity rendezvous control strategy based on differential correction algorithm using impulsive thrust around cislunar libration points. The rendezvous scenario discussed consists of far-range guidance (relative distance within ~ 100&#xa0;km) and close-range approach (relative distance within ~ 500&#xa0;m). Alongside the booming of near-Earth spaceflight, the rendezvous technique is being matured with the associated orbital control algorithm studied thoroughly by both engineering field and academia in the framework of C-W or T-H equation. In the new era of lunar exploration, the libration point <i>L</i>₁ and distance retrograde orbit (DRO) is a significant potential transition station for cislunar exploration yet critical parameters are lacking in systematical discussion. In particular, in the rendezvous scenario, the relative orbital control in the framework of circular restricted three-body problem (CR3BP) is being an open question: if its effectiveness is validated for both <i>L</i>₁ and DRO; if it can be extended to multi-objective optimization as an engineering compensation between fuel consumption and guidance time; how its performances like the field-of-view angle and final deviation look like; if the control scheme is applicable to phasing with relative distance remarkably larger than the one of far-range; how sensitive it is to the uncertainties. This paper is devoted to the addressment of the aforementioned questions.</p>