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In this paper,the solution and distribution of optimal four-impulse coplanar rendezvous between two elliptical spacecrafts in low eccentricities are investigated.With reference frame built in a circular orbit that is close to two spacecrafts,the relative dynamics described by linear time-invariable equations are established.The initial relative states are processed appropriately to make the solution and distribution of four-impulse model simple in form.Simulations are provided to compare two kinds of guidance strategies,and the strategy proposed in this paper has better performance at guidance precision.In addition,the selection of reference frame has great influence on guidance error,and there exists precision-optimal reference frame.The distribution of four-impulse model is also illustrated.