本文给出了近地卫星平面内轨道维持的一种方法。这种方法按“最小速度增量”要求,以一圈内的两次周向速度冲量完成对轨道要素α、e、ω的一次修正,用偏置初始半长轴α_o的方法抵消M的长期摄动变化。本文给出的方法适合于平面内轨道维持与初轨修正的一般情况。 This paper presents a method of orbital maintenance in near-Earth satellite. In this method, the first correction of the orbital elements α, e, ω is completed with two circumferential velocity impulses in a circle according to the requirement of “minimum velocity increment”, and the long term of M is canceled by offsetting the initial half-length axis α_o Perturbation changes. The method presented in this paper is suitable for the general case of in-plane orbit maintenance and initial trajectory correction.