文章研究了航天器在常值连续径向推力加速度作用下的运动特性.首先,基于非开普勒轨道理论,在惯性坐标系中建立了连续推力作用下航天器的动力学模型,经过推导和分析得了出在常值径向推力加速度下轨道动量矩仍保持常值,但其能量发生变化的结论.同时针对初始轨道是椭圆轨道的一般情况,分析了航天器在连续常值径向推力作用下环绕地球运动的条件,推导给出了求解逃逸点临界加速度的方程组.最后,对椭圆初始轨道和圆初始轨道的情况分别进行了分析和求解,并以仿真曲线的形式给出了不同常值加速度下轨道变化特性以及逃逸点临界加速度随轨道参数变化的特性,为机动轨道设计提供了理论参考.%Aim. The introduction of the full paper discusses relevant matters and then proposes the exploration mentioned in the title, which is explained in sections 1 through 3. Their core consists of; "Firstly, based on non-Keplerian orbit theory, we establish the dynamics model of the spacecraft under constant radial thrust in inertial frame. Under the constant radial acceleration, the moment of momentum of the orbit is constant, while the energy of the spacecraft is changed. Then, the conditions for spacecraft orbiting earth under constant radial thrust are analyzed in the general form of elliptical initial orbits, and the equations for solving critical acceleration are derived. " Finally, section 4 studies respectively the two cases of elliptical and circular initial orbits. Simulation curves are presented in Figs. 1, 2 and 3 and we analyze these curves with the help of Figs. 4, 5 and 6. These simulation curves and their analysis are, in our opinion, useful for the design of maneuver orbits.
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