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。 The article studies the motion of spacecraft under constant radial thrust acceleration. First of all, based on the non-Kepler orbit theory, the dynamics model of the spacecraft under continuous thrust is established in the inertial coordinate system. After deducing and analyzing, the momentum moment of the orbit remains constant under the constant radial thrust acceleration, But its energy changes the conclusion. Aiming at the general situation that the initial orbit is an elliptical orbit, the conditions of spacecraft orbiting the Earth under the continuous constant radial thrust are analyzed. The equations for solving the critical acceleration of the escape point are deduced. Finally, the elliptic initial orbit and the initial orbit of the ellipse are respectively analyzed and solved. The characteristics of the orbit change and the critical acceleration of the escape point with the orbital parameters under different constant accelerations are given in the form of simulation curves. Orbital design provides a theoretical reference.