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中文摘要：
文章在同时考虑太阳和小天体引力的基础上,建立探测器相对小天体运动的动力学方程,利用状态转换矩阵描述小行星附近的运动。采用了一种阈值控制方法,当误差超过阈值时,利用脉冲控制使得探测器回到目标位置。研究结果表明,该控制方法能很好地实现探测器的位置保持,且方法实现简单、控制周期长、推进剂消耗少。
英文摘要：
An impulse control method was proposed for the position keeping of a spacecraft near asteroid. Considering the gravity of the Sun and asteroid, the relative equation of motion of the spacecraft with respect to the asteroid was derived. The state transition matrix was used to describe the motion in the vicinity of the asteroid. A threshold control method was used to achieve the position keeping. The impulse controller was triggered when the position error was larger than a specified value. The results show that this method performs well for the position keeping, and the control period is long and propellant consumption is low.
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