摘要
根据月球探测器奔月变轨过程中自旋稳定各阶段的特点,提出了分阶段进行主动章动、进动控制的策略和方法。对影响自旋稳定指向精度的因素和控制方法进行了研究。数学仿真结果表明:起旋推力器推力偏差是引起章动的主要因素;质量不平衡和能量耗散引起的章动很小,初步设计时可略去不计。采用限制横向角速率以限制最大章动角的控制策略可快速消除章动,便于工程实现。
The strategy and method of active nutation and precession control in different phases are presented in this paper according to the characteristics of spine stability for lunar probe during translunar injection. The factor and control that are affected orientation error are also analyzed. The simulation results are showed that nutation angle caused by dynamic unbalance and energy dissipation is almost neglected and one by thruster assemble error is the main factor. The control strategy that the maximum nutation angle is limited by maximum transverse velocity is able to eliminate nutation and easy to realize in engineering.
出处
《上海航天》
2003年第5期57-61,共5页
Aerospace Shanghai
关键词
月球探测技术
自旋稳定
横向角速率
章动角
主动进动控制
轨道控制
Lunar probe
Spine stability
Transverse velocity
Nutation angle
Active nutation control
Active precession control
