绕月返回飞行再入航程调整的轨道控制  

Trajectory Maneuver for Reentry Downrange Modification during Circumlunar Return Flight

作　　者：张磊[1] 谢剑锋[1] 刘勇[1] 

机构地区：[1]北京航天飞行控制中心,北京100094

出　　处：《飞行器测控学报》2015年第1期64-69,共6页Journal of Spacecraft TT&C Technology

摘　　要：绕月返回飞行的再入航程调整用于扩大发射窗口及应急轨道重构,采用2次联合的轨道控制实现。为求解2次轨道控制的速度增量,在瞬时再入平面内确定新再入状态并进行反向轨道外推得到新返回轨道,再通过指定2次轨道控制时刻,将2次轨道控制的联合求解转化为仅须求解第一次轨道控制速度增量的Lambert转移问题,并利用Lambert制导法或线性修正法进行求解。研究表明,速度增量与再入航程调整量呈线性关系,适当提前再入时刻、扩大2次轨道控制时间间隔有助于减小速度增量。将上述方法及结论用于绕月自由返回轨道再入航程调整轨道控制策略的计算分析,可为飞控方案设计提供依据。Reentry downrange modification by two correlative trajectory maneuvers during circumlunar return flight is used to extend the launch window and reconstruct the emergency trajectory. A method is proposed to solve both velocity increments of two trajectory maneuvers. Specifically, new reentry state is calculated in the instantaneous reentry plane. Then, the new return trajectory is acquired by propagating the state backward. The two subsequent maneuver epochs are assigned. The original problem is translated into a Lambert transfer problem with only the ve- locity increment of the first trajectory maneuver to be solved by the Lambert guidance method or the linear correction method. Studies show that a linear relationship exists between the velocity increment and the reentry downrange modification value. Appropriate shift to an early reentry and expansion of trajectory maneuver time interval help reduce velocity increment. For the reentry downrange modification of the circumlunar free return trajectory, the method and conclusions are applied to the trajectory maneuver strategy calculation and analysis, and the results provide a basis for design of flight control plan.

关 键 词：再入航程调整 绕月返回 Lambert转移 轨道控制 

分 类 号：V412.41[航空宇航科学与技术—航空宇航推进理论与工程]