载人登月周期重访轨道保持策略设计  

A Strategy for Manned Lunar High Precision Cycler Orbit Stability Control

作　　者：贺波勇[1] 李海阳[1] 李飞[1] 沈红新[2] 

机构地区：[1]国防科学技术大学航天科学与工程学院,长沙410073 [2]西安卫星测控中心,西安710043

出　　处：《载人航天》2016年第4期411-416,共6页Manned Spaceflight

基　　金：国家自然科学基金(11372345);国家重点基础研究发展计划(2013CB733100)

摘　　要：针对高精度星历动力学模型下载人登月周期重访轨道(也称地月循环轨道)发散问题,设计了一种轨道保持控制策略。提出一种高精度星历动力学模型下的循环轨道初值设计方法,分析了日月中心引力、地球J2项等摄动力对轨道快速发散作用,设计了一种特殊点四脉冲周期重访轨道保持策略。高精度动力学数值仿真实验表明,该种轨道保持策略控制频率低、速度增量消耗小,控制精度能够满足任务需求,达到预期设计目标。An orbit keeping control strategy was designed for manned lunar cyclical revisit orbit（ also known as the trans-lunar cycler orbit） divergence problem,on account of the high precision ephemeris dynamics model. A trans-lunar cycler orbit initial design method was presented based on high precision ephemeris model. The main perturbation force and its effect on the fast divergence trajectory process were analyzed and the orbit keeping control strategy was designed. High precision dynamics numerical simulation results showed that the proposed strategy was of low control frequency and low speed increment,and the control accuracy could meet the requirements of the task. The design goal was achieved.

关 键 词：载人登月 循环轨道 轨道保持控制 高精度动力学模型 

分 类 号：V412[航空宇航科学与技术—航空宇航推进理论与工程]