月地低能返回轨道最优控制策略研究  

Study on Optimal Control Strategy for Low Energy Moon Return Trajectory

作　　者：刘玥[1] 付凯林 荆武兴[2] 钱霙婧[3] 

机构地区：[1]航天东方红卫星有限公司,北京100094 [2]哈尔滨工业大学航天学院,哈尔滨150001 [3]北京工业大学机械工程与应用电子技术学院,北京100022

出　　处：《载人航天》2018年第1期1-6,共6页Manned Spaceflight

基　　金：国家自然科学基金(11172077);高等学校博士学科点专项科研基金(20112302110055)

摘　　要：为解决月球货运飞船采用的低能返回轨道对初值极为敏感的问题,研究了月地低能返回轨道的最优控制策略。首先基于椭圆四体动力学模型,分析了月地低能返回轨道的动力学特性;进而引入协方差分析法分析了轨道初始飞行状态的误差传播特性,确定了保证终端再入点高度约束要求的飞行器入轨点位置、速度以及入轨时刻控制精度需求;根据轨道对不同时期施加控制的敏感性不同,设计了一种三脉冲轨道控制策略,以实现既精确控制落点约束,又节约控制燃料消耗的目的。从仿真结果可知,该策略可有效控制月地低能返回轨道终端再入点精度,降低初始敏感度。该控制方案用于月地转移可显著降低对推进控制系统的精度需求,提高转移方案的工程可实现性。The low energy Moon return trajectory adopted by the lunar cargo spaceship is extremely sensitive to the initial value. To solve this problem, the control strategy optimization for low energy Moon return trajectory was studied. Based on the elliptical four body model, the dynamical model of the spacecraft was analyzed. Then, the covariance analysis method was introduced to study the prop-agation properties of initial orbit errors so that the demands for control accuracy of the position error, the velocity error and the time error were clarified. In the end, a three maneuvers orbit fixing strate-gy was proposed according to the sensitiveness of the constraints of the accuracy of navigation and control impulse. The simulation results showed that the strategy could effectively guarantee an accu-rate reentry height. With the proposed control strategy, the low energy Moon return trajectory could be easily realized because the precision requirement of the trajectory control system was significantly reduced.

关 键 词：月球返回轨道 低能量 控制策略 误差传播 协方差分析法 

分 类 号：V448[航空宇航科学与技术—飞行器设计]