一种月球飞船动力下降预测制导方法的研究  

A Predictive Guidance Method for the Powered Descent of Lunar Spacecraft

作　　者：薛志飞 韩艳铧[1] 

机构地区：[1]南京航空航天大学航天学院,南京210016

出　　处：《航天控制》2017年第6期19-25,共7页Aerospace Control

基　　金：南京航空航天大学"中央高校基本科研业务费专项资金项目"资助(项目编号NS2016082)

摘　　要：研究了一种月球飞船动力下降段的预测制导方法。首先在轨道平面内建立了月球飞船飞行力学模型;然后基于开普勒轨道力学,由飞船当前飞行状态预测其落月位置和速度,以及相应的剩余飞行时间。设计了切向和法向解耦的闭环制导律。切向制导律根据预测的落点速度偏差和剩余飞行时间形成切向推力控制量来控制飞船速度大小,以消除落点速度偏差。法向制导律根据预测的落点位置偏差形成法向推力控制量,来改变飞船速度方向,以消除落点位置偏差。所设计的预测制导律,通过解析解预测落点状态,比传统的基于数值计算的预测方法在线计算量小,易于实现。数值仿真验证了该制导律的有效性。In this paper, a predictive guidance method for the powered descent of lunar spacecraft is stud- ied. Firstly, the flying dynamics model of the lunar spacecraft is established in the orbital plane. Then, based on the Kepler orbit mechanics, the landing position and velocity of the spacecraft are predicted ac- cording to the current flight state, and the corresponding remaining flight time is predicted. The tangential and normal decoupling closed - loop guidance laws are designed. The tangential guidance law, based on the predicted landing velocity deviation and the remaining flight time, forms tangential thrust to control the velocity of the spacecraft in order to reduce the landing velocity deviation. Regarding the predicted landing position deviation, normal thrust is formed to change the flight direction of the spacecraft in order to elimi- nate the landing position deviation by using the normal guidance law. The prediction algorithm is developed according to the analytical method, which is simpler than the traditional algorithm based on numerical method and is easy to realize on line. The numerical simulation verifies the effectiveness of the proposed guidance law.

关 键 词：月球飞船 动力下降 开普勒轨道 预测制导 

分 类 号：V448[航空宇航科学与技术—飞行器设计]