迭代制导在月面上升段的应用研究  

Study on Application of Iterative Guidance in Lunar Ascent

作　　者：巩庆海[1] 宋征宇[1] 吕新广[1] 

机构地区：[1]北京航天自动控制研究所,北京100854

出　　处：《载人航天》2015年第3期231-236,269,共7页Manned Spaceflight

基　　金：载人航天预先研究项目(020301)

摘　　要：针对迭代制导在月面上升段的应用开展研究。首先对迭代制导基本原理及其在运载火箭上的应用进行了回顾,给出了月面上升段的动力学模型和迭代制导算法模型。并通过对比应用场景,深入研究了垂直起飞段和迭代制导段的衔接,提出了针对月面上升段特点、兼顾工程可实现性和燃料最优的迭代制导应用方案。对发射点参数、目标轨道参数、迭代初值的获取方式进行了讨论。最后以阿波罗12号飞船载人月面返回的任务场景为算例,进行Monte Carlo模拟打靶数学仿真验证,表明迭代制导在月面上升段具有较高的入轨精度。The application of iterative guidance in lunar ascent was studied.Firstly,the foundation of iterative guidance and its application in launch vehicle were reviewed,then the dynamic model and iterative guidance algorithm were proposed.By comparing the differences between the two scenes and considering the lunar characteristic,the application scheme of iterative guidance in lunar ascent,with the advantage of both engineering obtainable and fuel optimal,was proposed.The link up of the vertical ascent phase and iterative guidance phase was thoroughly studied.The way of acquiring initial launch point parameters,target orbital parameters and initial parameters of iterative guidance for lunar ascent was discussed.Finally,the iterative guidance was tested by Monte Carlo simulation under the scene of Apollo 12 manned spacecraft returning from lunar surface,which demonstrated a high insert precision.

关 键 词：迭代制导 月面上升 载人登月 阿波罗飞船 数学仿真 

分 类 号：V44[航空宇航科学与技术—飞行器设计]