火箭垂直着陆段制导方法研究  

Research on Guidance of Vertical Landing Segment for Launch Vehicle

作　　者：吕建强[1] 陈曦 王光辉 徐帆[1] Lyu Jian-qiang;Chen Xi;Wang Guang-hui;Xu Fan(Beijing Aerospace Automatic Control Institute,Beijing,100854)

机构地区：[1]北京航天自动控制研究所,北京100854

出　　处：《导弹与航天运载技术》2022年第2期51-55,共5页Missiles and Space Vehicles

摘　　要：为了实现精确着陆,从制导角度分析了对发动机的需求,并讨论了基于现有条件的解决方案。针对推力调节动态过程对制导的影响,建立了简化的数学模型,设计了校正网络;基于四次多项式制导提出了一种基于过载反馈的制导方法,该方法将过载偏差作为推力调节指令,能够适应发动机推力调节的动态响应过程,同时能够克服火箭质量等多种参数不准确带来的偏差。仿真结果表明新方法具有很好的适应能力,能够为工程应用提供支撑。The demand to engine performance is analyzed from the guidance point of view,then a solution is proposed based on current conditions for accuracy vertical landing.Firstly,a model of thrust regulation process frequency characteristics is built to design correction network.Secondly overload feedback guidance method is proposed based on fourth-order polynomial guidance.The overload deviation is used for thrust regulation command.The overload feedback guidance can adapt to thrust regulation process frequency characteristics and can overcome effect of inaccuracy mass.Finally,the results of mathematical simulation demonstrate that the effectiveness of the new method and that can be used in engineering application.

关 键 词：制导 过载反馈 推力调节 动态性能 垂直着陆 

分 类 号：V448[航空宇航科学与技术—飞行器设计]