大推力氢氧补燃发动机推力闭环控制设计

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英文篇名：Thrust Closed-loop Control of the Large Scale Expendable Liquid Rocket Propulsion 作者：薛薇 ; 胡慧 ; 武小平 英文作者：Xue Wei;Hu Hui;Wu Xiaoping;Beijing Aerospace Propulsion Inst.; 关键词：液体火箭推进系统 ; 实时动态模型 ; 根轨迹法 ; 推力控制 ; 硬件在回路平台 英文关键词：liquid rocket engine;;real-time dynamic model;;root locus method;;thrust control;;hardware-in-the-loop 中文刊名：JZCK 英文刊名：Computer Measurement & Control 机构：北京航天动力研究所; 出版日期：2019-06-25 出版单位：计算机测量与控制 年：2019 期：v.27;No.249 语种：中文; 页：JZCK201906020 页数：5 CN：06 ISSN：11-4762/TP 分类号：96-100

摘要

提出了大推力氢氧补燃发动机推力闭环控制系统的软硬件平台,为建立液体火箭发动机综合控制系统奠定了坚实的基础;首先,建立了氢氧补燃发动机实时动态非线性模型,在此基础上得到了设计点线性化模型并验证;其次,在线性模型的基础上采用根轨迹法设计了推力闭环控制器,将控制器与非线性模型联合仿真验证了算法的有效性;最后,介绍了发动机硬件在回路系统的软硬件配置,并进行了控制器的平台验证,从操作和实现方式上验证了软硬件平台;该设计满足算法需求且界面人性化,易于操作。
        The principle of large scale expendable liquid rocket engine thrust closed-loop control was proposed and tested.This part is critical to the liquid rocket propulsion control system.Firstly,the real-time dynamic model was set up here,based on this model we got the linear model at the design point.Secondly,the root locus method was used to design the controller,then the simulation of real-time dynamic model combined with the controller was carried out.At last,the hardware-in-the-loop platform containing software and hardware was set up for the engine control.The results show that the controller and the platform work well and easy to operate.

引文

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