航空发动机燃油伺服系统可控流路设计方法  

Design method of controllable flow path for aero-engine fuel servo system

作　　者：赵文帅 王曦[1] 龙一夫 周龙 周振华 张胜 ZHAO Wenshuai;WANG Xi;LONG Yifu;ZHOU Long;ZHOU Zhenhua;ZHANG Sheng(School of Energy and Power Engineering,Beihang University,Beijing 100191,China;Product Design Institute,AECC Guizhou Honglin Aeroengine Control Technology Co.,Ltd,Guiyang 550009,China)

机构地区：[1]北京航空航天大学能源与动力工程学院,北京100191 [2]中国航发贵州红林航空动力控制科技有限公司产品设计所,贵州贵阳550009

出　　处：《推进技术》2024年第12期85-101,共17页Journal of Propulsion Technology

基　　金：国家科技重大专项(J2019-V-0010-0104)。

摘　　要：针对液压机械伺服系统正向设计的难点,提出了液压机械伺服系统可控流路的基本概念和理论。通过建立状态空间模型,采用闭环系统分析法及液压机械伺服系统可控流路概念,提出了单腔和串联式双腔两种基本结构的可控流路设计方法;在此基础上,以燃油伺服等压差控制系统的正向设计为典型算例,应用提出的可控流路设计方法进行了系统性设计。仿真结果表明,燃油伺服等压差控制系统静态误差为0,动态调节时间不大于0.01 s,超调量不大于10%,相角裕度大于45°,正弦波动输入信号的干扰下具有鲁棒抗干扰性能。In response to the difficulties in the forward design of hydraulic mechanical servo systems,the basic concept and theory of controllable flow paths in hydraulic mechanical servo systems are proposed.By estab⁃lishing a state space model,using closed-loop system analysis method and the concept of controllable flow paths in hydraulic mechanical servo systems,two basic design methods of controllable flow paths for single cavity and series dual cavity are proposed.On this basis,taking the forward design of a fuel servo constant pressure drop control system as a typical example,a systematic design is carried out using the proposed design method for con⁃trollable flow paths.The simulation results show that the static error of the fuel servo constant pressure drop con⁃trol system is 0,the dynamic settling time is less than 0.01 s,the overshoot is less than 10%,and the phase mar⁃gin is greater than 45°.The system has robust disturbance rejection performance under the interference of input signals with sinusoidal fluctuation.

关 键 词：航空发动机 燃油伺服系统 液压机械压力伺服 可控流路设计 状态空间 等压差控制 

分 类 号：V233.91[航空宇航科学与技术—航空宇航推进理论与工程]