高超声速超燃冲压发动机实时模型仿真研究  

Simulation of hypersonic scramjet engine real-time model

作　　者：刘明磊[1] 张海波[1] 

机构地区：[1]南京航空航天大学能源与动力学院,南京210016

出　　处：《航空动力学报》2017年第6期1447-1455,共9页Journal of Aerospace Power

基　　金：国家自然科学基金(51576096);江苏省"青蓝工程";"333"人才工程;南京航空航天大学研究生创新基地(实验室)开放基金(kfjj20160212)

摘　　要：给出了一种高超声速超燃冲压发动机实时模型建立方法.发动机采用基于特性的部件级建模思想,考虑了燃烧室的容积效应,其中,在计算进气道参数时给出一种计算激波角的方法,该方法能够一次得到激波角,不需数值解法,在保证精度的同时简化了计算过程.该发动机动态模型通过数值积分来完成,避免了循环迭代,提高了模型计算速度与实时性.以某超燃冲压发动机建模为例,通过闭环仿真实验得到在动态过程中响应时间在1s左右,超调量为0.5%.仿真结果表明:该建模方法满足提高实时性的要求,有助于对此类发动机动态过程进行控制研究.A method for establishing a hypersonic scramjet engine real-time model was presented.The engine model adopted the component level model based on characteristics,considering volume dynamics of the combustion chamber,and a method for calculating shock angle in the calculation of inlet parameters was given,enabling to get the shock angle at one time without numerical solution and simplify the calculation process with better accuracy.The engine model was completed by means of numerical integration,iteration was avoided with high speed of the model.Taking the modeling of a certain model as an example,the response time was about 1 s and the overshoot was 0.5 % in the dynamic process by close loop simulation experiment.Simulation results demonstrate that the modeling method meets the requirement of improving real-time performance and contributes to the dynamic process of such engine control study.

关 键 词：超燃冲压发动机 实时模型 容积动力学 稳态特性 动态特性 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]