冲压发动机线性动力学

70年代在超音速进气道动态建模中提出分段集总参数建立子系统的传递函数,并以串联系统的传递矩阵方法求解进气道结尾正激波位置的频响函数,此法较适用,并得到NASA 48cm进气道的实验验证。管彦深教授扩展了此法的应用。 

LINEAR DYNAMICS OF SUPERSONIC RAMJET

This paper presents a mathematical model of a supersonic ramjet.The basic thermoaerodynamical equations of ramjet components are linearized in conformity with small perturbation.Then the transfer functions of the components are deduced on the S domain.With the method of subsystem in series,the dynamical mathematical model of the ramjet with the inlet normal shock position,the parameters along duct and thrust is formulated under the perturbation of upstream Mach number,temperature,pressure and downstream fuel flow rate of the ramjet.A numerieal example of digital imitation of a real ramjet is completed and gives reasonable results.