Unsteady flow after the opening of the inlet cover of integral liquid-fueled ramjet engine and the separating of booster were investigated numerically. The overset/Chimera algorithm for structured grids were employed. The Roe scheme was used in finite volume method to solve unsteady Navier-Stokes equations. The simulation results , presented in Figs. 5 、 6 and 7, and their analysis show preliminarily that: ( 1 ) after the inlet cover was opened, the high speed air flow began to fill ramjet channels, the detached bow shock moved to inlet cowl, and the structure of shock was established and the filling air moved to ramjet outlet at local sound speed; (2) The booster began to separate when the high pressure air moved to the head of booster; the separation time was 0.0722 seconds ; (3) throughout the time of separation, the pressure of ramjet chamber fluctuated greatly.%应用数值方法对整体式液体冲压发动机进气道整流罩打开及助推器分离过程进行了研究.动网格采用结构网格中的Chimera重叠网格技术,空间离散格式采用Roe格式,控制方程采用雷诺平均N-S方程,湍流模型为标准k-ε模型.计算结果发现,进气道整流罩打开后高速气流开始充填发动机内通道,发动机头部脱体激波迅速向唇口方向移动,进气道头部斜激波系建立,气流以当地声速向发动机出口方向移动.高压气流到达助推器头部时助推器开始分离,整个分离过程燃烧室压力呈大幅振荡,分离时间为0.0722 s.由于分离时间很短,冲压发动机可以在助推器推出后再点火起动.
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