整体式固体火箭冲压发动机转级过程数值仿真  

Numerical Simulation of Transition Process of Integral Solid Propellant Ducted Rockets

作　　者：何勇攀[1,2] 陈玉春[1] 李立翰[2] 

机构地区：[1]西北工业大学动力与能源学院,陕西西安710072 [2]中国航天科工集团三十一研究所,北京100074

出　　处：《计算机仿真》2015年第3期119-122,152,共5页Computer Simulation

摘　　要：为了研究整体式固体火箭冲压发动机从助推级向冲压发动机级的工况转换(转级)过程,采用双时间步推进方法,求解非定常、三维、有化学反应的Navier-Stokes方程组,得到了发动机进气道/燃烧室一体化流场在转级过程中的变化情况,分析了相关因素对转级过程的影响。仿真研究表明,进气道出口堵盖打开前,进气道内气流保持压力振荡状态,振荡频率主要与飞行高度相关;堵盖打开后,空气与一次燃气进入补燃室掺混并燃烧,过程中发动机内流场发生剧烈的变化;堵盖打开时燃烧室内的压力对于进气道的起动至关重要。上述研究对于整体式固体火箭冲压发动机设计具有指导意义。In order to investigate the mode transition process from boost to ramjet of the solid propellant ducted rocket（SPDR）,unsteady,3-dimensional Navier-Stokes Equations with chemical reaction are solved in this paper,by using the dual-time stepping method. Evolution of the integrated flow field of inlet and combustor is obtained,and the impact of related factors on the transition process is analyzed. Results show that,before the inlet port cover is opened,the pressure of inlets is oscillating,and the frequency of the oscillation is mainly associated with flight height. When the inlet port cover is opened,air and gas get inside the combustion chamber,mixing and combusting,accompanied by a drastic change of the flow field. The pressure in the combustion is essential to the start of the inlet in the transition process.

关 键 词：固体火箭冲压发动机 转级过程 数值仿真 

分 类 号：V235.213[航空宇航科学与技术—航空宇航推进理论与工程]