摘要
为研究固体火箭发动机点火过程喷管内强瞬态流场演化机理,建立了强瞬态流动数值计算模型,根据是否考虑堵盖运动,研究了地面背压(100 kPa)和高空低背压(10、1 kPa)环境下的流场演化行为。结果表明:背压的降低有利于流场扩展与燃气膨胀,背压从100 kPa降低至1 kPa时,初始扰动波传播速度升高了2倍,分离激波运动速度升高了约15倍,喉部壅塞时刻提前了87.5%;低背压环境下,流动分离区涡结构尺度明显较小;涡结构的形成是由于流动分离后超声速射流对分离区内燃气的自由剪切作用而引起的;堵盖运动过程对于流场演化非常重要;在流场演化前期与低背压环境时,堵盖对流场扩展的影响不可忽略;同时,堵盖动力学行为受背压影响较大。
In order to research the evolution mechanism of strong transient flow during solid rocket motor ignition,a numerical model of strong transient flow was established.Based on whether to consider the closure movement,the evolution behavior of strong transient flow field under ground back pressure and high-altitude low back pressure environments was studied.The results show that the decrease of back pressure is beneficial to flow field evolution and gas expansion.When the back pressure decreases from 100 kPa to 1 kPa,the velocity of disturbance wave propagation increases by 2 times,the velocity of the separating shock wave movement increases by about 15 times,and the moment of throat choking occurs 87.5%earlier.The vortex structure of the flow separation region is significantly smaller in low back pressure environments,and the generation of vortex structure is due to the free shear layer of supersonic jet after flow separation.The closure movement is very important to the evolution of flow field.In the early stage of flow field evolution and low back pressure environments,the influence of closure on flow field cannot be ignored.At the same time,the closure dynamic behavior is greatly affected by the back pressure environments.
作者
王琪虎
王亚军
褚佑彪
何雨壕
龙玥霄
王嘉炜
WANG Qihu;WANG Yajun;CHU Youbiao;HE Yuhao;LONG Yuexiao;WANG Jiawei(The Institute of Xi'an Aerospace Solid Propulsion Technology,Xi'an 710025,China;China Academy of Aerospace Electronics Technology,Beijing 100094,China)
出处
《固体火箭技术》
北大核心
2025年第6期834-842,共9页
Journal of Solid Rocket Technology
关键词
固体火箭发动机
背压环境
喷管流场
流动演化
强瞬态特性
solid rocket motor
back pressure
flow field of nozzle
evolution of flow field
strong-transient characteristic
