双脉冲发动机点火过程数值模拟  

Numerical simulation on the ignition process of dual pulse motor

作　　者：朱亮 田小涛 李映坤 邓恒[1] 宋军[1] ZHU Liang;TIAN Xiaotao;LI Yingkun;DENG Heng;SONG Jun(Xi'an Modern Control Technology Research Institute,Xi'an710065,China;School of Mechanical Engineering,Nanjing University of Science and Technology,Nanjing210094,China)

机构地区：[1]西安现代控制技术研究所,西安710065 [2]南京理工大学机械工程学院,南京210094

出　　处：《固体火箭技术》2021年第6期773-782,共10页Journal of Solid Rocket Technology

基　　金：国家自然科学基金(No.52006099)。

摘　　要：双脉冲发动机第二脉冲点火过程较传统固体火箭发动机呈现出较大不同,为研究双脉冲发动机第二脉冲点火瞬态特性,基于有限体积法求解雷诺时均Navier⁃Stokes方程组,采用高精度AUSMPW+迎风格式,3阶MUSCL重构方法,k⁃ωSST湍流模型并耦合求解固相热传导方程,编制了计算程序,并利用相关实验验证了数值方法的可靠性。在此基础上,研究了第二脉冲点火瞬态特性,清晰刻画了点火阶段火焰传播过程,并得到了双脉冲发动机第二脉冲点火瞬态流场特征及燃烧室建压历程。计算结果显示,双脉冲发动机第二脉冲点火瞬态过程相比常规固体火箭发动机呈现出较大区别。此外,研究了点火药量、推进剂燃速及隔离装置强度对点火延迟的影响。研究结果表明,提高点火药量能有效缩短推进剂首次点燃时间及点火延迟时间,在一定程度上能改善发动机点火性能;采用高燃速推进剂能显著缩短发动机点火延迟时间,对提高发动机点火性能作用较大;隔离装置强度总体上对点火性能没有影响。There exist differences between the second pulse ignition process of dual pulse motor and the conventional solid rock⁃et motor.Characteristics of the second pulse ignition transient process was investigated by using high resolution upwind scheme AUSMPW+,3 order MUSCL reconstruction method and k⁃ωSST turbulence model with solving the solid state heat transfer equa⁃tions,where the unsteady Reynolds⁃average Navier⁃Stokes(RANS)equations was solved based on the finite volume method.The code was developed and then validated by related experimental case.The flame propagation process was depicted clearly.The fea⁃tures of the transient flow and the combustion chamber pressure build⁃up history were also obtained.The results show that the sec⁃ond pulse ignition transient process of dual pulse motor displays great differences from that of conventional solid rocket motor.Fur⁃thermore,the effects of ignition mass,propellant burning rate and the strength of the pulse separation device on ignition delay are studied.The results indicate that the first ignition time and ignition delay time can be shortened effectively by increasing the ignition mass,resulting in some improvement of the ignition performance.The ignition delay time can be also effectively shortened by in⁃creasing the propellant burning rate which has significant influence on improving the ignition performance,whereas the ignition per⁃formance can be hardly affected by the strength of pulse separation device.

关 键 词：双脉冲发动机 点火瞬态 计算流体力学 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]