固体火箭技术2025，Vol.48Issue(2)：195-204,10.DOI:10.7673/j.issn.1006-2793.2025.02.004
燃面突变脉冲触发固体火箭发动机不稳定燃烧的数值模拟
Numerical simulation of the combustion areapulse-triggered unstable combustion in solid rocket motors
魏家琛 1范文琦 1王兵1
作者信息
- 1. 清华大学 航天航空学院,北京 100084
- 折叠
摘要
Abstract
To investigate the triggering and driving mechanisms of the combustion instabilities of solid rocket motors,atriggering mechanism concerning combustion areapulse was proposed based on the heterogeneous combustion characteristics of composite pro-pellants.The numerical model of the mass flow rate on combustion surface of solid propellants and an equivalent numerical model of combustion area pulse-triggering were established based on combustion response functions.A numerical simulation study on the un-stable combustion of solid rocket motors triggered by combustion surface pulse was conducted.The results indicate that for the stud-ied model,the combustion area pulse can trigger unstable combustion,resulting in pressure oscillations primarily characterized by the first-order axial mode in the combustion chamber.The propellant parameters,such as the combustion response functions and pressure exponent,have a significant impact on unstable combustion,and the decrease of these values can effectively suppress unstable com-bustion.The increase in the probability and intensity of the combustion area pulse significantly shortens the time for the pressure os-cillation to reach the limit cycle.The aluminum powder in propellants exhibits a significant influence on particle damping effects dur-ing unstable combustion.The numerical simulation results validate the proposed physical mechanism and provide a feasible method for suppressing unstable combustion based on this mechanism.关键词
固体火箭发动机/复合推进剂/燃面突变脉冲/不稳定燃烧/数值模拟Key words
solid rocket motor/composite propellant/combustion areapulse/unstable combustion/numerical simulation引用本文复制引用
魏家琛,范文琦,王兵..燃面突变脉冲触发固体火箭发动机不稳定燃烧的数值模拟[J].固体火箭技术,2025,48(2):195-204,10.
