含能材料2025，Vol.33Issue(8)：867-881,15.DOI:10.11943/CJEM2025056
丁羟四组元推进剂细观异质结构燃烧响应理论模型
Theoretical Model of Combustion Response for Four-component Hydroxyl-terminated Polybutadiene Propellant with Microcosmic Heterostructure
摘要
Abstract
To optimize the combustion performance of solid propellants and enhance the combustion stability of solid rocket mo-tors(SRMs),an integrated combustion response model for four-component hydroxyl-terminated polybutadiene(HTPB)propel-lant with microcosmic heterostructure is established.The improved combustion model that considers the microstructure of four-component propellants is developed based on the heterogeneous quasi one-dimensional(HeQu1-D)framework,incorpo-rating both the micro-scale heterogeneous structure and the unsteady heat transfer process.The model is well verified against ex-perimental data from T-burner tests,with a maximum error of 5.34%in combustion response.Furthermore,the effects of compo-nent content distribution,particle sizes,and external environmental conditions are investigated under a working pressure of 12 MPa and excitation frequencies ranging from 250 to 2000 Hz.The results demonstrate that adjusting the particle sizes of AP and NA can significantly alter the propellant′s combustion response characteristics,where smaller AP particles combined with larger NA particles are more conducive to stable combustion.Regarding component content,increasing the relative proportion of AP helps reduce the pressure-coupled response function of propellant.When 10%of AP is replaced with RDX,the pressure-coupled response function exhibits a peak-value increase of 0.15 accompanied by a 25 Hz reduction in peak frequency.More pronounced effects are observed with HMX,where the same 10%of AP replacement leads to a greater peak value en-hancement of 0.43 and a more substantial peak frequency decrease of 85 Hz.This work contributes to understanding the mecha-nism of combustion instability and provides guidance for efficient optimization of propellant formulations.关键词
不稳定燃烧/丁羟四组元推进剂/细观异质结构/压力耦合响应函数Key words
combustion instability/four-component hydroxyl-terminated polybutadiene propellant/microcosmic heterostructure/pressure-coupled response function分类
军事科技引用本文复制引用
王茹瑶,李军伟,王小东,曹俊维,李强,王宁飞..丁羟四组元推进剂细观异质结构燃烧响应理论模型[J].含能材料,2025,33(8):867-881,15.基金项目
国家自然科学基金(22027811) National Natural Science Foundation of China(No.22027811) （22027811）
