补燃室结构对固冲发动机二次燃烧影响试验研究  

Experimental research on effects of combustor structure on solid ducked rocket secondary combustion

作　　者：程吉明 李进贤[1] 钱程远[1] 冯喜平[1] 朱国强[1] 杨玉新[2] 

机构地区：[1]西北工业大学燃烧、热结构与内流场重点实验室,西安710072 [2]中国航天科技集团公司四院四十一所,西安710025

出　　处：《固体火箭技术》2014年第5期645-649,共5页Journal of Solid Rocket Technology

基　　金：总装预研基金(9140A28030211HK0315)

摘　　要：为了研究含硼推进剂固冲发动机补燃室结构对二次燃烧点火特性和稳态燃烧性能的影响,选择头部距离、补燃室长度和空气入射角度作为结构设计参数,设计了模块化固冲发动机地面试验装置。基于正交试验原理安排试验方案,并开展地面直连试验。试验结果的极差分析表明,结构因素对二次燃烧点火延迟时间影响由强到弱依次为补燃室长度>空气入射角度>头部距离,对二次燃烧效率影响由强到弱依次为头部距离>补燃室长度>空气入射角度。方差分析表明,补燃室结构因素对点火延迟影响不显著,头部距离对二次燃烧效率影响作用较显著,其他因素对燃烧效率影响作用有限。In order to understand how combustor structure affects the secondary ignition and combustion characteristics of solid ducked rocket （ SDR） with boron based propellant, dome height, combustor chamber length and side arm angels were selected as structural design parameters and the modular ground test devices of SDR were designed. The experimental scheme was arranged based on orthogonal design theory and the ground direct-connection tests of SDR were carried out. The range analysis of the results shows that structural factors that affect combustor ignition delay from strong to weak is followed by combustor chamber length〉side arm angels〉dome height.Structural factors that affect secondary combustion efficiency from strong to weak is followed by dome height〉combustor chamber length〉side arm angels.The analysis of variance （ANOVA） shows that all the selected structural factors have little influence on combustor ignition delay.Dome height has a significant effect on secondary combustion efficiency,while the other two factors have limited influence on secondary combustion efficiency.

关 键 词：固冲发动机 正交设计 补燃室结构 二次燃烧 点火延迟时间 

分 类 号：V438[航空宇航科学与技术—航空宇航推进理论与工程]