高过载条件下固体火箭发动机绝热层失效研究  

Investigation on abnormal insulator erosion under high flight acceleration load

作　　者：乐发仁[1] 冯喜平[1] 武渊[1] 姜正乾[1] 

机构地区：[1]中国航天科技集团公司四院设计部,西安710025

出　　处：《固体火箭技术》2005年第1期33-35,共3页Journal of Solid Rocket Technology

摘　　要：根据化学反应 /两相流耦合,建立了铝粒子燃烧模型,通过化学反应速率模型的模化湍流燃烧,对含铝推进剂固体火箭发动机在高过载条件下的内流场进行数值研究。结果表明,过载条件下燃烧室局部异常铝滴积聚及剧烈的化学放热反应是导致绝热层异常烧蚀的主要原因。Based on chemical reaction / two-phase flow coupling, combustion model of aluminum particle was established. By means of turbulence combustion in chemical reaction rate model, internal flow field of aluminized solid propellant rocket motor was numerically investigated under the high acceleration condition. The results show that aluminum particle abnormal accumulation on local position of the chamber and severe chemical exothermic reaction are the main reason resulting in abnormal insulator erosion under the high acceleration condition.

关 键 词：固体火箭发动机 绝热层 高过载 失效 化学反应 含铝推进剂 燃烧模型 湍流燃烧 速率模型 数值研究 放热反应 局部异常 两相流 铝粒子 内流场 燃烧室 烧蚀 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程] V435.14