固体火箭冲压发动机二次燃烧试验研究  

Experimental research on secondary combustion of solid ducted rockets

作　　者：黄利亚[1] 夏智勋[1] 陈斌斌[1] 

机构地区：[1]国防科技大学航天科学与工程学院,长沙410073

出　　处：《固体火箭技术》2017年第5期552-556,共5页Journal of Solid Rocket Technology

基　　金：国家自然科学基金青年基金(51406231)

摘　　要：针对某工程论证需求,分别采用缩比和全尺寸固体火箭冲压发动机,利用地面直连试验系统,开展了壅塞式固体火箭冲压发动机试验研究,采用燃烧效率和试验比冲作为评价指标,对比分析了燃气发生器进气方式与喷嘴结构、空燃比、燃气流驻留时间、尺寸效应等因素对发动机二次燃烧性能的影响。结果表明,设计的一次进气发动机能够实现高效燃烧;在测试范围内,空燃比增大发动机燃烧效率降低;延长燃气驻留时间,提高了发动机二次燃烧性能。A scaled-down and a full-size engine were both employed to experimentally study the solid ducted rockets with a ground direct-connected test system.Based on combustion efficiency and experimental specific impulse,influences on the secondary combustion performance of different factors,such as atomizer structure,air/fuel ratio,gas residence time and size effect,were analyzed.The results of experiments show that,high combustion efficiency can be reached for a ducted rocket with an individual air injection.As the air/fuel ratio increases,the combustion efficiency has been improved within the test range.The extension of gas residence time would enhance the secondary combustion performance of the ducted rockets.

关 键 词：固体火箭冲压发动机 含硼富燃料推进剂 壅塞式 二次燃烧 试验 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]