固体火箭冲压发动机二次燃烧试验研究

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。

Experimental research on secondary combustion of solid ducted rockets

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 ana-lyzed. The results of experiments show that, high combustion efficiency can be reached for a ducted rocket with an individual air in-jection. As the air/fuel ratio increases, the combustion efficiency has been improved within the test range. The extension of gas resi-dence time would enhance the secondary combustion performance of the ducted rockets.