Abstract: Using П micro thermalcouple,copper stage guenched sample, SEM, flame color photography technics,we had studied combustion phenomenon for typical modified double base propellants. From the results we have put forward a hypothesis that the bubbles stretched from the combustion catalyst could enhance solid heat release, which results in superburning at low pressures , and the foam layer would be unburned propellant risiduals resulted from bubbles.Using a numerical calculation method for analyzing combustion wave structure of solid rocket propellants,we can get the detail information of chemical reactions in the condensed phase.There would be no condensed gas interface, and the surface temperature would be no meaning.The results show that there would be multi stage reaction mechanism in solid phase and that the reaction mechanism would be the same in condensed phase at different pressures, only the reaction heat release value would be different.

Key words: Solid propellant rocket engine;Modified double base propellant;Combustion test;Combustion wave;Quench

摘要： 采用П形微热偶、铜台熄火、扫描电镜、单幅火焰照相等技术， 研究了改性双基推进剂催化燃烧特征，用以催化剂为中心的气泡理论，解释了催化剂产生超速燃烧的机理。发现催化燃烧推进剂燃烧表面不均匀，高压下泡沫区比低压下细密而长，泡沫区的物质为未燃烧推进剂；更高压力下泡沫区的消失导致平台燃烧区的出现等现象。还提出了均质推进剂固相多反应机理， 并指出压力不同固相反应机理基本相同， 但固相放热程度不同

关键词: 固体推进剂火箭发动机;改性双基推进剂;燃烧试验;燃烧波;淬火