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

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