This paper is devoted to an experimental work which consists of the analysis of the flame of a small solid propellant sample, AP/Al/HTPB, subjected to a longitudinal acoustic wave. Experiments were conducted in a closed tube under two mean pressures: 1 and 2.5 MPa. The qualitative and quantitative analysis of the flame snapshots, using a microscope and a high-speed camera, revealed that the acoustic wave created at the end of the chamber by a pulser system strongly affects the flame and the combustion products dynamic above the solid propellant surface, namely, the flame and the hot products oscillate around a line perpendicular to the propellant surface. This dynamic of the hot gas disturbs the local burning rate and the regression surface profile. Thus, the thrust and the burning duration will change, therefore, the flight path of the rocket may shift and can lead to failure of the mission.

中文翻译：

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固体推进剂AP / Al / HTPB对纵向声波的火焰响应

本文致力于一项实验工作，该工作包括分析小型固体推进剂样品AP / Al / HTPB在纵向声波作用下的火焰。在密闭管中在两种平均压力下进行实验：1和2.5 MPa。使用显微镜和高速相机对火焰快照进行定性和定量分析，结果表明，脉冲发生器在燃烧室末端产生的声波会​​强烈影响固体推进剂表面上方的火焰和燃烧产物的动态即，火焰和热产物围绕垂直于推进剂表面的线振荡。热气体的这种动态干扰了局部燃烧速率和回归表面轮廓。因此，推力和燃烧持续时间将发生变化，因此，