多组分二硝酰胺铵（ADN）基液体推进剂，包括氧化性组分ADN，还原性组分甲醇，以及溶剂水。ADN基液体空间发动机的反应过程包括液体推进剂雾化、蒸发，催化床多孔介质内催化分解、以及燃烧室内高室压燃烧等多个特征过程。但目前还缺乏相关的实验研究和理论、数值模拟分析。本项目以液体ADN 基空间发动机的实现作为研究背景，研究ADN基液体推进剂催化分解及高压燃烧的多参数耦合过程。通过实验研究，获得催化剂形貌变化、燃烧压力、预热温度变化等影响因素与特征组分浓度、燃烧放热率等流场参数的相互关系；通过实验研究、理论分析和数值计算，探索发动机脉冲工作条件下高压燃烧过程中多流场参数的脉动耦合关系。研究结果对于理解包含多孔介质化学反应过程的高压燃烧机制、发展新型液体推进剂的燃烧反应动力学机理具有重要理论意义。

The ADN(Ammonium Dinitramide)-based liquid propellant contains the ADN as the oxidizer, the methanol as the fuel, and the water as the solvent. The reaction processes of the ADN-based liquid aerospace thruster contain the atomization and evopration of the liquid propellant, the catalytic decomposition in the porous media, and the high-pressure combustion in the combustion chamber as the multi-parameter coupling relationships. However, there are only few related theoretical, numerical, and experimental works about it. Taken the.ADN-based liquid aerospace thruster as the industrial background,this project investigates the multi-parameter coupling relationships in the catalytic decomposition and high-pressure combustion of the ADN-based liquid propellant. Through experimental investigations, the influences of the catalyst profile, combustion pressure, combustion temperature on the species concentrations, and the heat release rate are obtained. Co upled with numerical calculation and experimental investigation, the pulsed coupling relationships of the flow field.parameters in the high-pressure combustion under pulsed pressure boundary conditions are obtained. These results are valuable for a better understanding of the combustion mechanisms of the high-pressure combustion which includes porous media, which is beneficial to the development of high preformance aerospace propulsion techniques.