为了验证在碳氢燃料冲压发动机完全燃烧气体中加入镁粉二次燃烧以提升发动机推力性能方案的可行性，搭建了粉末增强型直连式冲压发动机试验系统。在模拟Ma6.0和30km飞行条件下开展了发动机试验，并通过改进推力测量方法来获得粉末超燃冲压发动机燃烧室推力和燃烧性能参数。试验围绕发动机方案可行性、粉/燃气比以及粉末滞留距离对推力性能的影响展开研究。结果表明：该方案具备可行性。镁粉主要与发动机燃气中水蒸气和二氧化碳反应，且水蒸气占主导。在喷注13%镁粉时发动机比推力增益达到了86.6%，对应燃烧效率为65.1%。综合考虑发动机尺寸与发动机性能时，粉末滞留距离与燃烧室总长比建议设计在0.62附近。
To evaluate the feasibility of enhancing thrust performance in hydrocarbon-fueled scramjet engines through sec-ondary combustion by injecting magnesium powder to fully combusted exhaust gases, a powder-enhanced direct-connect scramjet experimental system was developed. Experiments were conducted under simulated flight condi-tions of Mach 6.0 at an altitude of 30 km. An improved thrust measurement method was employed to obtain the thrust and combustion performance parameters of the powder-based scramjet combustor. The study focused on the feasibility of the powder enhanced scramjet, the effects of the powder-gas ratio, and the powder residence distance on thrust performance. Results demonstrated the viability of the proposed scheme, with magnesium powder primari-ly reacting with water vapor and carbon dioxide in the exhaust gases, where water vapor was the dominant reactant. When 13% magnesium powder was injected, the engine achieved a specific thrust gain of 86.6% and a combustion efficiency of 65.1%. Considering both engine size and performance, it is recommended to design the powder resi-dence distance-to-combustor length ratio around 0.62.
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