Abstract: A series of model rocket engine combustion experiments were conducted in order to investigatethe combustion characteristics of slurry propellant containing aluminum particles. The fuels used were traditionalliquid JP-10，JP-10-based slurry with 21-wt% loadings of nano-sized aluminum particles and JP-10-basedslurry with 12-wt% loadings of micro-sized aluminum hydride composite particles. The differences in the com.bustion characteristic between the slurry and the pure fuel were analyzed. The oxygen-to-fuel ratios were set tobe 1.6～2.0. The results showed that compared with pure JP-10，the JP-10-based slurries presented obviously lower mass specific impulse and combustion efficiency，due to the special aggregation phenomenon of metal parti.cles in the process of atomization and combustion. However，the JP-10-based slurries achieved a higher density specific impulse by 5.5% to 14.6% compared to pure JP-10，because the metalized propellant has higher density.It was also found that the ignition delay of the slurry fuels was slightly shorter than that of the pure JP-10 fuel and it proved that the addition of metal particles has a positive effect on the propellant ignition performance. In addi.tion，condensed combustion products are sampled in the jet plume behind the exit nozzles to analyze the compo.nents of products. By means of the energy dispersive spectrometer(EDS)，X-ray diffraction(XRD)，scanning electron microscope(SEM)，and transmission electron microscope(TEM)，it was found that 64%～74% alumi. num was oxidized in the tests，and the solid particles are mainly spherical and in size of 500nm～3mm.

Key words: Slurry fuels； Combustion characteristic； Rocket engine； Experimental study； Aluminum particle

摘要： 为研究含铝浆体推进剂的燃烧特性，对浆体推进剂模型火箭发动机开展了一系列试验研究。分别将质量分数为 21%的纳米铝粉颗粒以及质量分数为 12%的氢化铝复合粒子加入到 JP-10燃料中，对比分析了浆体燃料与纯净燃料在燃烧性能方面的差异。燃烧试验的氧燃比为 1.6～2.0。试验结果表明:与纯净 JP-10燃料相比，加入金属颗粒的 JP-10浆体燃料在雾化和燃烧过程中产生了严重的结块聚集效应，导致其燃烧效率与质量比冲明显降低，而由于浆体燃料密度远大于纯净 JP-10燃料，含纳米铝颗粒的浆体燃料的密度比冲相比于纯净 JP-10燃料有大幅提高，提高幅度为 5.5%～14.6%。试验还发现浆体燃料的点火延迟略低于纯净 JP-10燃料，金属颗粒的加入对推进剂点火性能有积极的影响。试验中采集了喷管出口的固体燃烧产物并进行了 XRD，EDS，SEM，TEM等多种手段分析，发现浆体燃料中铝的氧化率约为 64%～74%，颗粒团聚现象明显，主要呈球形，尺寸分布不均，约为 500nm～3μm。

关键词: 浆体推进剂；燃烧性能；火箭发动机；试验研究；铝粉颗粒