Abstract: This paper carried out afterburning experiments on solid hydrocarbon propellant ATR, which explored the afterburning chamber stable working conditions with the air flux at room temperature. Experiment equipment, especially for the afterburning study, was built up to examine the turbine simulator and explore solid hydrocarbon propellant ATR afterburning characteristics with simple mixture. Three main conclusions were drawn. Firstly, under experiment condition above, the afterburning could not be carried out in the superior specific impulse equivalence ratio. So, in the ATR engine coefficients designing process, both specific impulse performance and the ignitability should be taken into consideration. Secondly, under the experiment condition with corresponding used solid hydrocarbon propellant, the afterburning could only be carried out stably not higher than the equivalence ratio 4.4. Thirdly, since the combustion efficiency was not satisfied in the simple mixing mode, there should be much more attention paid on the exploration in the flame holder and superior mixing device for the solid hydrocarbon propellant. 

Key words: Solid hydrocarbon propellant air turbocharged rocket; Afterburning;Ignitability;Combustion efficiency

摘要： 为了探索常温来流条件下补燃室稳定燃烧的工作条件,设计并加工了一套专门用于研究掺混燃烧的试验装置,验证了模拟落压机构的效果,探索了只有简单掺混器状态下碳氢推进剂的二次燃烧特性。实验发现,只有简单掺混装置的情况,在比冲较优空燃比状态下未能实现二次燃烧,因此在发动机参数设计中不仅要考虑比冲性能还要兼顾可燃条件；实验中采用的固体碳氢推进剂在直接掺混方式下稳定燃烧的空然比上限为4.4左右；简单掺混方式燃烧效率不理想,今后需要探索适合碳氢燃料的火焰稳定器和增强掺混燃烧方法。 

关键词: 固体燃气涡轮火箭发动机;二次燃烧;点火条件;燃烧效率 