双脉冲固体发动机燃烧室EPDM绝热层烧蚀性能实验研究  

Experimental Study on Ablation Performance of EPDM Insulation Layer in Combustion Chamber of Dual Pulse Solid Rocket Motor

作　　者：闫航 陈嘉辉 冯喜平[1] 王乐[1] 侯晓[1] YAN Hang;CHEN Jia-hui;FENG Xi-ping;WANG Le;HOU Xiao(Science and Technology on Combustion,Internal Flow and Thermo-Structure Laboratory,Northwestern Polytechnical University,Xi’an710072,China)

机构地区：[1]西北工业大学燃烧、热结构与内流场重点实验室,陕西西安710072

出　　处：《推进技术》2022年第8期225-235,共11页Journal of Propulsion Technology

摘　　要：为了研究双脉冲发动机燃烧室内复杂热环境下三元乙丙(EPDM)绝热层的烧蚀性能,开展了工作时间为15s和两次点火工作时间为7.5s+7.5s的发动机实验。采用SEM电镜扫描、微米CT测试分析获得了烧蚀试件的表面宏观形貌、炭化层表面和断面微观形貌以及炭化层三维构型;利用测厚仪测量结果计算了试件的烧蚀率。结果表明,在总工作时间相等的情况下,双脉冲发动机中EPDM绝热层的烧蚀率比传统发动机大。与传统发动机中单次热冲击下烧蚀后试件相比,双脉冲发动机二次热冲击下烧蚀后试件的炭化层厚度减小约50%,总体孔隙率增大约13%;烧蚀表面致密层的致密程度也有所减小。双脉冲发动机工作时,EPDM绝热层的烧蚀性能在二次热冲击下发生较大变化,需在燃烧室内绝热层的设计过程中予以重视。In order to study the complicated ablation performance of EPDM insulation in the combustion chamber of a double-pulse solid rocket motor,an engine experiment scheme with working time of 15s and two ig⁃nition of 7.5s+7.5s was proposed.The surface morphology of the ablation specimen,the surface and section mor⁃phology of the carbonized layer and the three-dimensional configuration of the carbonized layer were obtained by SEM scanning and micron CT testing.The ablation rate of the specimen was calculated by the measurement results of the thickness gauge.The results show that the ablation rate of the EPDM insulation is higher than that of the con⁃ventional engine under the same total working time.Compared with the specimens in the traditional engine after a single thermal shock,the thickness of carbonization layer decreases by 50%and the overall porosity increases by 13%because of the double pulse engine after a second thermal shock.The density of the dense layer on the ablation surface also decreases.The ablation performance of EPDM insulation varies greatly under the secondary ther⁃mal shock when the double-pulse engine is in operation,which should be paid more attention to in the design process of the insulation in the combustion chamber.

关 键 词：双脉冲发动机 固体火箭发动机 燃烧室 绝热层 烧蚀 实验研究 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]