粒子侵蚀下三元乙丙绝热材料炭化层破坏特性实验研究  

EXPERIMENTAL STUDY ON THE BREAKAGE CHARACTERISTIC OF CHARRING LAYER OF EPDM HEAT-INSULATING MATERIAL ERODED BY PARTICLE FLOW

作　　者：徐义华[1,2] 胡春波[1] 李江[1] 

机构地区：[1]西北工业大学燃烧流动及热结构重点实验室,西安710072 [2]南昌航空大学飞行器工程学院,南昌330063

出　　处：《工程力学》2011年第5期251-256,共6页Engineering Mechanics

基　　金：国家自然科学基金项目(50976095);国家"973"基金项目(61371)

摘　　要：应用模拟固体火箭发动机烧蚀环境的炭化层制样装置制备三元乙丙绝热材料炭化层,分析了三元乙丙绝热材料炭化层结构特点,并设计了一套粒子侵蚀装置,对侵蚀角度为30°、60°和90°工况进行了三元乙丙绝热材料炭化层的粒子侵蚀破坏试验,应用高速摄影系统记录粒子侵蚀炭化层过程,经过分析计算得出了炭化层的剪切极限强度和抗压极限强度,为建立气流和粒子冲刷下的绝热材料烧蚀模型提供炭化层的力学性能参数。The device which can simulate the thermal ablation in a solid rocket motor was used to make the sample of charring layer of Ethylene-Propylene-Diene Monomer（EPDM） heat-insulating material.The structure characteristics of charring layer were analyzed.A suit of device used for researching particle eroding charring layer of heat-insulating material was designed.It is carried out three tests of particle eroding EPDM charring layer with the erosion angles of 30°,60° and 90°,respectively.The process of erosion is recorded by high-speed camera.The velocity of eroding particle is gained by analyzing the image.The force particle acting on the charring layer is computed by the law of momentum.The limiting shearing and crushing stress is derived by comparing the testing data,which can be applied to the model ablation of EPAM under considering the eroding effect of gas and particle.

关 键 词：航天推进系统 固体火箭发动机 粒子侵蚀 EPDM 炭化层 破坏特性 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]