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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 carbonization layer of EPDM insulation material was prepared by using a carbonization layer sample preparation device simulating solid rocket engine ablation environment. The carbonized layer structure of EPDM insulation material was analyzed. A set of particle erosion device was designed. The erosion angle was 30 °, 60 ° and 90 ° conditions of the EPDM carbonization layer particle erosion damage test, the use of high-speed photography system records particles eroded carbonization process, calculated through the analysis of the carbonized layer shear ultimate strength And compressive ultimate strength, the mechanical properties parameters of the carbonized layer are provided for establishing the ablation model of the thermal insulation materials under the airflow and particle erosion.