一种典型C/SiC构型件的热噪声适应性试验研究  

Experimental research of thermal-acoustic adaptability of a typically-configured C/SiC specimen

作　　者：王晓飞[1] 王圣刚[1] 麻连净[1] WANG Xiaofei;WANG Shenggang;MA Lianjing(Beijing Electro-Mechanical Engineering Institute,Beijing 100074,China)

机构地区：[1]北京机电工程研究所,北京100074

出　　处：《航天器环境工程》2021年第1期46-49,共4页Spacecraft Environment Engineering

摘　　要：航天器结构用新型C/SiC复合材料在飞行过程中会承受气动加热和噪声复合环境,容易出现疲劳破坏,需要进行地面热噪声试验考核。针对一种典型的C/SiC蒙皮骨架构型件,利用行波管开展热噪声试验研究,对试验件、试验装置和试验方法等进行介绍。利用试验获得的有效数据揭示热噪声复合环境下该C/SiC构型件的失效模式,验证其热噪声环境适应性。The carbon fiber toughened silicon carbide matrix composite(C/SiC)used in aircraft structure will be in a severe aerodynamic thermal-acoustic environment during the flight,which might damage the structure.Therefore,it is necessary to conduct the thermal-acoustic test in the laboratory.In this paper,an progressive wave tube is used for the thermal-acoustic test of a typically-configured C/SiC skin frame specimen.The detailed experimental set-up and the test method are given.From the valid test data,the failure mode of the specimen is identified,and the thermal noise environmental adaptability of the configuration part is validated.

关 键 词：C/SIC复合材料 环境适应性 热噪声试验 行波管 

分 类 号：V416.6[航空宇航科学与技术—航空宇航推进理论与工程]