火箭燃气射流近场噪声特性实验研究  

Experimental study of near field rocket noise in exhausted flow field

作　　者：徐强[1] 廖光煊[1] 李军[2] 曹从咏[2] 

机构地区：[1]中国科学技术大学火灾科学国家重点实验室,安徽合肥230026 [2]南京理工大学机械学院,江苏南京210094

出　　处：《推进技术》2002年第4期318-320,共3页Journal of Propulsion Technology

摘　　要：火箭燃气射流噪声特性是武器系统集成化所考虑的重要因素之一。通过对单室双推力实验发动机近场射流噪声的测量与分析 ,得到噪声峰值频率的变化范围。联合时频分析结果表明 ,同一测量位置处射流噪声的峰值频率与燃烧室压力的变化无关 ,而噪声幅值则依赖于燃烧室压力。The characteristic of rocket noise is one of the important factors in integration of rocket system Rocket noise of a single chamber two stage rocket motor was measured and analyzed, and the changing range of the its peak frequency was obtained According to the result of the joint time frequency analysis, the peak frequency had little relation with chamber pressure But noise magnitude had close relation to chamber pressure Experiment result serves as important reference to prediction of rocket noise

关 键 词：燃气射流 实验研究 双推力火箭发动机 声学测量 噪声强度 

分 类 号：V430[航空宇航科学与技术—航空宇航推进理论与工程]