火箭燃气射流近场噪声特性实验研究

推进技术 ›› 2002, Vol. 23 ›› Issue (4): 318-320.

火箭燃气射流近场噪声特性实验研究

徐强,廖光煊,李军,曹从咏

中国科学技术大学火灾科学国家重点实验室;安徽合肥230026;中国科学技术大学火灾科学国家重点实验室;安徽合肥230026;南京理工大学机械学院 ;江苏南京210094;南京理工大学机械学院 ;江苏南京210094

发布日期:2021-08-15

Experimental study of near field rocket noise in exhausted flow field

State Key Lab of Fire Science, China Univ of Science and Technology, Hefei 230026, China;State Key Lab of Fire Science, China Univ of Science and Technology, Hefei 230026, China;Coll of Mechanics, Nanjing Univ of Science and Technology, Nanjing 210094, China;Coll of Mechanics, Nanjing Univ of Science and Technology, Nanjing 210094, China

Published:2021-08-15

摘要/Abstract

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。实验结果对火箭燃气射流噪声场的预测提供了实验依据

关键词: 发动机噪声;双推力火箭发动机;射流;声学测量;噪声强度

Abstract: 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

Key words: Engine noise;Dual thrust rocket engine;Jet flow;Acoustic measurement;Noise intensity

徐强,廖光煊,李军,曹从咏. 火箭燃气射流近场噪声特性实验研究[J]. 推进技术, 2002, 23(4): 318-320.