固体火箭发动机声能共振规律试验研究  

Tests for sound energy resonance law of solid rocket engins ZHAO Tianquan,ZHANG Xiangyu,GAN Xiaosong

作　　者：赵天泉 张翔宇 甘晓松 ZHAO Tianquan;ZHANG Xiangyu;GAN Xiaosong(The 41st Institute of the Fourth Academy of CASC,Xi’an 710025,China)

机构地区：[1]中国航天科技集团有限公司四院四十一所,西安710025

出　　处：《振动与冲击》2021年第13期82-87,共6页Journal of Vibration and Shock

摘　　要：从固体火箭发动机声不稳定燃烧的声学特性出发,以声学激励作为扰动并提供能量,从声学响应角度评估发动机的稳定性,建立了探究固体火箭发动机声能共振规律的试验方法并搭建了试验系统,对于不同发动机结构开展了试验,结果表明试验系统可以表征声不稳定燃烧的声学特性;不同前封头结构声腔的各阶振荡频率基本相同,对于第一阶压力振荡,带有凹腔的椭球形前封头声腔稳定性最低。对于第二、三阶压力振荡,椭球形前封头声腔稳定性最高;潜入空腔体积越大,各阶压力振荡频率越低,声腔稳定性越差。传声特性分析结果表明,潜入空腔长度增加导致出口声功率透射系数减小,稳定性降低。Based on acoustic characteristics of acoustic unstable combustion of solid rocket engine,acoustic excitation was taken as the disturbance to provide energy,the test method to explore the acoustic energy resonance law of solid rocket engine was established and the test system was built.Tests were conducted for different engine structures.The results showed that the test system can characterize acoustic characteristics of acoustic unstable combustion;oscillation frequencies of different front heads’acoustic cavities are basically the same,for the first-order pressure oscillation,the ellipsoidal front head acoustic cavity with a cavity has the lowest stability,for the second and third order pressure oscillations,the ellipsoidal front head has the highest acoustic cavity stability;the larger the volume of submerged cavity,the lower the each order pressure oscillation frequency and the worse the acoustic vibration stability.The analysis results of sound transmission characteristics showed that increase in submerged cavity length causes decrease in transmission coefficient of outlet sound power and stability.

关 键 词：固体火箭发动机 声不稳定燃烧 声学特性 前封头结构 潜入空腔 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]