特种结构固体火箭发动机燃烧室随机振动疲劳分析  

Fatigue analysis on chamber of a special structure SRMunder random vibration

作　　者：邓康清 朱雯娟[2] 王相宇[2] 余小波[2] 郭春亮[2] 刘梦珂[2] 张峰涛 向进[2] 王鹍鹏[2] 张琪敏[2] DENG Kangqing;ZHU Wenjuan;WANG Xiangyu;YU Xiaobo;GUO Chunliang;LIU Mengke;ZHANG Fengtao;XIANG Jin;WANG Kunpeng;ZHANG Qimin(Science and Technology on Aerospace Chemical Power Laboratory,Xiangyang 441003,China;Hubei Institute of Aerospace Chemical Technology,Xiangyang 441003,China)

机构地区：[1]航天化学动力技术重点实验室,襄阳441003 [2]湖北航天化学技术研究所,襄阳441003

出　　处：《固体火箭技术》2023年第2期263-271,共9页Journal of Solid Rocket Technology

摘　　要：随机振动下固体火箭发动机的疲劳破坏分析与疲劳寿命准确预测一直是困扰固体发动机设计的难题。通过模态分析、随机振动分析和基于高斯分布的三区间法、Miner疲劳累积损伤理论进行的疲劳计算,仿真分析了一种特种结构固体发动机燃烧室经过随机振动试验后的疲劳破坏规律及影响因素。结果表明,发动机燃烧室在经历径向随机振动激励时,结构响应最大,最大等效应力位于与燃烧室壳体交界附近的装药杯支撑杆上,是发动机燃烧室的最薄弱处;发动机燃烧室存在90、294、411 Hz三个共振频率,设计时要注意避开。极限随机振动试验表明,振动60 s时,燃烧室未发生疲劳破坏,而振动15 min发生了疲劳破坏,这与仿真的结果是吻合的,验证了数值振动模型和疲劳破坏计算方法的有效性,可为预测固体火箭发动机的疲劳破坏和疲劳寿命提供参考和指导。The fatigue failure analysis and life prediction of solid rocket motor(SRM)under random vibration is still a challenge in SRM design.The fatigue failure law and influencing factors for chamber of a special structure SRM after random vibration test were simulated and analyzed by means of modal analysis,random vibration analysis and fatigue calculation based on the Gauss's three interval method and Miner's fatigue accumulation damage theory.The results show that the structural response of motor chamber is the largest when excited along the radial direction,and the maximum equivalent stress is located on the supporting rod of the grain cup near the chamber case,which is the weakest part of the chamber.There are three resonance frequencies 90 Hz,294 Hz and 411 Hz in the chamber,which should be avoided in the design.The extreme random vibration test shows that there is no fatigue failure in the combustion chamber for vibration 60 s,fatigue failure of the chamber occurs when vibration maintain 15 min,which is consistent with the simulation results.The validity of the numerical vibration model and the fatigue failure calculation method is verified,which can provide reference and guidance for predicting the fatigue failure and fatigue life of solid rocket motor.

关 键 词：固体火箭发动机 特种结构燃烧室 装药杯 随机振动 疲劳分析 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]