摘要
针对某重型运载火箭发动机地面热试车时绝热扩张段外露段结构破坏的故障,进行了失效模式分析,并基于模态结果和功率谱密度实测数据,开展了动力学仿真计算。仿真结果表明:在高振动载荷作用下,与喷管壳体尾部交界处的绝热扩张段产生较高的交变应力。伴随着发动机持续的高温高压高速燃气流动与粒子冲刷,绝热扩张段材料性能降低,高应力部位处的内型面开始出现碳布脱落等非正常现象,壁厚不断减薄,最终导致该部位开裂进而引发绝热扩张段解体。根据上述故障定位,提出了延长喷管壳体的补强方案,以此增加了高振动载荷环境下绝热扩张段的结构完整性保持能力,并顺利通过地面热试车的验证考核,表明改进方案合理,措施有效。
Aiming at the failure against structural damage in the exposed section of adiabatic diffuser during ground hot-firing test of a heavy-lift carrier rocket,the failure mode analysis was carried out,based on the modal results and the measured data of power spectral density also,the dynamics simulation was calculated.The simulation results show that the adiabatic diffuser at the junction with the tail of the nozzle shell generates a higher alternating stress under the action of high vibration load,with the continuous high-temperature,high-pressure and high-speed gas flow and particle scouring of the rocket motor,the material performance of the adiabatic expansion section is reduced,the inner surface of the high-stress site begins to exhibit abnormal phenomena such as carbon cloth shedding,and the wall thickness continues to decrease,which eventually leads to cracking at this site and triggers the disintegration of the adiabatic diffuser.According to the above fault location,a reinforcement scheme for extending the nozzle shell is proposed,which increases the structural integrity maintenance ability of the adiabatic diffuser under high vibration load environment,and successfully passes the verification test of the ground hot-firing test,indicating that the improvement scheme is reasonable,the measures are effective.
作者
赵威
崔建伟
张焘
张维维
刘国斌
王敏
ZHAO Wei;CUI Jianwei;ZHANG Tao;ZHANG Weiwei;LIU Guobin;WANG Min(The 41st Institute of the Sixth Academy of China Aerospace Science&Industry Corp,Hohhot 010010,China)
出处
《深空探测学报（中英文）》
2020年第3期311-318,共8页
Journal Of Deep Space Exploration
基金
国家重点研发计划资助项目(2017YFB1103400)。
关键词
重型运载火箭
喷管
振动
结构破环
故障模式
heavy-lift carrier rocket
nozzle
vibration
structural damage
failure mode
