摘要
隔热瓦是可重复使用飞行器热防护结构的重要组成部分,其在低速撞击下极易受损。文章针对“隔热瓦−应变隔离垫−冷结构金属板”这一典型热防护结构,试验研究其在落球(直径50 mm)低速(≤10 m/s)撞击下的损伤特性。试验结果表明,隔热瓦组件在受到撞击后,仅在受撞击区域形成一直径为16.5 mm、深度为1.79 mm的圆形凹坑,未观察到受撞击区域以外的裂纹、变形等损伤。随后建立隔热瓦组件撞击有限元仿真模型并根据试验结果对其进行修正。对比仿真结果与试验结果:撞击坑的直径和深度以及涂层脱落区域直径的仿真误差均在12%以内。该研究结果可为可重复使用飞行器热防护结构的设计、制造和维护提供参考。
Thermal insulation tiles are a critical component of reusable launch vehicle's heat protection system.However,they are susceptible to damage from low-velocity impacts.The damage effects of low-velocity impact on the structure composed of thermal insulation tiles,strain isolation pads,and cold structural metal plates through drop ball(50 mm in diameter)impact tests were investigated in this study.The results show that upon low-velocity impact,the thermal insulation tiles formed circular craters with a diameter of approximately 16.5 mm and a depth of approximately 1.8 mm.No cracks,deformations,or other damages were observed outside the impacted area.Following the experimental investigations,a finite element simulation model of the thermal insulation tile assembly’s impact response was developed and adjusted based on the experimental data.Comparison of the simulation results with the experimental results shows that the simulation errors in the diameter and depth of the impact crater and the diameter of the coating delamination area around the crater are all within 12%.The research may serve as a reference for the design,manufacturing,and maintenance of thermal protection structures for reusable launch vehicles.
作者
宋俊柏
刘振皓
吴振强
刘武刚
王龙
邢睿思
SONG Junbai;LIU Zhenhao;WU Zhenqiang;LIU Wugang;WANG Long;XING Ruisi(Science and Technology on Reliability and Environmental Engineering Laboratory,Beijing Institute of Structure and Environment Engineering,Beijing 100076,China)
出处
《航天器环境工程》
2025年第1期39-45,共7页
Spacecraft Environment Engineering
关键词
可重复使用飞行器
隔热瓦
低速撞击
撞击试验
撞击仿真
reusable launch vehicle
thermal insulation tiles
low-velocity impact
impact experiment
impact simulation
