郭静,程昊,张忠,刘宝瑞.刚性隔热瓦对舱段结构动特性影响规律分析[J].装备环境工程,2022,19(4):74-79. GUO Jing,CHENG Hao,ZHANG Zhong,LIU Bao-rui.Effect of Rigid Insulating Tiles on Dynamical Property of Aerospace Module Structure[J].Equipment Environmental Engineering,2022,19(4):74-79.
刚性隔热瓦对舱段结构动特性影响规律分析
Effect of Rigid Insulating Tiles on Dynamical Property of Aerospace Module Structure
投稿时间:2021-09-13  修订日期:2022-01-13
DOI:10.7643/issn.1672-9242.2022.04.012
中文关键词:  高超声速飞行器  热防护系统  动特性  刚性隔热瓦尺寸  缝隙大小  热环境中图分类号:V416 文献标识码:A 文章编号:1672-9242(2022)04-0074-06
英文关键词:hypersonic vehicles, thermal protection system (TPS), dynamical property, rigid insulating tiles size, gap size, thermal environment
基金项目:国家自然科学基金(11502024,11502023,11402028,51805036)
作者单位
郭静 北京强度环境研究所 可靠性与环境工程技术重点实验室,北京 100076 
程昊 北京强度环境研究所 可靠性与环境工程技术重点实验室,北京 100076 
张忠 北京强度环境研究所 可靠性与环境工程技术重点实验室,北京 100076 
刘宝瑞 北京强度环境研究所 可靠性与环境工程技术重点实验室,北京 100076 
AuthorInstitution
GUO Jing 1. Science and Technology on Reliability and Environment Engineering Laboratory, Beijing Institute of Structure and Environment Engineering, Beijing 100076, China 
CHENG Hao 1. Science and Technology on Reliability and Environment Engineering Laboratory, Beijing Institute of Structure and Environment Engineering, Beijing 100076, China 
ZHANG Zhong 1. Science and Technology on Reliability and Environment Engineering Laboratory, Beijing Institute of Structure and Environment Engineering, Beijing 100076, China 
LIU Bao-rui 1. Science and Technology on Reliability and Environment Engineering Laboratory, Beijing Institute of Structure and Environment Engineering, Beijing 100076, China 
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中文摘要:
      目的 分析刚性隔热瓦尺寸、瓦间缝隙大小及热环境对典型舱段结构动特性的影响规律。方法 以刚性隔热瓦式热防护系统的高超声速飞行器舱段结构为研究对象,建立其动力学模型,分别研究自由-自由边界条件下刚性隔热瓦尺寸及瓦间缝隙大小对舱段结构动特性的影响规律。开展热环境下舱段结构的稳态热传导分析,获得热环境下舱段结构的温度场分布,然后将温度场作为载荷,进行舱段结构自由-自由边界条件下的热模态计算,分析热环境对刚性隔热瓦式热防护舱段结构动特性的影响规律。结果 刚性隔热瓦尺寸从150 mm增加至250 mm时,舱段第1阶弯曲模态频率从114.40 Hz提高至114.55 Hz,提高了0.13%。刚性隔热瓦间缝隙大小从0.8 mm增加至1.5 mm时,舱段第1阶弯曲模态频率从114.50 Hz提高至114.77 Hz,提高了0.24%。典型热环境下舱段结构最大热应力为0.014 4 MPa,最大热变形为0.206 mm,刚性隔热瓦间缝隙尺寸取0.8 mm时,满足要求。常温和热环境下,舱段结构第1阶弯曲模态频率分别为114.50、114.48 Hz,温度载荷导致舱段结构弯曲模态频率降低0.017%。结论 自由-自由边界条件下,在合理的设计范围内,刚性隔热瓦尺寸及刚性隔热瓦间缝隙大小对舱段结构动特性影响均较小。线性温度梯度工况下,温度场引起的热变形和热应力也很小,因此热环境对舱段结构热模态特性的影响亦很小,可以不予过分考虑。
英文摘要:
      The effects of the rigid insulating tiles size, the gap size among tiles and the thermal environment on the dynamical property of aerospace module structure are analyzed. The dynamical model is developed for hypersonic vehicle module structure with rigid insulating tiles thermal protection system (TPS). The effects of the rigid insulating tiles size and the gap size among tiles on dynamical property of aerospace module structure under free-free boundary conditions are investigated, respectively. Moreover, the steady thermal analysis is conducted for the aerospace module structure under a thermal environment. The distribution of the temperature field is obtained. Then the thermal mode under free-free boundary condition is studied by taking the temperature field as thermal load. The effects of thermal environment on the dynamical property of aerospace module structure with rigid insulating tiles are carried out. The first bending mode frequency increases from 114.40 Hz to 114.55 Hz while the rigid insulating tiles size increases from 150 mm to 250 mm, which increased rate is 0.13%. The first bending mode frequency increases from 114.50 Hz to 114.77 Hz while the gap size among tiles increases from 0.8mm to 1.5mm, which increased rate is 0.24%. The maximum thermal stress and thermal deformations are 0.014 4 MPa and 0.206 mm under the typical thermal environment, respectively. The gap size is 0.8 mm, which meets the requirement enough. The first bending mode frequencies are 114.50 Hz and 114.48 Hz at room and high temperature, respectively. The temperature load leads the first bending mode frequency to decrease by 0.017%. In the reasonable design domain, for aerospace module structure under free-free boundary conditions, the effects of the rigid insulating tiles size and the gap size among tiles on its dynamical property are both inconsiderable. Under the linear temperature gradient case, the thermal deformation and the thermal stress caused by the thermal load are much smaller. So the effects of thermal environment on the dynamical property of aerospace module structure are also negligible.
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