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| Effect of Rigid Insulating Tiles on Dynamical Property of Aerospace Module Structure |
| Received:September 13, 2021 Revised:January 13, 2022 |
| View Full Text View/Add Comment Download reader |
| DOI：10.7643/issn.1672-9242.2022.04.012 |
| KeyWord:hypersonic vehicles, thermal protection system (TPS), dynamical property, rigid insulating tiles size, gap size, thermal environment |
| Author | Institution |
| GUO Jing |
1. Science and Technology on Reliability and Environment Engineering Laboratory, Beijing Institute of Structure and Environment Engineering, Beijing , China |
| CHENG Hao |
1. Science and Technology on Reliability and Environment Engineering Laboratory, Beijing Institute of Structure and Environment Engineering, Beijing , China |
| ZHANG Zhong |
1. Science and Technology on Reliability and Environment Engineering Laboratory, Beijing Institute of Structure and Environment Engineering, Beijing , China |
| LIU Bao-rui |
1. Science and Technology on Reliability and Environment Engineering Laboratory, Beijing Institute of Structure and Environment Engineering, Beijing , China |
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| Abstract: |
| 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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