The inflatable reentry vehicle provides a new technical way in aerospace entry, descent, and landing. The structural failure of inflatable reentry vehicle experiment caused by thermal aeroelastic effect is serious, which needs to be further studied. A traditional numerical method about flexible vehicles separates the aeroheating and aeroelastic problems, resulting in poor matching with the actual test. In this paper, a thermal-fluid-solid coupling model considering inflation gas effect was established, which associates the aeroheating and aeroelastic modules and adopts the LES to improve the depicting ability of hypersonic flow. The model was used to solve the thermal aeroelastic characteristics under extreme aeroheating load. From aeroheating results, the large-scale vortex on windward generated by the interaction of the shock layer and boundary layer has great influence on aeroheating due to the heat dissipation, and the skin deformation also increases the surface friction and local heating near depressions. From aeroelastic analysis, the flexible structure performs violent forced vibration induced by the unsteady large-scale vortex on windward, and the aeroheating effect will significantly increase the thermal stress and natural vibration properties. The thermal-fluid-solid coupling method for the flexible structure proposed in this paper provides a reasonable reference for engineering.

中文翻译：

---

高超音速流动中的充气再入飞行器实验的热气动弹性特征

充气式再入飞行器为航空进入，下降和着陆提供了新的技术途径。由热气动弹性效应引起的充气式再入飞行器实验的结构破坏是严重的，有待进一步研究。关于挠性车辆的传统数值方法将空气加热和空气弹性问题分开，导致与实际测试的匹配性较差。本文建立了考虑充气气体效应的热-固-固耦合模型，该模型将空气加热模块和空气弹性模块联系起来，并采用LES来提高高超声速流的描绘能力。该模型用于求解极端热负荷下的热空气弹性特征。从空气加热的结果来看，激波层与边界层相互作用产生的迎风大涡旋由于散热而对空气加热有很大影响，表皮变形也增加了凹陷附近的表面摩擦和局部加热。从气动弹性分析来看，柔性结构会因风向上的不稳定大尺度涡旋而产生剧烈的强迫振动，而气动加热效果将显着增加热应力和自然振动特性。本文提出的柔性结构热流固耦合方法为工程提供了合理的参考。柔性结构在风向上会受到不稳定的大涡旋所引起的剧烈的强迫振动，而空气的热效应会显着增加热应力和自然振动特性。本文提出的柔性结构热流固耦合方法为工程提供了合理的参考。柔性结构在风向上会受到不稳定的大涡旋所引起的剧烈的强迫振动，而空气的热效应会显着增加热应力和自然振动特性。本文提出的柔性结构热流固耦合方法为工程提供了合理的参考。