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首页> 外文会议>AIAA international space planes and hypersonic systems and technologies conference >Coupled Analysis of Aerodynamic Heating, Radiative Heat Transfer and Heat Conduction for Hypersonic Vehicles
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Coupled Analysis of Aerodynamic Heating, Radiative Heat Transfer and Heat Conduction for Hypersonic Vehicles

机译：高超音速飞行器空气动力加热，辐射换热与导热的耦合分析

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The aerodynamic heating results in the rapid rise of the surface temperature of hypersonic vehicles. As a key factor that influences the selection and design of thermal structures, equilibrium surface temperatures occur when the aerodynamic heat flux imposed on the surface is balance by thermal radiation from the surface, which are typically utilized in the conceptual and preliminary designs of hypersonic vehicles. Obviously the equilibrium surface temperature is the peak temperature that thermal-structure can achieve, since heat conducted into the structure is not calculated when the surface fluxed are balanced. In order to accurately obtain the temperature environment over specified trajectories, an integrated coupled approach in which the aerodynamic heating, radiative heat transfer and structure heat conduction are all taken into account is proposed. This study aims to develop a coupled analysis methodology for the temperature environment prediction under combined aerodynamic heating, radiative transfer and structure heat conduction. The integrated coupled approach is used to obtain the temperature environment of the typical control surface for a representative hypersonic trajectory. Results illustrate that the temperature environment obtained by integrated coupled approach is obviously lower than that by equilibrium, which regularly leads to 25% maximum percent error on the leading edge, 48% maximum percent error on the other regions. Furthermore, the estimation temperature is associated with the trajectory, which indicates that during climbing phase, the difference of surface temperature obtained by equilibrium and coupled approach is much larger than that during gliding phase.
机译：空气动力学加热导致高超音速车辆的表面温度迅速升高。作为影响热结构选择和设计的关键因素，当施加在表面上的空气动力学热通量通过来自表面的热辐射而达到平衡时，就会产生平衡的表面温度，这通常用于高超音速飞行器的概念设计和初步设计中。显然，平衡表面温度是热结构可以达到的峰值温度，因为当表面通量达到平衡时，不会计算传导到结构中的热量。为了准确地获得指定轨迹上的温度环境，提出了一种综合耦合的方法，其中考虑了空气动力加热，辐射热传递和结构热传导。这项研究旨在开发一种结合空气动力学加热，辐射传递和结构热传导的温度环境预测的耦合分析方法。集成耦合方法用于获得代表高超声速轨迹的典型控制表面的温度环境。结果表明，通过积分耦合方法获得的温度环境明显低于通过平衡获得的温度环境，这通常导致前沿的最大误差百分比为25％，其他区域的误差百分比为48％。此外，估计温度与轨迹相关，这表明在爬升阶段，通过平衡和耦合方法获得的表面温度差异远大于滑行阶段。

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