高超声速飞行器鼻锥的热环境和结构热分析研究

Research on Analysis of Thermal Environment and Structure of Nose Tip for Hypersonic Vehicle

基于典型的高超声速气动加热飞行环境,利用热流迭代修正方法对轴对称一体化结构高超声速飞行器鼻锥进行结构温度场分析。首先通过流场计算得到飞行器鼻锥的冷壁边界热流密度分布,并将其作为结构热响应有限元计算的初始边界条件。为了验证计算方法的可执行性,并为计算结果分析比较提供参考数据,首先进行只考虑导热和辐射的计算,不考虑壁面温度变化对热流影响的热流修正迭代计算。而后,针对壁面温度随时间变化,对热流密度进行修正,进行多次迭代计算模拟,用以确定高超声速飞行器鼻锥材料以及结构设计尺寸。

Basing on typical aerodynamic heating environment at hypersonic flow, the structure temperature field computation for nosetip of hypersonic vehicle is performed by iteratively modifying the thermal load. Firstly, the heat flux density distribution of cold wall are obtained from flow field calculation, which is used to be the boundary condition to initialize the finite element method calculation. The calculation of heat transfer and heat radiation is carded out to proving the feasibility of the numerical method, and the results can be compared with that of the final numerical simulation. Because the temperature are represented as a time function, the influence of temperature increment to the flux density is considered, and the flux density is iteratively modified with heating time to certain the bulk material and structural projected dimension.