Cumulative thermal deformation evolution under prelonged aerodynamic and thermal loads
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摘要:
长时间气动力/热作用下产生的累积热变形及其在整个飞行历程中引发的不利影响是未来高超声速巡航飞行器设计不可忽视的问题。针对高超声速飞行器典型翼面结构，以自研热环境/热响应耦合计算分析平台为基础，结合自适应时间步的双向耦合计算策略建立全数值的气动力/热/结构多场耦合累积热变形预测方法；在此基础上开展翼面结构在长时间气动力/热耦合作用下的累积热变形演化规律及形成机理研究，并分析其在时间变化历程中对气动特性的影响。研究结果表明，由于翼面结构所受气动力、气动加热、结构传热、变形响应等物理过程的时空尺度差异，累积热变形呈现第1发展、第2发展、充分发展等非线性特征突出的3个演化阶段，并且各种因素需要经过较长的时间才能充分发展并实现累积变形的稳定。上述累积热变形演化行为引发了伴随整个飞行历程的气动特性的非线性变化，进一步带来升力下降、升阻比下降及俯仰力矩偏差等不利影响。相关不利影响亟需在未来长航时高超声速飞行器设计中加以考虑并主动应对。
Abstract:Cumulative thermal deformations during long periods of aerodynamic thermal coupling and their associated adverse effects are issues that cannot be ignored for future hypersonic aircrafts with long endurance. For typical structures of hypersonic wing structure, a fully numerical aerodynamic/thermal/structural multi-field coupling cumulative thermal deformation prediction method is established, based on in-house numerical solvers, and in conjunction with adaptive time-stepping and two-way coupling strategy. Based on this method, an analysis of the cumulative thermal deformation characteristics and their causes of the wing structure under long-term aerodynamic/thermal co-activity was carried out, as well as the the deformation impacts on the aerodynamic characteristics were performed. The results of the study indicate that, due to the temporal and spatial scale differences of physical processes such as aerodynamic forces, aerodynamic heating, aerodynamic heat transfer and deformation response in wing structures, the cumulative thermal deformation exhibits three distinct nonlinear evolutionary stages: first development, second development, and full development. Moreover, it requires a considerable amount of time for various factors to fully develop and achieve stable accumulated deformation. The aforementioned evolution of accumulated thermal deformation behavior triggers the nonlinear changes in aerodynamic characteristics throughout the entire flight journey, resulting in adverse effects such as decrease of lift, decrease of lift-to-drag ratio and the deviation of pitching moment. Therefore, in the design of long-duration hypersonic aircraft in the future, these associated adverse effects need to be duly considered and actively addressed.
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图 3 本文计算变形与解析解对比
Figure 3. Comparison of present displacement with analytical solution
图 4 本文计算径向热应力与解析解对比
Figure 4. Comparison of present radial thermal stress with analytical solution
图 5 本文计算周向热应力与解析解对比
Figure 5. Comparison of present circumferential thermal stress with analytical solution
图 11 高超声速飞行器机翼气动力/热计算网格
Figure 11. The aerodynamic force and heating calculation grid for wing of hypersonic aircraft
图 14 初始时刻表面压力分布云图
Figure 14. Contour of surface pressure distribution at initial moment
图 16 监测点位置以及温度和热流密度随时间的变化
Figure 16. Monitor points and variation of the temperature and heating rate for monitor points with time
图 17
1000 s时的累积热变形分布Figure 17. The accumulated thermal deformation distribution of
1000 s
图 19 监测点累积热变形随时间的变化规律
Figure 19. Changes of accumulated heat deformation with time at monitoring points
图 20 监测点$y$方向热变形随时间变化规律（对数坐标）
Figure 20. Variation of thermal deformation in $y$ direction for monitor points with time (in logarithmic coordinate system)
图 21 翼面整体弯曲角度随时间的变化规律
Figure 21. Variation of bending angle of wing structure with time
图 23 不同分析方法下的$y$方向位移
Figure 23. The deformations in $y$ direction for different analysis methods
表 1 高温合金GH1015材料物理性能
Table 1. Material physical properties of high temperature alloy GH1015
性能 数值 密度/(kg·m−3) 8320 泊松比 0.3 表面辐射系数 0.8 
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表 2 高温合金GH1015材料热物理性能
Table 2. Thermal-physical properties of high temperature alloy GH1015
温度/K 导热系数/
(W·(m·K)−1)比热容/
(J·(kg·K)−1)弹性
模量/GPa热膨胀系数/
10−6 K−1273 9.9 440 170 14.0 373 12.0 450 166 14.4 473 13.5 475 158 14.7 573 15.5 495 152 15.0 673 17.3 505 142 15.5 773 19.0 530 135 15.8 873 21.0 555 128 16.1 973 22.8 575 115 16.4 1073 24.9 615 108 16.7 1173 26.7 650 94 17.0 1273 28.6 710 78 17.3
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