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Aeroelastic Optimization with an Economical Transonic Flutter Constraint Using Navier-Stokes Aerodynamics

机译：经济的跨音速颤振约束的气动弹性优化，使用Navier-Stokes空气动力学

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摘要

Structural optimization with a flutter constraint for a vehicle designed to fly in the transonic regime is a particularly difficult task. In this speed range, the flutter boundary is very sensitive to aerodynamic nonlinearities, typically requiring high-fidelity Navier-Stokes simulations. However, the repeated application of unsteady computational fluid dynamics to guide an aeroelastic optimization process is very computationally expensive. This expense has motivated the development of methods that incorporate aspects of the aerodynamic nonlinearity, classical tools of flutter analysis, and more recent methods of optimization. Although it is possible to use doublet-lattice method aerodynamics, this paper focuses on the use of an unsteady high-fidelity aerodynamic reduced-order model combined with successive transformations that allows for an economical way of using high-fidelity aerodynamics in the optimization process. This approach is applied to the common research model wing structural design. The high-fidelity aerodynamics produces a heavier wing than that optimized with doublet-lattice aerodynamics. It is found that the optimized lower wing skin thickness distribution using high-fidelity aerodynamics differs significantly from that using doublet-lattice aerodynamics.
机译：对于设计成在跨音速状态下飞行的车辆而言，具有颤振约束的结构优化是一项特别困难的任务。在此速度范围内，颤振边界对空气动力学非线性非常敏感，通常需要高保真度的Navier-Stokes模拟。但是，反复应用不稳定的计算流体动力学来指导气动弹性优化过程在计算上非常昂贵。这项费用促使开发了结合了空气动力学非线性，颤振分析的经典工具以及最新的优化方法等方面的方法。尽管可以使用双重晶格方法空气动力学，但本文着重于使用不稳定的高保真空气动力学降阶模型与连续变换相结合，从而允许在优化过程中经济地使用高保真空气动力学。该方法适用于通用研究模型机翼结构设计。高保真空气动力学产生的机翼比采用双晶格空气动力学优化的机翼重。发现使用高保真空气动力学优化的下机翼蒙皮厚度分布与使用双晶格空气动力学优化的下翼蒙皮厚度分布显着不同。

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