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Transonic Aerodynamic Load Modeling of X-31 Aircraft Pitching Motions

机译:X-31飞机俯仰运动的跨音速气动载荷建模

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摘要

The generation of reduced-order models for computing the unsteady and nonlinear aerodynamic loads on an aircraft from pitching motions in the transonic speed range is described. The models considered are based on Duhamel's superposition integral using indicial (step) response functions, Volterra theory using nonlinear kernels, radial basis functions, and a surrogate-based recurrence framework, both using time-history simulations of a training maneuver(s). Results are reported for the X-31 configuration with a sharp leading-edge cranked delta wing geometry, including canard/wing vortex interactions. The validity of the various models studied was assessed by comparison of the model outputs with time-accurate computational-fluid-dynamics simulations of new maneuvers. Overall, the reduced-order models were found to produce accurate results, although a nonlinear model based on indicial functions yielded the best accuracy among all models. This model, along with a time-dependent surrogate approach, helped to produce accurate predictions for a wide range of motions in the transonic speed range.
机译:描述了降阶模型的生成,该降阶模型用于根据跨音速范围内的俯仰运动来计算飞机上的非稳态和非线性空气动力学载荷。所考虑的模型基于Duhamel的叠加积分,使用的是积分(阶跃)响应函数,Volterra理论使用的是非线性核,径向基函数,以及基于替代的递归框架,都使用了训练演习的时间历史模拟。报告了X-31构型的结果,该构型具有锋利的前缘曲柄三角翼几何形状,包括鸭翼/翼涡旋相互作用。通过将模型输出与新操作的时间精确的计算流体动力学模拟进行比较,来评估所研究的各种模型的有效性。总体而言,尽管基于所有函数的基于非线性函数的非线性模型产生了最佳的准确性,但发现降阶模型可以产生准确的结果。该模型与基于时间的替代方法一起,有助于对跨音速范围内的各种运动产生准确的预测。

著录项

  • 来源
    《AIAA Journal》 |2013年第10期|2447-2464|共18页
  • 作者单位

    U.S. Air Force Academy, Colorado 80840,Modeling and Simulation Research Center;

    U.S. Air Force Academy, Colorado 80840,Modeling and Simulation Research Center;

    University of Liverpool, Liverpool, England L69 3BX, United Kingdom,School of Engineering currently the University of Southampton;

    University of Liverpool, Liverpool, England L69 3BX, United Kingdom,School of Engineering;

  • 收录信息 美国《科学引文索引》(SCI);美国《工程索引》(EI);
  • 原文格式 PDF
  • 正文语种 eng
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