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首页> 外文学位 >Application of an aeroelastic analysis method for aerodynamic improvement of fighter wings at maneuver flight conditions.
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Application of an aeroelastic analysis method for aerodynamic improvement of fighter wings at maneuver flight conditions.

机译：气动弹性分析方法在机动飞行条件下改善战斗机机翼气动性能的应用。

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摘要

Modern fighter aircraft must operate at a wide variety of flight conditions ranging from low-speed flight to transonic and supersonic cruise to transonic maneuver. The maneuvering characteristics of these aircraft is an important consideration when evaluating the overall effectiveness of the vehicle, but typically, these aircraft must be primarily designed to efficiently cruise, since this condition tends to consume the majority of the available fuel. Therefore, efficient design methods are required to optimize the aerodynamic performance of these aircraft at both cruise and maneuver flight conditions.;An aeroelastic analysis method, based on three-dimensional Navier-Stokes equation aerodynamics, has been applied to improve the performance of fighter wings operating at sustained maneuver flight conditions. The scheme reduces the trimmed pressure drag of wings performing sustained high-g maneuvers through a simultaneous application of control surface deflection and aeroelastic twist. The aerodynamic and structural interactions are decoupled by assuming an aeroelastic twist mode shape and optimizing the performance based on this aeroelastic mode. The wing structural stiffness properties are then determined through an inverse scheme based on the aerodynamic loads and desired twist at the maneuver flight condition. The decoupled technique is verified by performing a fully coupled aeroelastic analysis using the maneuver flight conditions and the optimized structural stiffness distributions.;This application uses a high-order numerical aerodynamic analysis method to efficiently define an aeroelastically deflected wing geometry with optimal aerodynamic performance at transonic maneuver flight conditions. In addition, the aerodynamic performance of the wing at cruise conditions is in no way compromised by the application of this scheme. Thus, this method represents a multiple-point wing design capability utilizing computational aerodynamics and aeroelastic tailoring.
机译：现代战斗机必须在从低速飞行到跨音速，超音速巡航到跨音速机动的各种飞行条件下运行。在评估车辆的总体效率时，这些飞机的机动特性是一个重要的考虑因素，但是通常，这些飞机的主要设计必须是有效巡航，因为这种情况会消耗大部分可用燃料。因此，需要有效的设计方法来优化这些飞机在巡航和机动飞行条件下的空气动力学性能。;基于三维Navier-Stokes方程空气动力学的空气弹性分析方法已被用于改善战斗机机翼的性能在持续机动飞行条件下运行。该方案通过同时施加控制面挠度和气动弹性扭曲来减少执行持续高重力操纵的机翼的修整压力阻力。通过采用气动弹性扭曲模式形状并基于此气动弹性模式优化性能，可以使气动和结构相互作用脱钩。然后，基于气动载荷和机动飞行条件下的期望扭转，通过反推法确定机翼的结构刚度特性。通过使用机动飞行条件和优化的结构刚度分布进行完全耦合的空气弹性分析来验证解耦技术;该应用程序使用高阶数值空气动力学分析方法来有效地定义具有弹性的偏转机翼几何形状，并在跨音速时具有最佳的空气动力学性能机动飞行条件。另外，该方案的应用绝不会损害机翼在巡航条件下的空气动力性能。因此，这种方法代表了利用计算空气动力学和气动弹性剪裁的多点机翼设计能力。

著录项

  • 作者

    Schuster, David Martin.;

  • 作者单位

    Georgia Institute of Technology.;

  • 授予单位 Georgia Institute of Technology.;
  • 学科 Engineering Aerospace.
  • 学位 Ph.D.
  • 年度 1992
  • 页码 236 p.
  • 总页数 236
  • 原文格式 PDF
  • 正文语种 eng
  • 中图分类
  • 关键词

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