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首页> 外文期刊>Journal of Aircraft >Underwing Missile Aerodynamic Effects on Flight-Measured Limit-Cycle Oscillations
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Underwing Missile Aerodynamic Effects on Flight-Measured Limit-Cycle Oscillations

机译：机翼导弹气动对飞行测量极限周期振荡的影响

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摘要

F-16 testing revealed differences in limit-cycle oscillation response characteristics associated with subtle aerodynamic variations of the underwing missiles. Physical length differences between long and short missiles led to the accidental discovery of the limit-cycle oscillation sensitivity. In addition to the length difference, the long missiles were found to have builtup collar sections, to which the fins and canards were attached to the missile body. Two cases are presented where both long and short missiles were carried underwing. For the case with no wingtip missiles present, carriage of the long missiles showed significant limit-cycle oscillation response, while the short missiles showed very little response. For the case with wingtip missiles present, the limit-cycle oscillation response levels were slightly higher for carriage of the short missiles but were otherwise quite similar to the long-missile responses. Computational fluid dynamics on a rigid wing suggest that the differences between the long and short missiles alter the flowfield by changing the impinging shock strength and location on the lower whig surface outboard of the underwing missile. For the empty wingtip launcher case, the location of the impinging shock on the lower surface influences the strength of the shock on the upper surface. This influence on the upper shock strength could be a key contributor to the limit-cycle oscillation mechanism when wingtip aerodynamics do not inhibit the flowfield.
机译：F-16测试表明，极限飞行振荡响应特性的差异与机翼导弹的细微空气动力学变化有关。长和短导弹之间的物理长度差异导致偶然发现极限循环振荡灵敏度。除了长度上的差异外，还发现这些长导弹具有结实的领子部分，鳍片和鸭舌帽附接到导弹主体上。提出了两种情况，其中长短导弹都在机翼下携带。对于没有翼尖导弹的情况，长型导弹的运输显示出明显的极限循环振荡响应，而短型导弹则显示出很少的响应。对于有翼尖导弹的情况，携带短型导弹的极限循环振荡响应水平略高，但与长导弹的响应非常相似。刚性机翼上的计算流体动力学表明，长导弹与短导弹之间的差异通过改变撞击力和在机翼导弹外侧下部辉格表面上的位置来改变流场。对于空的翼尖发射器壳体，撞击在下表面上的位置会影响撞击在上表面上的强度。当翼尖空气动力学不抑制流场时，这种对上部冲击强度的影响可能是极限循环振荡机制的关键因素。

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  • 来源
    《Journal of Aircraft》 |2013年第5期|1637-1645|共9页
  • 作者

    Charles M. Denegri; James A. Dubben; Sergey L. Kernazhitskiy;

  • 作者单位

    Principal Technical Advisor, Flutter Analysis and Test Methodology, Carriage Mechanics Division, 205 West D Avenue, Suite 348. U.S. Air Force SEEK EAGLE Office, Eglin Air Force Base, Florida 32542-6865;

    Lead Flutter Engineer, Carriage Mechanics Division, 205 West D Avenue, Suite 348. U.S. Air Force SEEK EAGLE Office, Eglin Air Force Base, Florida 32542-6865;

    Computational Fluid Dynamics Engineer, Interference Mechanics Division, 205 West D Avenue, Suite 348. U.S. Air Force SEEK EAGLE Office, Eglin Air Force Base, Florida 32542-6865;

  • 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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