• 主题
高级搜索  >
历史搜索 清空历史
首页> 外文学位 >Numerical wing/store interaction analysis of a parametric F16 wing.
【24h】

Numerical wing/store interaction analysis of a parametric F16 wing.

机译：参数化F16机翼的数值机翼/商店相互作用分析。

获取原文
获取原文并翻译 | 示例
页面导航
  • 摘要
  • 著录项
  • 相似文献
  • 相关主题

摘要

A new numerical methodology to examine fluid-structure interaction of a wing/pylon/store system has been developed. The aeroelastic equation of motion of the complete system is solved iteratively in the time domain using a two-entity numerical code comprised of ABAQUS/Standard and the Unsteady-Vortex-Lattice Method. Both codes communicate through an iterative handshake procedure during which displacements and air loads are updated. For each increment in time the force/displacement equilibrium is found in this manner.; The wing, pylon, and store data considered in this analysis are based on an F16 configuration that was identified to induce flutter in flight at subsonic speeds. The wing structure is modeled as an elastic plate and pylon and store are rigid bodies. The store body is connected to the pylon through an elastic joint exercising pitch and yaw degrees of freedom. Vortex-Lattice theory featuring closed ring-vortices and continuous vortex shedding to form the wakes is employed to model the aerodynamics of wing, store, and pylon.; The methodology was validated against published data demonstrating excellent agreement with documented key phenomena of fluid-structure iteration. The model correctly predicts the effects of the pylon induced lateral flow disruption as well as wing-tip-vortex effects. It can identify the presence of aerodynamic interference between the store, pylon, and wing wakes and examine its significance with respect to the pressure and lift forces on the participating bodies. An elementary flutter study was undertaken to examine the dynamic characteristics of a stiff production pylon at near-critical airspeeds versus those of a soft-in-pitch pylon. The simulation reproduced the stabilizing effect of the stiffness reduction in the pitch motion. This idea is based on the concept of the decoupler pylon, introduced by Reed and Foughner in 1978 and flight tested in the early 1980's.
机译：已经开发出一种新的数值方法来检查机翼/塔架/储能系统的流体-结构相互作用。使用由ABAQUS / Standard和非定常涡旋格子方法组成的二元数字代码在时域中迭代求解整个系统的气动弹性方程。两种代码都通过迭代握手过程进行通信，在此过程中更新了位移和空气载荷。对于每个时间增量，都以这种方式找到力/位移平衡。在此分析中考虑的机翼，塔架和商店数据基于F16构造，该构造被确定为以亚音速引导飞行中的颤振。机翼结构建模为弹性板，而挂架和存放架为刚体。存储体通过行使俯仰和偏航自由度的弹性接头与塔架相连。涡流-格子理论以闭环涡流和连续涡流脱落形成尾流为特征，用于对机翼，机舱和塔架的空气动力学建模。该方法论已针对已发表的数据进行了验证，该数据与流体结构迭代的关键现象已得到很好的证明。该模型正确地预测了定向塔引起的侧向流动中断以及翼尖涡旋效应的影响。它可以识别出商店，塔架和机翼尾翼之间是否存在空气动力干扰，并检查其在参与车身上的压力和升力方面的重要性。进行了基本的颤振研究，以检查在接近临界空速时的刚性生产塔架与俯仰软塔的动态特性。模拟再现了俯仰运动中刚度降低的稳定效果。这个想法基于里德（Reed）和福夫纳（Foughner）在1978年提出并在1980年代初期进行了飞行测试的解耦塔的概念。

著录项

相似文献

  • 外文文献
  • 中文文献
  • 专利
获取原文

客服邮箱：kefu@zhangqiaokeyan.com

京公网安备：11010802029741号 ICP备案号：京ICP备15016152号-6 六维联合信息科技 (北京) 有限公司©版权所有

  • 客服微信

  • 服务号