...
  • 主题
高级搜索  >
历史搜索 清空历史
首页> 外文期刊>Journal of the American Helicopter Society >Rotor Dynamic Wake Distortion Model for Helicopter Maneuvering Flight
【24h】

Rotor Dynamic Wake Distortion Model for Helicopter Maneuvering Flight

机译：直升机机动飞行的转子动态尾流畸变模型

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

Modeling of rotor dynamic wake distortion effects during helicopter transitional flight from a steady hover condition is considered in this paper. The variations of induced inflow over the rotor disk with time during transitional flight phases, such as pitching, rolling, climbing and transition to forward flight from a steady hover condition, are investigated using the vortex tube analysis. Numerical results indicate that the dynamic wake distortion effects can be approximated using first order equations for longitudinal and lateral wake curvatures, wake skew and wake spacing. The new model is implemented in a generic helicopter flight simulation program, and simulation results are compared with the Black Hawk helicopter flight test data in both the frequency domain and the time domain.
机译：本文考虑了直升机在稳定悬停条件下过渡飞行过程中转子动态尾流畸变效应的建模。使用涡流管分析，研究了在过渡飞行阶段（例如俯仰，滚动，爬升和从稳定悬停状态过渡到向前飞行）在转子盘上引起的流入量随时间的变化。数值结果表明，动态尾流失真效应可以使用纵向和横向尾流曲率，尾流偏斜和尾流间距的一阶方程式近似。新模型在通用直升机飞行仿真程序中实现，并将仿真结果与Black Hawk直升机在频域和时域的飞行测试数据进行比较。

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