北京航空航天大学学报 ›› 2010, Vol. 36 ›› Issue (2): 168-171.

• 论文 • 上一篇    下一篇

计及大迎角失速的直升机旋翼的气动力模拟

苏 媛, 曹 栋, 曹义华   

  1. 北京航空航天大学 航空科学与工程学院, 北京 100191
  • 收稿日期:2009-05-22 出版日期:2010-02-28 发布日期:2010-09-13
  • 作者简介:苏 媛(1966-),女,山东菏泽人,副教授,sysunny123@yahoo.com.cn.

Simulation of helicopter rotor aerodynamic force in conditions of high angle of attack and dynamic stall

Su Yuan, Cao Dong, Cao Yihua   

  1. School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China
  • Received:2009-05-22 Online:2010-02-28 Published:2010-09-13

摘要: 为了描述旋翼诱导速度的分布和大小,综合应用动态入流理论和王氏涡流理论,建立了一个适合直升机机动飞行时的入流模型;以叶素理论为基础,采用状态空间表达式的形式,建立起旋翼非定常气动模型,得到了旋翼气动力随桨盘方位角的变化规律,计算结果与参考数据吻合较好;最终针对失速流和深度失速流两种情况,以MATLAB软件为计算平台,求得了在给定输入情况下某型直升机平飞跃升机动过程中的旋翼拉力响应曲线,研究了大迎角情况下的气动载荷,为直升机旋翼的非定常气动力模拟提供了参考.

Abstract: Using Pitt-Peters dynamic inflow model and Wang’s vortex theory, helicopter inflow model was set up. The distribution and magnitude of rotor induced velocity in helicopter maneuvering flight were obtained. According to blade element theory and state-space function, rotor unsteady aerodynamic model was established, and the rotor dynamic response characteristics were calculated for different azimuth angles. The agreement between the computational results and the referenced data indicates that the models are feasible and effective. Finally, for the two flight conditions with dynamic stall and deep dynamic stall, MATLAB software was taken as the computational platform, and rotor loads responses at high angles of attack for pop-up maneuver can be obtained. The theoretical method can provide the references for the simulation of the unsteady aerodynamic forces in helicopter maneuvering flight.

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