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操纵突变下旋翼气动载荷变化特性研究

张凯1,张威1,马砾2,吴林波1,招启军3   

  1. 1. 中国直升机设计研究所
    2. 南京航空航天大学 直升机旋翼动力学国家级重点实验室
    3. 南京航空航天大学
  • 收稿日期:2026-02-27 修回日期:2026-07-07 出版日期:2026-07-16 发布日期:2026-07-16
  • 通讯作者: 张凯
  • 基金资助:
    直升机动力学全国重点实验室基金

Study on variation characteristics of rotor aerodynamic load under abrupt maneuver conditions

  • Received:2026-02-27 Revised:2026-07-07 Online:2026-07-16 Published:2026-07-16
  • Contact: Kai ZHANG
  • Supported by:
    the Fund of National key laboratory of helicopter aeromechanics

摘要: 针对直升机机动飞行时操纵突变状态的复合材料旋翼桨叶非定常气动/弹性载荷计算,建立了一套适用于非定常机动飞行气弹载荷模拟的高精度CFD/CSD紧耦合分析方法,主要包括旋翼运动嵌套网格生成及弹性变形方法、基于可压缩雷诺平均N-S方程的非定常流场求解方法、基于中等变形梁理论和Hamilton原理建立的桨叶结构动力学模型和适用于旋翼桨叶机动飞行模拟的非定常CFD/CSD紧耦合策略。随后,采用具备先进外形的桨尖后掠直升机旋翼,开展了缩比模型旋翼机动状态下操纵突变风洞试验研究。在验证本文数值模拟方法有效性的同时,针对不同操纵速率、幅值对机动状态旋翼气动特性综合影响开展了详细分析,得到不同机动状态下旋翼操纵对旋翼气动载荷影响的一般规律。

关键词: 旋翼, 机动飞行, CFD/CSD紧耦合, 风洞试验, 非定常气弹载荷

Abstract: To calculate the unsteady aerodynamic/elastic load of composite rotor blade in helicopter maneuvering flight, a set of high-precision CFD/CSD tight coupling method is established, mainly including overset grid generation and elastic deformation method for rotor motion, unsteady flowfield solution method based on compressible Reynolds-averaged N-S equation, structural dynamic model of rotor blade built based on moderate deformation beam theory and Hamilton principle, and unsteady CFD/CSD tight coupling strategy suitable for rotor blade maneuvering flight simulation. Subsequently, a wind tunnel experimental investigation on abrupt changes in rotor control input under maneuvering conditions was conducted using a scaled model rotor of a swept-tip helicopter with advanced configuration. While verifying the validity of the numerical simulation method in this paper, a detailed analysis is carried out on the comprehensive influence of different maneuvering rates and amplitudes on rotor aerodynamic characteristics under maneuvering conditions, and the general laws of the influence of rotor maneuvering on rotor aerodynamic loads under different maneuvering conditions are preliminarily obtained.

Key words: Rotor, maneuvering flight, CFD/CSD tight couple, wind tunnel test, unsteady aeroelastic load

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