摘要
在直升机旋翼减振应用中,连续后缘襟翼和常规分离式襟翼相比具有重量轻、结构紧凑、气流平稳等优点。选用压电纤维复合材料作为驱动材料,基于NACA23012翼型设计带有连续变形后缘襟翼的桨叶段,对襟翼及其驱动结构进行选材设计分析;采用流固耦合方法分析连续后缘襟翼对剖面翼型气动特性的影响。结果表明:连续后缘襟翼在直升机桨叶工作迎角、马赫数范围内可实现有效偏转,显著改变翼剖面气动升力和力矩,证明了连续后缘襟翼在旋翼减振控制中的潜在应用价值。
Continuous trailing-edge flap has many advantages over conventional discrete flap in helicopter rotor vibration reduction applications,such as light weight,compact structure and stable airflow.Macro fiber composite is chosen as the actuating material.A blade section with a continuous trailing-edge flap is designed based on NACA23012 airfoil,and its materials are selected and analyzed.The influence of continuous trailing-edge flap on airfoil aerodynamic characteristics is analyzed by fluid-solid coupling method.Results show that continuous trailing-edge flap can output sufficient deflection under the working conditions of helicopter blade,including angle of attack as well as Mach number,and improve aerodynamic lift and moment of the blade profile significantly,which demonstrates the potential value of continuous trailing-edge flap in rotor vibration reduction applications.
作者
李贇
董凌华
周金龙
杨卫东
Li Yun;Dong Linghua;Zhou Jinlong;Yang Weidong(National Key Laboratory of Rotorcraft Aeromechanics,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)
出处
《航空工程进展》
CSCD
2018年第2期230-238,共9页
Advances in Aeronautical Science and Engineering
基金
南京航空航天大学研究生创新基地(实验室)开放基金(kfjj20160109)
江苏高校优势学科建设工程资助项目
关键词
旋翼
直升机
连续后缘襟翼
流固耦合
压电纤维复合材料
rotor
helicopter
continuous trailing-edge flap
fluid-solid coupling
macro fiber composite
