直升机桨叶连续后缘襟翼设计与气动影响分析

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。

Design and Aerodynamic Authority Analysis of Continuous Trailing-Edge Flap of Helicopter Blade

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. MFC is used as the driving material, the blade section with continuous deformation trailing edge flap is designed based on the NACA23012 airfoil, and the material selection design of the profile structure is analyzed. The aerodynamic characteristics of the Continuous Trailing-Edge Flap is analyzed by Fluid-Structure Interaction method. The results show that the Continuous Trailing-Edge Flap can realize effective deflection in range of the helicopter blade working angle of attack, Mach number, and generate significant additional lift and torque increment. That demonstrates the potential value of Continuous Trailing-Edge Flap in rotor vibration damping application.