变弯度后缘与常规舵面机翼的颤振主动抑制对比  

Comparison of morphing trailing edges and conventional control surfaces for active flutter suppression

作　　者：杨永健 宋晨[1] 张桢锴 杨超[1] YANG Yongjian;SONG Chen;ZHANG Zhenkai;YANG Chao(School of Aeronautic Science and Engineering,Beihang University,Beijing 100191,China)

机构地区：[1]北京航空航天大学航空科学与工程学院,北京100191

出　　处：《航空工程进展》2023年第3期41-49,60,共10页Advances in Aeronautical Science and Engineering

基　　金：国家自然科学基金(11402013)。

摘　　要：后缘变弯度机翼的气动弹性建模与稳定性分析日益受到关注。为了探究变弯度后缘相比常规偏转舵面机翼颤振主动抑制的方法与特点,以一个小展弦比后缘变弯度机翼为对象,首先建立结构有限元模型,并引入变弯度后缘变形模态和常规舵面偏转模态,采用亚声速偶极子格网法计算非定常气动力;然后采用基于最小状态法的有理函数拟合进行频域到时域模型的转换,建立两种构型机翼的气动弹性模型;最后利用线性高斯二次型(LQG)法设计控制律进行颤振主动抑制,分析对比两种控制方式的特性差异。结果表明:采用变弯度后缘的闭环系统能够将颤振临界速度提高22%,其提升效果优于常规舵面,所需舵面偏转峰值更小。Aeroelastic modelling and stability analysis of wing with morphing trailing edge have attracted more and more attention.In order to explore the methods and characteristics between active flutter suppression of wings with morphing trailing edge and conventional control surface,a small aspect ratio wing with morphing trailing edge is taken as the object to research.Firstly,a structural finite element model is established,and the deformation modes of morphing trailing edge and conventional control surface are introduced to calculate the unsteady aerodynamic forc-es by employing subsonic doublet lattice method.Then,the rational function fitting based on minimum-state me-thod is used to transform the frequency-domain model to time-domain model,and the aeroelastic models of two configuration wings are established.Finally,a linear quadratic Gaussian(LQG)method is used to design the con-trol law to perform the active flutter suppression,and the property difference of two control modes are analyzed.The results show that the wing with morphing trailing edge can increase the critical speed of flutter by 22%,the control effect is better than conventional control surface,and the required defection angle is smaller.

关 键 词：变弯度后缘 常规偏转舵面 气动弹性 颤振主动抑制 线性高斯二次型法 

分 类 号：V215.34[航空宇航科学与技术—航空宇航推进理论与工程]