升力面法厚度修正及其在折叠翼变体仿真中的应用  

Thickness correction by lifting surface method and its application in morphing simulation of folding wing

作　　者：徐浩 韩景龙[2] 陈扬[1] 何飞毅 倪昊 XU Hao;HAN Jinglong;CHEN Yang;HE Feiyi;NI Hao(Shanghai Aerospace Control Technology Institute,Shanghai 201109,China;College of Aerospace Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)

机构地区：[1]上海航天控制技术研究所,上海201109 [2]南京航空航天大学航空学院,南京210016

出　　处：《北京航空航天大学学报》2024年第12期3806-3814,共9页Journal of Beijing University of Aeronautics and Astronautics

基　　金：国家自然科学基金(11472133)。

摘　　要：变体过程铰链力矩的计算是折叠翼飞行器设计的重要一环,现有仿真在气动建模中多采用传统的升力面法。该方法忽略了翼型厚度的影响,会产生较大的计算误差。引入一种可以考虑翼型厚度的定常高阶面元法,并给出一种采用高阶面元法对升力面法进行厚度修正的气动建模策略。将修正后的气动模型与现有多柔体结构模型及飞行控制模型耦合,对折叠翼的飞行变体过程进行仿真。结果表明:修正后的气动模型可以对翼型厚度进行有效考虑,计算所得铰链力矩误差小于5%。Calculating hinge moments during the morphing process is a critical link in the aircraft design with a folding wing.Existing simulations mostly use the traditional lifting surface method for aerodynamic modeling,which ignores the influence of the airfoil thickness and causes a great calculation error.This paper introduced a steady high-order panel method that considered the airfoil thickness and presented an aerodynamic modeling strategy using the high-order panel method to modify the thickness of the lifting surface method.The modified aerodynamic model was then coupled with the flexible multibody model and the flight control model to simulate the flight morphing process of a folding wing.The results show that the modified aerodynamic model can effectively consider the airfoil thickness,and the calculation error of the hinge moment is less than 5%.

关 键 词：折叠翼 变体飞行器 动力学仿真 飞行仿真 铰链力矩 高阶面元法 

分 类 号：V212[航空宇航科学与技术—航空宇航推进理论与工程]