太阳能无人机机翼几何非线性气动弹性分析  

Geometrically Nonlinear Aeroelastic Analysis of a Solar UAV Wing

作　　者：胡志勇[1] 尤伍 张健[1] HU Zhiyong;YOU Wu;ZHANG Jian(AVIC The First Aircraft Institute,Xi’an 710089,China)

机构地区：[1]中航工业第一飞机设计研究院

出　　处：《空军工程大学学报（自然科学版）》2019年第2期1-6,共6页Journal of Air Force Engineering University(Natural Science Edition)

基　　金：科技部国际合作专项项目(2013DFA80710);中国航空工业集团公司技术创新基金(16R010001)

摘　　要：以大展弦比机翼为研究对象,结合几何非线性结构有限元建模方法与非线性气动力计算技术,提出了一种利用插值技术求解几何非线性气动弹性问题的方法。并以某太阳能无人机机翼缩比模型为例进行计算分析以及试验研究。研究结果表明:提出的方法得到非线性颤振解与常规方法得到的计算结果基本一致,但应用此方法后,不仅计算效率成倍提高,而且能规避常规方法中由于计算工况设定不合理可能导致的严重计算偏差。In this paper,taking the large aspect ratio wing as a research object,and combined with the geometric nonlinear structure finite element modeling method and the nonlinear aerodynamic calculation technology,a interpolation method is proposed to solve the geometically nonlinear aeroelastic problem.Taking a scaled model of solar UAV wing as an example,the calculation and analysis and experimental research are carried out.The resuts show that the nonlinear flutter solution obtained by the method in this paper is basically the same as that obtained by the conventional method.By so doing,not only the calculation efficiency is doubled,but also the serious calculation deviation may be avoided in the conventional method,which may result from the unreasonable setting of the calculation working condition.

关 键 词：太阳能无人机 几何非线性 气动弹性 风洞试验 

分 类 号：V215.3[航空宇航科学与技术—航空宇航推进理论与工程]