Author:
Zhao An-Min,Hui Zou,Liu De-Shan,Liu Bing-Fei
Abstract
In this paper, an innovative double rib sheet structure is proposed, which can replace the traditional rigid hinge joint with the surface contact. On the one hand, the variable camber wing structural design not only can improve the capacity to sustain more load but also will not increase the overall weight of the wing. On the other hand, it is a simple mechanical structure design to achieve the total wing camber change. Then the numerical simulation results show that the maximum stress at the connect of the wing rib is 88.2MPa, and the double ribs sheet engineering design meet the structural strength requirements. In addition, to make a fair comparison, the parameters of variable camber are fully referenced to the Talon Unmanned Aerial Vehicle (UAV). The results reveal that the total variable camber wing can further enhance aircraft flight efficiency by 29.4%. The design of the whole variable camber wing structure proposed in this paper has high engineering value and feasibility.
Reference12 articles.
1. POWERS S, WEBB L, FRIEND E, LOKOS W, editors. Flight test results from a supercritical mission adaptive wing with smooth variable camber. 28th National Heat Transfer Conference; 1992.
2. Zhu H, Liu WD, Zhao CS. Morphing Aircraft and Its Morph-driving Techniques[J]. Machine Building & Automation. 2010.
3. Kota S, Osborn R, Ervin G, Maric D, Flick P, Paul D. Mission Adaptive Compliant Wing – Design, Fabrication and Flight Test Mission Adaptive Compliant Wing[J]. 2006.
4. Airfoil Structural Morphing Based on S.M.A. Actuator Series: Numerical and Experimental Studies
Cited by
3 articles.
订阅此论文施引文献
订阅此论文施引文献，注册后可以免费订阅5篇论文的施引文献，订阅后可以查看论文全部施引文献