Affiliation:
1. Nanjing University of Science and Technology
Abstract
This paper introduces a new kind of flexible wing with embedded piezoelectric actuator as framework for Micro Air Vehicles (MAV), which was fixed spar in the previous flexible wing. This made it a controllable flexible wing because the new flexible wing can not only works as previous model without control, but also can change its wing profiles in our purpose by using the embedded piezoelectric actuator when its necessary. The mathematical model of the deformation of piezoelectric actuator under control has developed. with which the structure of the flexible wing was designed. The simulation of dynamic characteristic of the flexible wing with embedded piezoelectric actuator has been done with ANSYS software.
Publisher
Trans Tech Publications, Ltd.
Reference14 articles.
1. A.Y.N. Sofla, S.A. Meguid, K.T. Tan , W.K. Yeo. Shape morphing of aircraft wing: Status and challenges. Materials and Design 31 (2010) 1284–1292.
2. YONGSHENG LIAN. MEMBRANE AND ADAPTIVELY-SHAPED WINGS FOR MICRO AIR VEHICLES. UNIVERSITY OF FLORIDA (2003).
3. Liu Ya-wel, Huang Jun. Research of the Latest Development Trends of Fixed-wing Micro Aerial Vehicles. AERO W EAP0NRY. 2008 No．1.
4. Wang Jindong, Zhou Zhaoying, ZHU Rong, SONG Yuning. Flight stability of flexible wing micro air vehicles. J Tsinghua Univ(Sci &. Tech), 2006, Vol 46, No. 1l.
5. Hong J. Zhang, Yu Zhou, Li Cheng. Control of Flow Separation from an Airfoil Using Piezo-Ceramic Actuators. AIAA 2006-3689.