| Issue |
MATEC Web Conf.
Volume 233, 2018
8th EASN-CEAS International Workshop on Manufacturing for Growth & Innovation
|
|
|---|---|---|
| Article Number | 00006 | |
| Number of page(s) | 8 | |
| DOI | https://doi.org/10.1051/matecconf/201823300006 | |
| Published online | 21 November 2018 | |
Dynamic Force Analysis of a Novel Mechanism for Chord and Camber Morphing Wing Under Aerodynamic Loading
1
Graduate Research Assistant, Department of Aerospace Engineering, METU, Republic of Turkey
2
Undergraduate Student, Department of Aerospace Engineering, METU, Republic of Turkey
3
Professor, Department of Aerospace Engineering, METU, Republic of Turkey
* e-mail: hlsahin@metu.edu.tr
In this paper, the dynamic force analysis of a novel deployable mechanism, called as scissor-structural mechanism (SSM), for active camber and chord morphing have been presented. The mechanism is created via combination of several scissor-like-elements (SLEs). With a novel kinematic synthesis concept, various types of scissor-like-elements are assembled together to provide the desired airfoil geometries. The types (translational, polar), the number of scissor-like-elements, their orientations with respect to centerline of the airfoil and their distribution frequencies over the chord length are the design parameters, which allow designers to achieve all the possible geometric shapes. With the assumption of an existing fullycompliant wing skin, it is possible to adjust the wing profile to various desired airfoil geometries. With the help of developed computer routine, the mechanism is generated which yields the minimum possible design error. After the selection of mechanism, the position, velocity and acceleration analyses of the mechanism have been done. In order to prove aerodynamic efficiency of newly created airfoil geometries and obtain pressure distribution over the airfoil, 2D aerodynamic analyses have been done with the package program XFOIL. The flow characteristics used for the analysis are determined by the flight envelope of a generic UAV. Obtained pressure distribution is applied as the lumped force on the joints. By assigning the approximate link masses and mass centers, the dynamic force analysis of the mechanism has also been performed in order to estimate the required torque to drive the synthesized mechanism.
© The Authors, published by EDP Sciences, 2018
This is an Open Access article distributed under the terms of the Creative Commons Attribution License (http://creativecommons.org/licenses/by/4.0), which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.
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