Abstract
This paper presents development of finite element model of sailplane LAK-17B fuselage, which will be used to demonstrate the compliance with requirements of strength, deformation, crashworthiness and flutter behavior. FE analysis may be used only if the structure conforms to those for which experience has shown the method to be reliable. LAK-17B is a modification of a certified sailplane LAK-17A. Compliance with strength requirements of this sailplane was confirmed by load tests. Data of these tests will be used to evaluate numerical model reliability. The article presents modeling principles used to create finite element models of the sailplanes LAK-17A and LAK-17B together with consideration of load evaluation procedure.
About this article
Received
July 5, 2012
Accepted
September 4, 2012
Published
September 30, 2012
Keywords
finite element model
sailplane
fuselage
Copyright © 2012 Vibroengineering
This is an open access article distributed under the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.
