Volume 18, Issue 2 (4-2018)
Modares Mechanical Engineering 2018, 18(2): 314-322 |
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moharami S, Irani S, Shams S, Fallah M. The flutter speed and effect of laminate layers of composite wing carrying two powered engines. Modares Mechanical Engineering 2018; 18 (2) :314-322
URL: http://mme.modares.ac.ir/article-15-3171-en.html
URL: http://mme.modares.ac.ir/article-15-3171-en.html
1- student of Aerospace Engineering, K. N . University of Technology, Tehran, Iran.
2- Department of new sciences and technologis
3- student of Aerospace Engineering, K. N . University of Technology, Tehran, Iran
2- Department of new sciences and technologis
3- student of Aerospace Engineering, K. N . University of Technology, Tehran, Iran
Abstract: (3993 Views)
In this article, the Flutter speed of a composite wing carrying two power engines is analyzed. The wing is modeled as a beam with two degrees of freedom, which is a cantilever, with two thrust as a follower force and mass of the engines. Wagner theory has been used for aerodynamic model and using the assumed mode, the wing dynamic equations of the motion has been achieved by Lagrange equations. Linear flutter speed according to the eigenvalues of the motion equations was calculated. In order to valid the results of present work, at first composite wing assumed without engines and then wing modeled with two engines that results are compared with published results and good agreement has been observed. Composite wing has been analyzed as one layer and also laminate layers, and effect of variables such as follower force, engines mass, position of engines and number of layers has been investigated and the results show that with increase in mass and force of engines and also with increases distance between engine and wing root, flutter speed decreases and with decrease distance between engines and leading edge, flutter speed increases.
Keywords: Instability, Flutter, Wing, Composite
Article Type: Research Article |
Subject:
Aerospace Structures
Received: 2017/10/17 | Accepted: 2018/01/5 | Published: 2018/02/10
Received: 2017/10/17 | Accepted: 2018/01/5 | Published: 2018/02/10
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