The Effect of Laminated Layers on the Flutter Speed of Composite Wing
محتوى المقالة الرئيسي
الملخص
The paper presents an investigation to the flutter speed of composite wing for different ply orientation. Structurally the composite wing was idealized as a composite beam load carrying structure. Theodorsen’s expression was used to get the 2- dimension unsteady lifting force and pitching moment in the limit of incompressible flow and subsonic speed which were integrated over the wing span. A free vibration analysis was first carried out to get the natural frequencies and mode shapes .The velocity-damping (V-g) method was used to calculate the flutter speed and the flutter frequency. A wing of unmanned aerial vehicle was manufactured from woven glass and polyester resin where the flutter speed was calculated experimentally by the wind tunnel test .The flutter speed was calculated analytically for different ply orientation, it is found that the increasing in torsion rigidity leads to increase in the flutter speed, the fiber combination with high torsion rigidity and relatively low coupling rigidity give higher flutter speed.
تفاصيل المقالة
كيفية الاقتباس
تواريخ المنشور
المراجع
Attaran " Structural Optimization of an Aero elastically Tailoring Composite Flat Plate Made of Woven Fiberglass/Epoxy ” Department of
Aerospace of Engineering University Putra Malaysia , Jurnal Mekanikal , No. 22,p. 75-88 December, 2006.
ASTM International "D 3039-07 Standard test method for Tensile Properties of Polymer Matrix Composite Materials", 2011.
Banerjee " Flutter Analysis of COMPOSITE Wings Using Symbolic Computation" Department of Mechanical Engineering and Aeronautics, City University,2000 .
Banerjee" A dynamic stiffness element for free vibration analysis of composite beams and its application to aircraft wings". Department of Mechanical Engineering and Aeronautics, City University,2007.
Daniel " Aeroelastic Tailoring of Composite Plates Through Eigenvalues Optimization" Buenos Aires, Argentina, 2010.
Dayang Laila Abang Haji Abdul Majid ShahNor Basri “ LCO flutter of cantilevered woven 10 glass/epoxy laminate in subsonic flow”
Department of Aerospace Engineering, Faculty of Engineering, Universiti Putra Malaysia ,2008.
Eric L.Brown "Integrated Strain Actuation In Aircraft With Highly Flexible Composite Wings" Doctor of Philosophy thesis, Massachusetts
Institute of Technology,2003.
Guo, Bannerjee and Cheung "The Effect of Laminate Lay-Up on the Flutter Speed of Composite Wings"journal of aerospace engineering,vol.207 No.3,p.115-122 June 2003.
Guo" Aeroelastic optimization of an aerobatic aircraft wing structure" Department of Aerospace Engineering, School of Engineering, Cranfield University UK, Aerospace Science and Technology (2007).
Güclü Seber " Flutter Analysis of a Tapered Wing Using Assumed Modes Method", 2009. William T.Thomson , Marie Dillon and
Chandramouli Padmanabhan "Theory of Vibration With Applications". Pearson, Fifth edition 2010.
Hodges and Pierce," Aeroelasticity" Georgia Institute of Technology, Atlanta, Georgia ,2009.
Mayuresh J.patil "Aeroelastic Tailoring of Composite Box Beam" Georgia Institute of Technology ,Atlanta ,Georgia , AIAA 1997.
Mayuresh J. Patil" Nonlinear Aeroelastic Analysis , Flight Dynamics ,and Control of a Complete Aircraft" Doctor of Philosophy thesis, Georgia Institute of Technology,1999.
Masaki Kameyama"Optimum design of composite plate wings for aeroelastic characteristics using lamination parameters"computer and structure,(2007) .
Majid and Basri " Flutter Analysis of a Hybrid Plate-like Fiber-Reinforced composite wing" Department of Aerospace Faculty of Engineering Universiti Putra Malaysia,2011.
NASA" Basic Mechanics of laminated composite plates" NASA reference publication 1351,1994. Stephan Borneman" Calculating Effective Rigidities of a Laminated Composite Beam (Classical Laminate Theory)", 2010.
Suleman" Design and Testing of a Morphing Wing for an Experimental UAV" University of Victoria, Canada,2007.
Wang " Vibration Analysis of Cracked Composite Bending-torsion Beams for Damage Diagnosis" Doctor of Philosophy thesis, university of Virginia,2004.
Zhanming Qin" Vibration and Aeroelasticity of Advanced Aircraft Wings Modeled as ThinWalled Beams , Dynamics, Stability and Control "Doctor of Philosophy thesis, university of Virginia,2001.