Redesigning of a Canard Control Surface of an Advanced Fighter Aircraft: Effect on Buckling and Aerodynamic Behavior
A redesign of canard control-surface of an advanced all-metallic fighter aircraft was carried out by using carbon fibre composite (CFC) for ribs and panels. In this study ply-orientations of CFC structure are optimized using a Genetic-Algorithm (GA) with an objective function to have minimum failure index (FI) according to Tsai-Wu failure criterion. The redesigned CFC structure was sufficiently strong to withstand aerodynamic loads from stress and deflection points of view. Now, in the present work CFC canard structure has been studied for its buckling strength in comparison to existing metallic design. In this study, the existing metallic design was found to be weak in buckling. Upon a detailed investigation, it was revealed that there are reported failures in the vicinity of zones where initial buckling modes are excited as predicted by the finite element based buckling analysis. In view of buckling failures, the redesigned CFC structure is sufficiently reinforced with stringers at specific locations. After providing reinforcements against buckling, the twist and the camber variations of the airfoil are checked and compared with existing structure data. Finally, the modal analysis has been carried out to compare the variation in excitation frequency due to material change. The CFC structure thus redesigned is safe from buckling and aerodynamic aspects as well.
-  Shrivastava S., Mohite P.M., Design and optimization of a composite canard control surface of an advanced fighter aircraft under static loading, Curved Layer. Struct., 2015, 2, 91-105.
-  Hexel Composites, Product Data of HexPlyIM7/8552 Carbon Fiber Epoxy matrix laminate, 2013,
-  Holland J.H., Complex adaptive systems, Daedalus, 1992, 121, 17-30.
-  Balaji C., Madadi R.R., Optimization of the location of multiple discrete heat sources in a ventilated cavity using artificial neural networks and micro genetic algorithm, Int. J. Heat Mass Transfer, 2008, 51, 2299-2312.
-  Carlos E.S.C., Hodges H.D., Patil J.M. Aeroelastic analysis of composite wings, In: Proceedings of 37th Structures, Structural Dynamics and Materials Conference (15-17 April 1996, Salt Lake City, Utah, USA) AIAA J, 1996, 1-11.
-  De Leon D.M., de Souza C.E., Fonseca J.S.O., da Silva R.G.A., Aeroelastic tailoring of composite plates through eigenvalues optimization, Mecánica Computacional, 2010, 29, 609-623.
-  Kumar M.M., Jacob C.V., Lakshminarayana N., Puneeth B.M., Nagabhushana M., Buckling analysis of woven glass epoxy laminated composite plate. Am. J. Eng. Res., 2013, 2, 33-40.
-  Guo S.J., Stress concentration and buckling behavior of shear laded composite panel with reinforced cutouts, Compos. Struct., 2007, 80, 1-9.
-  Abramovich H., Weller T., Bisagni C., Buckling behavior of composite laminated stiffened panels under combined shear-axial compression, J. Aircraft, 2008, 45, 402-413.[WoS]
-  Natarajan S., Ferreira A.J.M., Nguyen-Xuan H., Analysis of crossply laminated plates using isogeometric analysis and unified formulation. Curved Layer. Struct., 2014, 1, 1-10.
-  Almeida F.S., Awruch A.M., Design optimization of composite laminated structures using genetic algorithms and finite element analysis, Compos. Struct., 2009, 88, 443-454.
-  Hassan G.A., Fahmy M.A., Goda I.M., The effect of fiber orientation and laminate stacking sequences on the torsional natural frequencies of laminated composite beams, J. Mech. Design Vib., 2013, 1, 20-26.
-  Rajappan R., Pugazhenthi V., Finite element analysis of aircraft wing using composite structure. Int. J. Eng. Sci., 2013, 2, 74-80.
-  Mohazzab A.H., Dozio L., Prediction of natural frequencies of laminated curved panels using refined 2-D theories in the spectral collocation method, Curved Layer. Struct., 2015, 2, 1-14.
-  Bachrach W., Kodiyalam S., Effective mechanical properties strategy for modal analysis and optimization of composite structures, Compos. Eng., 1995, 5, 1-7.
-  Hariri H., Bernard Y., Razek A., A two dimensions modeling of non-collocated piezoelectric patches bonded on thin structure, Curved Layer. Struct., 2014, 2, 2353-7396.
-  Christensen R. M., Lo K.H., Solutions for effective shear properties in three phase sphere and cylinder models, J. Appl. Mech. Phys. Solids, 1979, 27, 315-330.
-  Tsai S.W., Wu E.M., A general theory of strength for anisotropic materials, J. Compos. Mat., 1971, 5, 58-80.
-  MIL-STD-8591, Airborne Stores, Suspension Equipment and Aircraft-store Interface (Carriage Phase), Department of Defense USA, Design Criteria's for Standard, 12th Dec 2009.
-  Shames I.H., Clive D., Energy and Finite Element Methods in Structural Mechanics SI Unit Edition, Taylor&Francis, New York, 1991.
-  Thomson W.T., Theory of Vibration with Application 4th Edition, Stanley Thrones Publishers Ltd, 1998.