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2015 | 2 | 1 |

Tytuł artykułu

Design and Optimization of a Composite Canard Control Surface of an Advanced Fighter Aircraft under Static Loading

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The minimization of weight and maximization of payload is an ever challenging design procedure for air vehicles. The present study has been carried out with an objective to redesign control surface of an advanced all-metallic fighter aircraft. In this study, the structure made up of high strength aluminum, titanium and ferrous alloys has been attempted to replace by carbon fiber composite (CFC) skin, ribs and stiffeners. This study presents an approach towards development of a methodology for optimization of first-ply failure index (FI) in unidirectional fibrous laminates using Genetic-Algorithms (GA) under quasi-static loading. The GAs, by the application of its operators like reproduction, cross-over, mutation and elitist strategy, optimize the ply-orientations in laminates so as to have minimum FI of Tsai-Wu first-ply failure criterion. The GA optimization procedure has been implemented in MATLAB and interfaced with commercial software ABAQUS using python scripting. FI calculations have been carried out in ABAQUS with user material subroutine (UMAT). The GA's application gave reasonably well-optimized ply-orientations combination at a faster convergence rate. However, the final optimized sequence of ply-orientations is obtained by tweaking the sequences given by GA's based on industrial practices and experience, whenever needed. The present study of conversion of an all metallic structure to partial CFC structure has led to 12% of weight reduction. Therefore, the approach proposed here motivates designer to use CFC with a confidence.







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  • Department of Aerospace Engineering, Indian Institute of Technology Kanpur, UP, India 208016
  • Department of Aerospace Engineering, Indian Institute of Technology Kanpur, UP, India 208016


  • [1] Holland J.H., Complex adaptive systems, Daedalus, 1992, 121, 17-30.
  • [2] 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, 1008, 51, 2299-2312.
  • [3] Callahan K.J., Weeks G.E., Optimum design of composite laminates using genetic algorithm, Compos. Eng., 1992, 2, 149-160.
  • [4] Ball N.R., Sargent P.M., Ige D.O., Genetic algorithm representations for laminate layups, Artif. Intell. Eng., 1993, 8, 99-108.[Crossref]
  • [5] 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.
  • [6] Soremekun G., Gürdal Z., Haftka R.T., Watson L.T., Composite laminate design optimization by genetic algorithm with generalized elitist selection. Comput. Struct., 2001, 79, 131-143.[Crossref]
  • [7] Lopez R.H., Lursen M.A., Cursi J.E.S., Optimization of hybrid laminated composites using a genetic algorithm, J. Braz. Soc. Mech. Sci. & Eng., 2009, 31, 269-278.[Crossref]
  • [8] Liu B., Haftka R.T., Single-level composite wing optimization based on flexural lamination parameters. Struct. Multidisc. Optim., 2004, 26, 111-120.[Crossref]
  • [9] 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.
  • [10] Zhang Y., Xiong F., Yang S., Numerical simulation for composite wing structure design optimization of a mini type unmanned aerial vehicle. Open Mech. Eng. J., 2011, 5, 11-18.
  • [11] Shabeer K.P., Murtaza M.A., Optimization of aircraft wing with composite material, Int. J. Innov. Res. Sci. Eng. Technol., 2013, 2, 2471-2477.
  • [12] Todoroki A., Ishikawa A., Design of experiments for stacking sequence optimizations with genetic algorithm using response surface approximation, Compos. Struct., 2004, 64, 349-357.
  • [13] Hadjiloizi D.A., Kalamkarov A.L., Metti Ch., Georgiades A.V., Analysis of Smart Piezo-Magneto-Thermo-Elastic Composite and Reinforced Plates: Part I - Model Development, Curved Layer. Struct., 2014, 1, 11-31.
  • [14] Hadjiloizi D.A., Kalamkarov A.L., Metti Ch., Georgiades A.V., Analysis of Smart Piezo-Magneto-Thermo-Elastic Composite and Reinforced Plates: Part II – Applications, Curved Layer. Struct., 2014, 1, 32-58.
  • [15] Hashin Z., Rosen B.W., The elastic moduli of fibre-reinforced materials. J. Appl. Mech., 1964, 31, 223-232.[Crossref]
  • [16] Hashin Z., The elastic modulii of heterogeneous material, J. Appl. Mech., 1962, 31, 143-150.[Crossref]
  • [17] 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.
  • [18] Hexel Composites, Product Data of HexPlyIM7/8552 Carbon Fiber Epoxy matrix laminate, 2013,
  • [19] Herakovich C.T., Mechanics of Fibrous Composites, John Wiley & Sons, Inc. New York, 1998.
  • [20] MIL-STD-8591, Airborne stores, suspension equipment and Aircraft-store interface (Carriage Phase), Department of Defense, USA, Design Criteria's for Standard, 2009.
  • [21] Daley B.N., Lord D.R., Aerodynamic Characteristics of Several 6-Percent-Thick Airfoils at Angles of Attack From 0 degs to 20 degs at High Subsonic Speeds, NACA TN 3424, 1955.
  • [22] Tsai S.W., Wu E.M., A general theory of strength for anisotropic materials, J. Compos. Mat., 1971, 5, 58-80.[Crossref]
  • [23] Deb K., Pratap A., Agarwal S., Meyarivan T., A Fast and elitist multi-objective genetic algorithm: NSGA-II. IEEE Trans. Evol. Comput., 2002, 6, 187-192.[Crossref]
  • [24] Mohite P.M., NPTEL Course on Composite Materials and Structures,

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