Aeroelastic Tailoring of Blended Composite Panels with Lamination Parameters

Abstract:

An optimization method for blended composite panels with aeroelastic constraint is presented in this paper. On the basis of composite panel sub-region division, the lamination parameters of a guide laminate and length indicator of each ply of the guide laminate are introduced as design variables using parallel genetic algorithm (GA) for optimization. For each individual, the inverse problem of obtaining laminate configuration to target the lamination parameters is solved by another GA. The method of defining design variables can reduce the number of design variables obviously compared with previous work. And the numerical results indicate that the present method is capable of producing fully blended designs of composite wing with aeroelastic performance improvement and weight reduction.

• Periodical: Applied Mechanics and Materials (Volumes 401-403)
• Pages: 571-577
• DOI: https://doi.org/10.4028/www.scientific.net/AMM.401-403.571
• Online since: September 2013
• Authors: Peng Jin, Bi Feng Song, Xiao Ping Zhong
• Keywords: Aeroelastic Tailoring, Blended, Composite, Lamination Parameters

References

[1] M.H. Shirk, T.J. Hertz, and T.A. Weisshaar. Aeroelastic tailoring – theory, practice and promise. Journal of Aircraft , Vol. 23(1986), pp.6-18.

DOI: 10.2514/3.45260

[2] J.M. Housner, M. Stein. Flutter Analysis of swept-wing subsonic aircraft with parameter studies of composite wings. NASA TN D-7539(1974).

[3] K. Sogai. Direct search method to aeroelastic tailoring of a composite wing under multiple constraints. Journal of Aircraft, Vol. 26 (1989), pp.1076-1080.

DOI: 10.2514/3.45883

[4] S. Guo, W. Cheng, D.G. Cui. Aeroelastic tailoring of composite wing structures by laminate layup optimization. AIAA Journal, Vol. 44 (2006), p.3146–3149.

DOI: 10.2514/1.20166

[5] K.M. Kameyama, H. Fukunaga, Laminate Design of Composite Plate Wing for Aeroelastic Characteristics Using Real-coded Distributed Genetic Algorithms. AIAA 1st Intelligent Systems Technical Conference 20-22 September 2004, Chicago, Illinois.

DOI: 10.2514/6.2004-6440

[6] G.A. Soremekun, Z. Gürdal, and C. Kassapoglou. Stacking sequence blending of multiple composite laminates using genetic algorithm. Composite Structures, Vol. 56(2002), pp.53-62.

DOI: 10.1016/s0263-8223(01)00185-4

[7] B.P. Kristinsdottir, Z.B. Zabinsky, M.E. Tuttle, and S. Neogi. Optimum design of large composite panels with varying loads. Composite Structures, Vol. 51 (2001), pp.93-102.

DOI: 10.1016/s0263-8223(00)00128-8

[8] B. Liu, and R. T Haftka. Composite wing structural design optimization with continuity constraints, In: Proceedings of the 42nd AIAA/ASME/ASCE/AHA/ACS structures, structural dynamics and material conference, 2001 April 16-19; Seattle, WA.

DOI: 10.2514/6.2001-1205

[9] V.V. Toropov, R. Jones, and T. Willment. Weight and Manufacturability Optimization of Composite Aircraft Components Based on A Genetic Algorithm, Proceedings of 6th World Congress of SMO, Brazil(2005).

[10] D.B. Adams, L.T. Watson, Z. Gürdal, and C.M. Anderson. Genetic algorithm optimization and blending of composite laminates by locally reducing laminate thickness, Advances in Engineering Software (2004).

DOI: 10.1016/j.advengsoft.2003.09.001

[11] J. Campen, O. Seresta, and M.M. Abdalla. General blending definitions for stacking sequence design of composite laminate structures. In: 49th AIAA/ASME/ASCE/AHS/ASC structures, structural dynamics and material conference, Schaumburg.

DOI: 10.2514/6.2008-1798

[12] P. Jin, B.F. Song, and X.P. Zhong. Structure optimization of large composite wing with parallel genetic algorithm. Journal of Aircraft, Vol. 48 (2011), pp.2145-2148.

DOI: 10.2514/1.c031493

[13] MSC. Software Corporation. MSC/NASTRAN Aeroelastic Analysis User's Guide. (2003).

[14] C.G. Diaconu. Layup optimization for buckling of laminated composite shells with restricted layer angles. AIAA Journal, Vol. 42 (2004), p.2153–2163.

DOI: 10.2514/1.931