Selection of the Optimal Structural Design of a Spar Composite Wing

This paper describes a method for optimizing the design of a spar-type composite aircraft wing structure based on multi-criterion approach. Two types of composite wing structures such as two-spar and three-spar ones were considered. The optimal design of a wing frame was determined by the Pareto method basing on three criteria: minimal weight, minimal wing deflection, maximal safety factor and minimal weight. Positions of wing frame parts, i.e. spars and ribs, were considered as optimization parameters. As a result, an optimal design of a composite spar-type wing was proposed. All the calculations necessary to select the optimal structural and design of the spar composite wing were performed using nonlinear static finite element analysis in the FEMAP with NX Nastran software package.

References

[1] Reznik S.V., Ageeva T.G., Dudar E.N. Complex method for construction design of reusable spacecraft wing. Aviakosmicheskaya tekhnika i tekhnologiya [Aerospace technology], 2010, no. 2, pp. 3–8. (In Russ.).

[2] Morgulets S.V., Chernetsov A.A., Afanas’yev A.V., et al. A complex method for design engineering of the PCM thin-walled structures - case study of an aircraft wing torsion box. Aviatsionnaya promyshlennost’ [Aviation Industry], 2012, no. 1, pp. 37–41. (In Russ.).

[3] Ageeva T.G., Mikhaylovskiy K.V. Substantiation of the choice of materials for the wing of tourist class suborbital reusable space vehicle. Inzhenernyy zhurnal: nauka i innovatsii [Engineering Journal: Science and Innovation], 2016, no. 10, doi: http://dx.doi.org/10.18698/2308-6033-2016-10-1543 (in Russ.).

[4] Reznik S.V., Prosuntsov P.V., Ageeva T.G. Optimal design of the suborbital reusable spacecraft wing made of polymer composite. Vestnik NPO im. S.A. Lavochkina, 2013, no. 1, pp. 38–43. (In Russ.).

[5] Khong F.N., Biryuk V.I. Research on optimization of structural layout of the straight-wing aircraft made from composite materials. Trudy MFTI [Proceedings of Moscow institute of physics and technology], 2014, vol. 6, no. 2, pp. 133–141. (In Russ.).

[6] Tatarnikov O.V., Karpenkov K.S. Development of a computer simulation approach for honeycomb constructions for aerospace application. IOP Conf. Ser.: Mater. Sci. Eng., 2015, vol. 74, art. 012016, doi: https://doi.org/10.1088/1757-899X/74/1/012016

[7] Aung P.W., Tatarnikov O., Aung N.L. Structural optimization of a light aircraft composite wing. IOP Conf. Ser.: Mater. Sci. Eng., 2020, vol. 709, art. 044094, doi: https://doi.org/10.1088/1757-899X/709/4/044094

[8] Wang Y., Ouyang X., Yin H., et al. Structural-optimization strategy for composite wing based on equivalent finite element model. J. Aircr., 2016, vol. 53, no. 2, pp. 351–359, doi: https://doi.org/10.2514/1.C033469

[9] Schuhmacher G., Daoud F., Petersson Q., et al. Multidisciplinary airframe design optimization. Proc. ICAS, 2012, paper ICAS 2012-0.4.

[10] Martins J.R.R.A., Lambe A.B. Multidisciplinary design optimization: a survey of architectures. AIAA J., 2013, vol. 51, no. 9, pp. 2049–2075, doi: https://doi.org/10.2514/1.J051895

[11] Zhu W., Yu X., Wang Y. Layout optimization for blended wing body aircraft structure. Int. J. Aeronaut. Space Sci., 2019, vol. 20, pp. 879–89, doi: https://doi.org/10.1007/s42405-019-00172-7

[12] Likeng H., Zhenghong G. Wing-body optimization based on multi-fidelity surrogate model. Proc. ICAS., 2012, pp. 633–640.

[13] Kirubakaran R. Aircraft wing weight optimization by composite material structure design configuration. IOSR-JMCE, 2017, vol. 14, no. 6, pp. 71–80.

[14] Zhitomirskiy G.I. Konstruktsiya samoletov [Aircraft construction]. Moscow, Mashinostroenie Publ., 2005. 406 p. (In Russ.).