Advertisement

New Model and Analytical Review of Approaches to Buckling Problem Investigation of Structurally Anisotropic Aircraft Panels Made from Composite Materials

Conference paper
  • 356 Downloads
Part of the Lecture Notes in Electrical Engineering book series (LNEE, volume 622)

Abstract

The different approaches were analyzed to investigate the buckling problems of structurally anisotropic panels made from composite materials. One considered the studies of scientific schools from 2000 year to present time, mainly. The classification of mathematical models, analytical methods of calculations, numerical methods of calculations, and testing results is presented in this review. Aircraft composite structure design in the field of production technology is the outlook research trend. New mathematical model relations for the buckling investigation of structurally anisotropic panels comprising composite materials are presented in this study. The primary scientific novelty of this research is the further development of the theory of thin-walled elastic ribs related to the contact problem for the skin and the rib with an improved rib model. One considers the residual thermal stresses and the preliminary tension of the reinforcing fibers with respect to panel production technology. The mathematical model relations for the pre-critical stress state investigation of structurally anisotropic panels made of composite materials are presented. Furthermore, the mathematical model relations for the buckling problem investigation of structurally anisotropic panels made of composite materials are presented in view of the pre-critical stress state. The critical force definition of the general bending mode of the thin-walled system buckling and the critical force definition of the multi-wave torsion buckling are of the most interest in accordance with traditional design practices. In both cases, bending is integral with the plane stress state. Thus, the buckling problem results in the boundary value problem when solving for the eighth-order partial derivative equation in the rectangular field. The schematization of the panel as structurally anisotropic has been proposed as a design model when the critical forces of total bending mode of buckling are determined. For a multi-wave torsion buckling study, one should use the generalized function set. The solution is designed by a double trigonometric series and by a unitary trigonometric series. A computer program package is developed using the MATLAB operating environment. The computer program package has been utilized for multi-criteria optimization of the design of structurally anisotropic aircraft composite panels. The influence of the structure parameters on the level of critical buckling forces for bending and for torsion modes has been analyzed. The results of testing series are presented. The results of new calculations are presented.

Keywords

Review Panels made of composite materials Eccentric longitudinal and lateral set Thin-walled rib Non-symmetric package structure Force and technology temperature action Pre-critical stress state Buckling Bending mode Torsion mode 

Notes

Acknowledgements

The study was performed in the framework of the RFFI (the project № 17-08-00849/17).

References

  1. 1.
    Gavva LM, Endogur AI (2018) Statics and buckling problems of aircraft structurally-anisotropic composite panels with the influence of production technology. IOP Conf Ser: Mater Sci Eng 312(1):012009CrossRefGoogle Scholar
  2. 2.
    Setoodeh AR, Karami G (2003) A solution for the vibration and buckling of composite laminates with elastically restrained edges. Compos Struct 60(3):245–253CrossRefGoogle Scholar
  3. 3.
    Gangadhara PB (2008) Free vibration and buckling response of hat—stiffened composite panels under general loading. Int J Mech Sci 50(8):1326–1333CrossRefGoogle Scholar
  4. 4.
    Mittelstedt C, Schroder KU (2010) Local postbuckling of hat-stringer stiffened composite laminated plates under transverse compression. Compos Struct 92:2830–2844CrossRefGoogle Scholar
  5. 5.
    Yshii LN, Lucena Neto E, Monteiro FAC, Santana RC (2018) Accuracy of the buckling predictions of anisotropic plates. J Eng Mech 144(8):04018061CrossRefGoogle Scholar
  6. 6.
    Ragb O, Matbuly MS (2017) Buckling analysis of composite plates using moving least squares differential quadrature method. Int J Comput Methods Eng Sci Mech 18(6):292–301MathSciNetCrossRefGoogle Scholar
  7. 7.
    Castro SGP, Donadon MV (2017) Assembly of semi-analytical models to address linear buckling and vibration of stiffened composite panels with debonding defect. Compos Struct 160:232–247CrossRefGoogle Scholar
  8. 8.
    Shukla KK, Nath Y (2002) Bucklingg of laminated composite rectangular plates under transient thermal loading. Trans ASME J Appl Mech 69(5):684–692CrossRefGoogle Scholar
  9. 9.
    Chen CS, Lin CY, Chen RD (2011) Thermally induced buckling of functionally grated hybrid composite plates. Int J Mech Sci 53:51–58CrossRefGoogle Scholar
  10. 10.
    Matsunaga H (2005) Thermal buckling of cross-ply laminated composite and sandwich plates according to a global higher-order deformation theory. Compos Struct 68(4):439–454CrossRefGoogle Scholar
  11. 11.
    Cetkovic M (2016) Thermal buckling of laminated composite plates using layerwise displacement model. Compos Struct 142:238–253CrossRefGoogle Scholar
  12. 12.
    Cetkovic M, Gyorgy L (2016) Thermo-elastic stability of angle-ply laminates-application of layerwise finite elements. Struct Integrity Life 16(1):43–48Google Scholar
  13. 13.
    Kettaf FZ, Benguediab M, Tounsi A (2015) Analytical study of buckling of hybrid multilayer plates. Periodica Polytech Mech Eng 59(4):164–168CrossRefGoogle Scholar
  14. 14.
    Naik NS, Sayyad AS (2019) An accurate computational model for thermal analysis of laminated composite and sandwich plates. J Therm Stresses 42(5):559–579CrossRefGoogle Scholar
  15. 15.
    Chen X, Dai S, Xu K (2001) Qinghua daxue xuebao. Ziran kexue ban 41(2):77–79, 83Google Scholar
  16. 16.
    Pandey R, Shukla KK, Jain A (2009) Thermoelastic stability analysis of laminated composite plates: an analytical approach. Commun Nonlinear Sci Numer Simul 14(4):1679–1699ADSCrossRefGoogle Scholar
  17. 17.
    Vescovini R, Dozio L (2015) Exact refined buckling solutions for laminated plates under uniaxial and biaxial loads. Compos Struct 127:356–368CrossRefGoogle Scholar
  18. 18.
    Kazemi M (2015) A new semi-analytical solution for buckling analysis of laminated plates under biaxial compression. Arch Appl Mech 85:1667–1677CrossRefGoogle Scholar
  19. 19.
    Yeter E, Erklig A, Bulut M (2014) Hybridization effects on the bucking behavior of laminated composite plates. Compos Struct 118:19–27CrossRefGoogle Scholar
  20. 20.
    Abramovich H, Weller T, Bisagni C (2008) Buckling behavior of composite laminated stiffened panels under combined shear and axial compression. J Aircr 45(2):402–413Google Scholar
  21. 21.
    Huang L, Sheikh AH, Ng CT, Griffith MC (2015) An efficient finite element model for buckling analysis of grid stiffened laminated composite plates. Compos Struct 122:41–50CrossRefGoogle Scholar
  22. 22.
    Guo MW, Harik IE, Ren WX (2002) Buckling behavior of stiffened laminated plates. Int J Solid Struct 39(11):3039–3055CrossRefGoogle Scholar
  23. 23.
    Thankam VS, Singh G, Rao GV, Rath AK (2003) Thermal post-buckling behavior of laminated plates using a shear-flexible element based on coupled-displacement field. Compos Struct 59(3):351–359CrossRefGoogle Scholar
  24. 24.
    Tenek LT (2001) Postbuckling of thermally stressed composite plates. AIAA J 39(3):546–548ADSCrossRefGoogle Scholar
  25. 25.
    Tran LV, Wahab MA, Kim SE (2017) An isogeometric finite element approach for thermal bending and buckling analyses of laminated composite plates. Compos Struct 179:35–39CrossRefGoogle Scholar
  26. 26.
    Kumar S, Kumar R, Mandal S, Ranjan A (2018) Numerical studies on thin wall laminated composite panels under compressive loading. Int J Civ Eng Technol 9(6):586–594Google Scholar
  27. 27.
    Kumar S, Kumar R, Mandal S, Rahul AK (2018) The prediction of buckling load of laminated composite hat-stiffened panels under compressive loading by using of neural networks. Open Civ Eng J 12(1):468–480CrossRefGoogle Scholar
  28. 28.
    Zarei A, Khosravifard A (2019) A meshfree method for static and buckling analysis of shear deformable composite laminates considering continuity of interlaminar transverse shearing stresses. Compos Struct 2019:206–218CrossRefGoogle Scholar
  29. 29.
    Castro SGP, Donadon MV, Guimaraes TAM (2019) ES-PIM applied to buckling of variable angle tow laminates. Compos Struct 209:67–78CrossRefGoogle Scholar
  30. 30.
    Falzon B G, Stevens K, Davies GO (2000) Postbuckling behavior of a blade-stiffened composite panel loaded in uniaxial compression. Compos A 31(5):459–468Google Scholar
  31. 31.
    Park O, Haftka RT, Sakar BV, Starnes JH, Nagendra S (2001) Analytical-experimental correlation for a stiffened composite panel loader in axial compression. J Aircr 38(2):379–387CrossRefGoogle Scholar
  32. 32.
    Rouse M, Assadi M (2001) Evalutional of scaling approach for stiffened composite flat panels loaded in compression. J Aircr 38(5):950–955CrossRefGoogle Scholar
  33. 33.
    Ungbhakorn V, Singhatanagdid P (2003) Similitude invariants and scaling laws for buckling experiments on anti-symmetrically laminated plates subjected to biaxial loading. Compos Struct 59(4):455–465CrossRefGoogle Scholar
  34. 34.
    Baker DJ (2000) Evaluation of thin Kevlar-epoxy fabric panels subjected to shear loading. J Aircr 1(37):138–143CrossRefGoogle Scholar
  35. 35.
    Zhao W, Xie Z, Wang X, Li X, Hao J (2019) Buckling behavior of stiffened composite panels with variable thickness skin under compression. Mech Adv Mater StructGoogle Scholar
  36. 36.
    Bai R, Bao S, Lei Z, Liu D, Yan C (2018) Experimental study on compressive behavior of I-stiffened CFRP panel using fringe projection profilometry. Ocean Eng 160:382–388CrossRefGoogle Scholar
  37. 37.
    Kumar S, Kumar R, Mandal S (2018) Behavior of FRP composite panel subjected to inplane loading. Int J Civ Eng Technol 9(6):1324–1332Google Scholar
  38. 38.
    Sanchez ML, De Almeida SFM, Carrillo J (2017) Evaluation of the effect of thermal residual stress on buckling and post-buckling of composite plates with lateral reinforcement. Revista Latinoamericana de Metalurgia y Materiales 37(1):45–49Google Scholar
  39. 39.
    Firsanov VV, Gavva LM (2017) The investigation of the bending form of buckling for structurally-anisotropic panels made of composite materials in operating MATLAB system. Struct Mech Eng Constr Build 4:66–76 (in Russian)CrossRefGoogle Scholar

Copyright information

© Springer Nature Singapore Pte Ltd. 2020

Authors and Affiliations

  1. 1.Department of Aircraft Design, Department of Machine ComponentsMoscow Aviation Institute (NRU)MoscowRussia

Personalised recommendations