Aeroelasticity of composite plates with curvilinear fibres in supersonic flow
Source abstract
Abstract
Abstract The target of this investigation is to understand the aeroelastic (dynamic or static) instability of variable stiffness composite laminates (VSCLs) in the presence of supersonic airflow. The studied VSCLs have curvilinear fibre paths. Two different types of VSCLs are considered: the first type (already adopted in several previous researches) includes fibre path angles changing linearly from T 1 at right and left edges to T 0 at the centre, and the second type (not introduced before) includes fibre paths where their angles change linearly from T 0 at the left edge to T 1 at the right edge. Displacements and rotations in the plate are modelled by a Third-order Shear Deformation Theory (TSDT) and are discretised by a p -version finite element model . Aerodynamic forces due to supersonic airflow, in the steady or unsteady regime, are modelled using linear Piston theory and the equations of motion of the self-excited vibration system are formed using the principle of virtual work. Dynamic (flutter) and static (divergence) instabilities are identified using the eigenvalues of the linear system. Effects of different boundary conditions and various fibre angles as well as the influence of airflow direction on the flutter and divergence occurrence in VSCL plates are studied.
Source: openaire · Quality: candidate unverified · Source record ↗
Research context
OpenAlex topics: Composite Structure Analysis and Optimization · Vibration and Dynamic Analysis · Aeroelasticity and Vibration Control
SciVX discovery tags are terminology-based. OpenAlex topics are source-provided classifications.
References (41)
Show source-provided references
1. Tatting BF, Gurdal Z, Automated finite element analysis of elastically-tailored plates, Tech. Rep. CR-2003-212679, NASA; 2003.
2. Tatting BF, Gürdal Z, Jegley D, Design and manufacture of elastically tailored tow placed plates, Tech. Rep. CR-2002-211919, NASA; 2002.
3. Damage onset on tow-placed variable stiffness composite laminates10.1016/j.compstruct.2014.03.038 ↗
4. Akhavan · 2015
5. Waldhart · 1996
6. IJsselmuiden · 2011
7. The engineering aspects of automated prepreg layup: history, present and future10.1016/j.compositesb.2011.12.003 ↗
8. Mixed shell element for static and buckling analysis of variable angle tow composite plates10.1016/j.compstruct.2016.05.030 ↗
9. A new paradigm for the optimum design of variable angle tow laminates
10. Framework for the buckling optimization of variable-angle tow composite plates10.2514/1.J054029 ↗
11. Optimal design of tow-placed fuselage panels for maximum strength with buckling considerations10.2514/1.40357 ↗
12. Natural modes of vibration of variable stiffness composite laminates with curvilinear fibers10.1016/j.compstruct.2011.04.027 ↗
13. Design of variable stiffness composite panels for maximum fundamental frequency using lamination parameters10.1016/j.compstruct.2006.08.018 ↗
14. Design of variable-stiffness conical shells for maximum fundamental eigenfrequency10.1016/j.compstruc.2007.04.020 ↗
15. Geometrically non-linear static analysis of unsymmetric composite plates with curvilinear fibres: p-version layerwise approach10.1016/j.compstruct.2014.07.007 ↗
16. A p-version layerwise model for large deflection of composite plates with curvilinear fibres10.1016/j.compstruct.2013.09.014 ↗
17. Large deflection and stresses in variable stiffness composite laminates with curvilinear fibres10.1016/j.ijmecsci.2013.03.013 ↗
18. Free geometrically nonlinear oscillations of perfect and imperfect laminates with curved fibres by the shooting method10.1007/s11071-015-2043-z ↗
19. Non-linear forced periodic oscillations of laminates with curved fibres by the shooting method10.1016/j.ijnonlinmec.2015.06.004 ↗
20. Nonlinear free vibration analysis of variable stiffness symmetric skew laminates10.1016/j.euromechsol.2014.10.008 ↗
21. Geometrically non-linear periodic forced vibrations of imperfect laminates with curved fibres by the shooting method10.1016/j.compositesb.2016.10.059 ↗
22. Panel flutter analysis and optimization of composite tow steered plates
23. Comparison of curvilinear stiffeners and tow steered composites for aeroelastic tailoring of aircraft wings10.1016/j.compstruc.2017.01.010 ↗
24. Flutter analysis of laminated curvilinear-stiffened plates10.2514/1.J055021 ↗
25. Aeroelastic benefits of tow steering for composite plates10.1016/j.compstruct.2014.08.007 ↗
26. Aeroelastic tailoring of a representative wing box using tow-steered composites10.2514/1.J055364 ↗
27. Experimental and finite element modal analysis of variable stiffness composite laminated plates
28. On the equations of bending of plates
29. Reddy · 2004
30. An investigation into geometrically nonlinear analysis of rectangular laminated plates using the hierarchical finite element method10.1016/0168-874X(94)90107-4 ↗
31. Free vibration analysis of a flat plate using the hierarchical finite element method10.1016/0022-460X(91)90855-E ↗
32. Dowell · 2004
33. Piston theory-a new aerodynamic tool for the aeroelastician10.2514/8.3740 ↗
34. Multimode approach to nonlinear supersonic flutter of imperfect circular cylindrical shells10.1115/1.1435366 ↗
35. Amabili · 2008
36. Nonlinear supersonic flutter of circular cylindrical shells10.2514/2.1365 ↗
37. Aeroelastic behavior of cantilevered rotating rectangular plates10.1016/j.ijmecsci.2011.01.013 ↗
38. Using aeroelastic modes for nonlinear panel flutter at arbitrary supersonic yawed angle10.2514/2.1940 ↗
39. Flutter and buckling characteristics and active control of sandwich panels with triangular lattice core in supersonic airflow10.1016/j.compositesb.2016.10.013 ↗
40. An inverse trigonometric shear deformation theory for supersonic flutter characteristics of multilayered composite plates10.1016/j.ast.2016.02.017 ↗
41. Experimental and numerical research on aerodynamic characteristics of rectangular fin mounted vertically over the wing