Nonlinear Vibrations of Thin Arbitrarily Laminated Composite Plates Subjected to Harmonic Excitations Using DKT Elements

Chiang, C. K.; Xue, David Y.; Mei, Chuh

doi:10.2514/6.1993-1324

Cited by 1 publication

(1 citation statement)

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“…As this was developed, the nonlinear time functions were approximated such that they were simple harmonic functions by neglecting the higher harmonics. By applying a LUM/NTF approach, the nonlinear time function was linearised, as follows (18)(19)(20) :…”

Section: Formulationmentioning

confidence: 99%

Vibration analyses of an equivalent plate wing with an external store

Na¹,

Kim²,

Shin³

2014

Aeronaut. j. (1968)

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Generally, pylon-mounted external stores significantly affect the aerodynamic characteristics of the aircraft due to their flexibility (1) . Therefore, many investigations upon the dynamic and aeroelastic characteristics of an aircraft wing with external stores have been done over the last few decades (2)(3)(4) Recently, a study was carried out regarding the aeroelastic effects on wings by the engine placement (5) For severe operation conditions, classical linear theory with a small amount of amplitude vibration may not be an appropriate analysis (6) . Nonlinear vibration analysis will be required, especially when the amplitude of the vibration is larger than the wing thickness. Chia (7) performed static, dynamic, and post-buckling analyses of various isotropic and composite plates for that purpose. Dumir and Bhaskar derived finite element formulations to analyse the nonlinear vibration of beams and plates (8) . Moreover, the variational-asymptotic plate formulation (9) and the accompanying equations for the global analysis for the plates (10) have been studied. That approach accounted every possible geometrical non-linearity associated with large displacement and small strain.Paper No. 3992. Manuscript

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Section: Formulationmentioning

confidence: 99%