Non-linear transient response of fluttering stiffened composite plates subject to thermal load

Cited 14 time in webofscience Cited 0 time in scopus
  • Hit : 380
  • Download : 0
Non-linear transient response of fluttering stiffened composite plates subject to thermal loads has been analyzed. The first order shear deformable plate and Timoshenko beam theories are used for the finite element modelling of a skin panel and stiffeners considering von Karman non-linear strain-displacement relationships. A supersonic piston theory is used for modelling aerodynamic loads. In order to find a critical flutter speed, linear flutter analysis of stiffened laminated panels considering large aero-thermal deflections has been performed. The flat and stable motion, limit cycle oscillation, and buckled but dynamically stable and chaotic motion of stiffened laminated panels have been investigated using the implicit Newmark integration method. Results show that the increase of the height and number of stiffeners to reduce an aero-thermal deflection can dramatically drop the boundaries of a dynamic stability at a certain point. Also, the non-linear behaviors, such as dynamically stable motions with static aero-thermal deflections, limit cycle oscillations, periodic motions with large amplitude and chaotic oscillations, are observed in the time domain analysis. (C) 2001 Academic Press.
Publisher
ACADEMIC PRESS LTD
Issue Date
2001-08
Language
ENG
Article Type
Article
Appears in Collection
AE-Journal Papers(저널논문)
This item is cited by other documents in WoS
⊙ Detail Information in WoSⓡ Click to see webofscience_button
⊙ Cited 14 items in WoS Click to see citing articles in records_button

qr_code

  • mendeley

    citeulike


rss_1.0 rss_2.0 atom_1.0