NON-LINEAR TRANSIENT RESPONSE OF FLUTTERING STIFFENED COMPOSITE PLATES SUBJECT TO THERMAL LOAD

✍ Scribed by I.K OH; I LEE; D.M LEE

• Publisher: Elsevier Science
• Year: 2001
• Tongue: English
• Weight: 577 KB
• Volume: 245
• Category: Article
• ISSN: 0022-460X
• DOI: 10.1006/jsvi.2001.3576

✦ Synopsis

Non-linear transient response of #uttering sti!ened composite plates subject to thermal loads has been analyzed. The "rst order shear deformable plate and Timoshenko beam theories are used for the "nite element modelling of a skin panel and sti!eners considering von Karman non-linear strain}displacement relationships. A supersonic piston theory is used for modelling aerodynamic loads. In order to "nd a critical #utter speed, linear #utter analysis of sti!ened laminated panels considering large aero-thermal de#ections has been performed. The #at and stable motion, limit cycle oscillation, and buckled but dynamically stable and chaotic motion of sti!ened laminated panels have been investigated using the implicit Newmark integration method. Results show that the increase of the height and number of sti!eners to reduce an aero-thermal de#ection 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 de#ections, limit cycle oscillations, periodic motions with large amplitude and chaotic oscillations, are observed in the time domain analysis.

2001 Academic Press