Simplified procedures for the analyses of random thermal acoustic responses
of aircraft structures are derived using equivalent lineanization and the
Fokker-Plank equation. Experimental results are obtained for an aluminum pl
ate with combined radiant heating and base excitation. Base excitation can
provide a flat frequency spectrum of uniform pressure excitation whereas lo
udspeaker devices will give standing wave and coupling effects. The nonline
ar dynamic behaviour of the acoustic response of thermally buckled plates f
rom the theoretical results agreed with those from the experimental results
. The most important dynamic behaviour is the presence of low frequency dyn
amic snap-through motion which changed the static equilibrium slate of the
buckled plate. Also the nonlinear dynamic behaviour changed from the harden
ing spring type to the softening spring type due to the snap through motion
. It is found that the Fokker-Planck equation gives an accurate prediction
of the intermittent snapthrough response where as the equivalent linearizat
ion give a good prediction for continuous snap-through response. (C) 2000 P
ublished by Elsevier Science Ltd. All rights reserved.