An efficient finite element method for predicting critical temperature, postbuckling deflection and flutter response is developed for composite plates with embedded prestrained shape memory alloy (SMA) fibers. The temperature-dependent (TD) material properties of SMA and composites and the large panel deflections are considered in the formulation. The finite element formulation and solution procedure of the Incremental Updated Lagrangian (IUL) method for nonlinear TD material properties of SMA are presented briefly. Flow yaw angle at supersonic speed is also considered in the formulation. For the static solution, the system equations are solved using Newton-Raphson method to obtain aerothermal postbuckling deflection under combined aerodynamic and thermal loads. For the dynamic flutter response, the finite element modal method and time domain numerical integration are employed. Results show that the critical buckling temperature can be raised high enough so that buckling deflection can be eliminated, and the desired flat and stable region in the temperature-dynamic pressure operating domain can be enlarged greatly for composite surface panels with embedded SMA for supersonic vehicle applications. Weight savings based on critical temperature in using SMA are also presented.
Suppression of supersonic panel flutter and thermal deflection using shape memory alloy
2003
10 Seiten, 30 Quellen
Aufsatz (Konferenz)
Englisch
Suppression of Supersonic Panel Flutter and Thermal Deflection Using Shape Memory Alloy
British Library Conference Proceedings | 2003
|Supersonic Nonlinear Panel Flutter Suppression Using Shape Memory Alloys
Online Contents | 2007
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