R. Vaicaitis, P. Kavallieratos

The surface thermal protection systems of advanced high speed aircraft such as the National Aerospace Plane (NASP) will be constructed from high temperature resistant composite and intermetallic materials. The various dynamic response studies indicate that under severe aerodynamic, acoustic and thermal loads the response of these surface panels is nonlinear. The equations of motion for nonlinear response of composite surface panels are developed in space-time domain. A time domain Monte Carlo type approach is used to determine the nonlinear deflection and stress response solutions. The formulation includes surface loads due to nonsteady aerodynamic flow, cavity and static pressure, parametric excitations, turbulent boundary layer and engine exhaust noise, oscillating surface shocks and aerodynamic heating. Numerical results are presented for a simply supported laminated composite panel.

DGLR/AIAA 14th Aeroacoustics Conference, 1992

Conference Paper

englisch

21,0 x 29,7 cm, 10 Seiten

DGLR-Bericht, 1992, 1992-03, DGLR/AIAA 14th Aeroacoustics Conference - Proceedings; S.800-809; 1992; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

aeroacoustics

Bibliothek

1992