Accession Number:

ADA273142

Title:

Nonlinear Equations of Motion for a Panel Subject to External Loads

Descriptive Note:

Interim rept. Jan 1992-Oct 1993

Corporate Author:

AIR FORCE FLIGHT DYNAMICS LAB WRIGHT-PATTERSON AFB OH

Personal Author(s):

Report Date:

1993-11-01

Pagination or Media Count:

46.0

Abstract:

The equations of motion of a constant thickness, rectangular panel subject to external static loads and unsteady supersonic aerodynamic forces is derived. Both isotropic and orthotropic panels are examined. The static loads come from in-plane forces, a temperature differential, and a pressure differential. The equations allow for slight initial curvature due to manufacturing imperfections. The equations are derived using a nonlinear strain- displacement relationship which permits both linear and nonlinear panel response studies. First order piston theory predicts the unsteady aerodynamic forces due to the supersonic flow over the upper surface. Nonlinear equations, Plate theory, Piston theory, Aeroelasticity.

Subject Categories:

  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE