Nonlinear Equations of Motion for a Panel Subject to External Loads

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.

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Document Details

Document Type
Technical Report
Publication Date
Nov 01, 1993
Accession Number
ADA273142

Entities

People

  • Mark A. Hopkins

Organizations

  • Flight Dynamics Laboratory

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aerodynamic Forces
  • Aeroelasticity
  • Composite Materials
  • Computational Fluid Dynamics
  • Computational Science
  • Differential Equations
  • Equations
  • Equations Of Motion
  • Fluid Dynamics
  • Fluid Flow
  • Kinetic Energy
  • Mach Number
  • Materials
  • Static Loads
  • Static Pressure
  • Supersonic Flow
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Structural Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow