STRESSES IN SKIN PANELS SUBJECTED TO RANDOM ACOUSTIC LOADING

Abstract

The report summarises the fully documented experimental data which is available on the stresses induced in typical aircraft structure by jet noise at take off. The experimental values are compared with a design procedure based on a single degree of freedom analysis and the method is extended for application to control surfaces and to integrally stiffened skin panels. The estimates are generally within a factor of two of the measured values. The relatively new phenomenon of shock cell noise is introduced and a typical result for the variation of r.m.s. stress during take off and climb is discussed.

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1967
Accession Number
AD0658846

Entities

People

  • Brian L. Clarkson

Organizations

  • University of Southampton

Tags

Communities of Interest

  • Air Platforms
  • Energy and Power Technologies

DTIC Thesaurus Topics

  • Air Force
  • Aircrafts
  • Airframes
  • Aspect Ratio
  • Control Surfaces
  • Experimental Data
  • Frequency
  • Frequency Bands
  • Fuselages
  • Jet Engines
  • Materials
  • Materials Laboratories
  • Measurement
  • Resonant Frequency
  • Static Pressure
  • Transport Aircraft
  • Vibration

Readers

  • Acoustics.
  • Aerodynamics/Aeronautics.
  • Structural Health Monitoring of Composite Structures.