Flex Wing Fabrication and Static Pressure Testing

Abstract

This report documents the fabrication of flex wings in a manufacturing summary and experimental tests performed with a static pressure loading apparatus. The purpose of the static pressure tests were to simulate a typical aerodynamic pressure loading applied to the flex wing. A pressure loading was applied to the flex wing until failure occurred. The maximum normal force and root bending moment were calculated to predict the performance of the flex wing. Test results indicated a maximum root bending moment of 205 and 246 in-lbs for the .012 and .016 inch wings, respectively. These results compared well with previous studies. The results of the static pressure tests will be used to verify the finite element model 1 and build the flex wing data base. It is recommended that the effects of collapse and stowage deformations on the flex wing flight load performance be further studied.

Open PDF

Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1995
Accession Number
ADB200629

Entities

People

  • Larry D. Lucas

Organizations

  • United States Army Aviation and Missile Command

Tags

Communities of Interest

  • Autonomy
  • Energy and Power Technologies
  • Weapons Technologies

DTIC Thesaurus Topics

  • Aircrafts
  • Airframes
  • Assembly
  • Department Of Defense
  • Engineering
  • Engineers
  • Fabrication
  • Internal Pressure
  • Jet Propulsion
  • Load Cells
  • Manufacturing
  • Security
  • Spot Welding
  • Spot Welds
  • Strain Gages
  • Tensile Strength
  • Test And Evaluation

Readers

  • Aerodynamics/Aeronautics.
  • Materials Science
  • Mechanical Engineering/Mechanics of Materials.