FUSELAGE STRUCTURAL ANALYSIS. VOLUME 1. SHEAR AND BENDING

Abstract

The final stress analysis of the U. S. Army XV-5A lift fan research aircraft forward and aft fuselage sections is presented. The forward and aft sections of the fuselage are conventional aircraft semi-monocoque structures, and the center section is a welded tubular space truss. The analysis of the longitudinal bending members and skins or webs is contained. The primary intent of the report is to provide a tabulation of internal shear and bending stress distributions for the final critical loading conditions. Critical margins of safety of primary components are computed. Structural adequacy was also demonstrated by proof tests simulating the critical conditions. All loads shown are ultimate values.

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Document Details

Document Type
Technical Report
Publication Date
Feb 01, 1964
Accession Number
AD0653563

Entities

Organizations

  • General Electric

Tags

DTIC Thesaurus Topics

  • Aircrafts
  • Army Aviation
  • Axial Loads
  • Bending Stress
  • Box Beams
  • Cockpits
  • Fuselages
  • Government Procurement
  • Governments
  • Landing Gear
  • Lift Fans
  • Nose Wheels
  • Research Aircraft
  • Roll
  • Shear Flow
  • Stresses
  • Wheel Wells

Readers

  • Aerospace Engineering
  • Business Analytics
  • Structural Dynamics.

Technology Areas

  • Space