Accession Number:

AD0653563

Title:

FUSELAGE STRUCTURAL ANALYSIS. VOLUME 1. SHEAR AND BENDING

Descriptive Note:

Corporate Author:

GENERAL ELECTRIC CO CINCINNATI OH ADVANCED ENGINE AND TECHNOLOGY DEPT

Personal Author(s):

Report Date:

1964-02-01

Pagination or Media Count:

233.0

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.

Subject Categories:

  • VSTOL
  • Research and Experimental Aircraft

Distribution Statement:

APPROVED FOR PUBLIC RELEASE