Accession Number:

ADA361350

Title:

C-5 A Fuselage Stress Analysis.

Descriptive Note:

Final rept. Jun 91-Mar 92,

Corporate Author:

CSA ENGINEERING INC PALO ALTO CA

Personal Author(s):

Report Date:

1992-06-01

Pagination or Media Count:

15.0

Abstract:

This report describes the work performed to provide analytical predictions that can be used to address cracking problems that have arisen in particular areas of the C-5A forward fuselage section. The specific objective of the present study was to investigate various factors in as much detail as possible that are likely to contribute to cracking of the fuselage skin. Three distinct activities were undertaken to establish the cause of skin cracking review and evaluation of available data, creation and execution of test plans, and performance of static and dynamic stress analysis results from tests were used to validate analytical models. Recommendations for a follow-on study and possible fixes based on results obtained to date are presented.

Subject Categories:

  • Aircraft
  • Test Facilities, Equipment and Methods

Distribution Statement:

APPROVED FOR PUBLIC RELEASE