Accession Number : ADA320011

Title :   Engineering Approach to Damage Tolerance Analysis of Fuselage Skin Repairs.

Descriptive Note : Final rept.,

Corporate Author : FEDERAL AVIATION ADMINISTRATION TECHNICAL CENTER ATLANTIC CITY NJ

Personal Author(s) : Bakuckas, J. G., Jr. ; Chen, C. C. ; Yu, J. ; Tan, P. W. ; Bigelow, C. A.

PDF Url : ADA320011

Report Date : NOV 1996

Pagination or Media Count : 29

Abstract : A simplified approach to damage tolerance analysis of riveted fuselage skin repairs has been incorporated in a new user-friendly software package, Repair Assessment Procedure and Integrated Design (RAPID). In this study, the damage tolerance analysis methodology in RAPID was evaluated in terms of the fastener loads, stress-intensity factor solutions, crack growth, residual strength, and inspection schedule. Three example problems, each representing a typical fuselage skin repair configuration, were analyzed. The analysis results obtained from RAPID were compared with results generated using a Representative Original Equipment Manufacturer (ROEM) method and a special purpose finite element program for fracture mechanics analysis and crack growth simulation in layered two dimensional structures. In general, results generated using RAPID were in good agreement with results generated using the ROEM method and the finite element code.

Descriptors :   *DAMAGE ASSESSMENT, *FUSELAGES, *TOLERANCES(MECHANICS), STRESSES, COMPUTER PROGRAMS, SIMULATION, METHODOLOGY, INTEGRATED SYSTEMS, MANUFACTURING, LAYERS, TWO DIMENSIONAL, FINITE ELEMENT ANALYSIS, STRUCTURES, INTENSITY, STRENGTH(MECHANICS), FRACTURE(MECHANICS), CODING, CRACK PROPAGATION, REPAIR, ENGINEERING, SCHEDULING, RESIDUALS, CONFIGURATIONS, INSPECTION, RIVETS, USER NEEDS, SIMPLIFICATION, SKIN(GENERAL), STRESS CONCENTRATION.

Subject Categories : Aircraft
      Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE