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Title: Experimental and analytical program to determine strains in 737 LAP splice joints subjected to normal fuselage pressurization loads

Abstract

The Federal Aviation Administration Technical Center (FAATC) has initiated several research projects to assess the structural integrity of the aging commercial aircraft fleet. One area of research involves the understanding of a phenomenon known as ``Widespread Fatigue Damage`` or WFD, which refers to a type of multiple element cracking that degrades the damage tolerance capability of an aircraft structure. Research on WFD has been performed both experimentally and analytically including finite element modeling of fuselage lap splice joints by the Volpe Center. Fuselage pressurization tests have also been conducted at the FAA`s Airworthiness Assurance NDI Validation Center (AANC) to obtain strain gage data from select locations on the FAA/AANC 737 Transport Aircraft Test Bed. One-hundred strain channels were used to monitor five different lap splice bays including the fuselage skin and substructure elements. These test results have been used to evaluate the accuracy of the analytical models and to support general aircraft analysis efforts. This paper documents the strain fields measured during the AANC tests and successfully correlates the results with analytical predictions.

Authors:
 [1];  [2]
  1. Sandia National Labs., Albuquerque, NM (United States)
  2. Department of Transportation, Cambridge, MA (United States). John A. Volpe National Transportation Systems Center
Publication Date:
Research Org.:
Sandia National Lab. (SNL-NM), Albuquerque, NM (United States)
Sponsoring Org.:
American Inst. of Aeronautics and Astronautics, Washington, DC (United States)
OSTI Identifier:
206946
Report Number(s):
SAND-96-0330C; CONF-960424-1
ON: DE96007421
DOE Contract Number:  
AC04-94AL85000
Resource Type:
Conference
Resource Relation:
Conference: American Institute of Aeronautics and Astronautics (AIAA)/American Society of Mechanical Engineers (ASME) structures, structural dynamics and materials conference, Salt Lake City, UT (United States), 15-17 Apr 1996; Other Information: PBD: [1996]
Country of Publication:
United States
Language:
English
Subject:
42 ENGINEERING NOT INCLUDED IN OTHER CATEGORIES; AIRCRAFT COMPONENTS; JOINTS; STRAINS; AIRCRAFT; FAILURES; CRACKS; SAFETY; INSPECTION; PRESSURIZATION; STRAIN GAGES

Citation Formats

Roach, D P, and Jeong, D Y. Experimental and analytical program to determine strains in 737 LAP splice joints subjected to normal fuselage pressurization loads. United States: N. p., 1996. Web.
Roach, D P, & Jeong, D Y. Experimental and analytical program to determine strains in 737 LAP splice joints subjected to normal fuselage pressurization loads. United States.
Roach, D P, and Jeong, D Y. 1996. "Experimental and analytical program to determine strains in 737 LAP splice joints subjected to normal fuselage pressurization loads". United States. https://www.osti.gov/servlets/purl/206946.
@article{osti_206946,
title = {Experimental and analytical program to determine strains in 737 LAP splice joints subjected to normal fuselage pressurization loads},
author = {Roach, D P and Jeong, D Y},
abstractNote = {The Federal Aviation Administration Technical Center (FAATC) has initiated several research projects to assess the structural integrity of the aging commercial aircraft fleet. One area of research involves the understanding of a phenomenon known as ``Widespread Fatigue Damage`` or WFD, which refers to a type of multiple element cracking that degrades the damage tolerance capability of an aircraft structure. Research on WFD has been performed both experimentally and analytically including finite element modeling of fuselage lap splice joints by the Volpe Center. Fuselage pressurization tests have also been conducted at the FAA`s Airworthiness Assurance NDI Validation Center (AANC) to obtain strain gage data from select locations on the FAA/AANC 737 Transport Aircraft Test Bed. One-hundred strain channels were used to monitor five different lap splice bays including the fuselage skin and substructure elements. These test results have been used to evaluate the accuracy of the analytical models and to support general aircraft analysis efforts. This paper documents the strain fields measured during the AANC tests and successfully correlates the results with analytical predictions.},
doi = {},
url = {https://www.osti.gov/biblio/206946}, journal = {},
number = ,
volume = ,
place = {United States},
year = {Thu Feb 01 00:00:00 EST 1996},
month = {Thu Feb 01 00:00:00 EST 1996}
}

Conference:
Other availability
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