NASA Logo, External Link
Facebook icon, External Link to NASA STI page on Facebook Twitter icon, External Link to NASA STI on Twitter YouTube icon, External Link to NASA STI Channel on YouTube RSS icon, External Link to New NASA STI RSS Feed AddThis share icon
 

Record Details

Record 47 of 12518
Advances in Structural Integrity Analysis Methods for Aging Metallic Airframe Structures with Local Damage
Offline Availability: Go to Request Form
Author and Affiliation:
Starnes, James H., Jr.(NASA Langley Research Center, Hampton, VA United States)
Newman, James C., Jr.(NASA Langley Research Center, Hampton, VA United States)
Harris, Charles E.(NASA Langley Research Center, Hampton, VA United States)
Piascik, Robert S.(NASA Langley Research Center, Hampton, VA United States)
Young, Richard D.(NASA Langley Research Center, Hampton, VA United States)
Rose, Cheryl A.(NASA Langley Research Center, Hampton, VA United States)
Abstract: Analysis methodologies for predicting fatigue-crack growth from rivet holes in panels subjected to cyclic loads and for predicting the residual strength of aluminum fuselage structures with cracks and subjected to combined internal pressure and mechanical loads are described. The fatigue-crack growth analysis methodology is based on small-crack theory and a plasticity induced crack-closure model, and the effect of a corrosive environment on crack-growth rate is included. The residual strength analysis methodology is based on the critical crack-tip-opening-angle fracture criterion that characterizes the fracture behavior of a material of interest, and a geometric and material nonlinear finite element shell analysis code that performs the structural analysis of the fuselage structure of interest. The methodologies have been verified experimentally for structures ranging from laboratory coupons to full-scale structural components. Analytical and experimental results based on these methodologies are described and compared for laboratory coupons and flat panels, small-scale pressurized shells, and full-scale curved stiffened panels. The residual strength analysis methodology is sufficiently general to include the effects of multiple-site damage on structural behavior.
Publication Date: Feb 01, 2003
Document ID:
20030019147
(Acquired Mar 21, 2003)
Subject Category: AERONAUTICS (GENERAL)
Document Type: Conference Paper
Publication Information: Ageing Mechanisms and Control: Specialists' Meeting on Life Management Techniques for Ageing Air Vehicles; 27-1 - 27-16; (RTO-MP-079(II)); (SEE 20030019125)
Financial Sponsor: NASA Langley Research Center; Hampton, VA United States
Organization Source: NASA Langley Research Center; Hampton, VA United States
Description: 16p; In English; Original contains color illustrations
Distribution Limits: Unclassified; Publicly available; Unlimited
Rights: Copyright; Distribution within the U.S. granted by agreement
NASA Terms: AIRCRAFT STRUCTURES; AIRFRAMES; CRACK PROPAGATION; FRACTURE MECHANICS; METAL SURFACES; AGING (MATERIALS); STRUCTURAL ANALYSIS; NONLINEARITY; PANELS; PRESSURE DISTRIBUTION; CORROSION; ALUMINUM; CYCLIC LOADS; DAMAGE ASSESSMENT; FINITE ELEMENT METHOD
› Back to Top
Find Similar Records
NASA Logo, External Link
NASA Official: Gerald Steeman
Site Curator: STI Program
Last Modified: September 26, 2017
Contact Us