Testing and analysis of flat and curved panels with multiple cracks

Broek, David; Jeong, David Y.; Thomson, Douglas; John A. Volpe National Transportation Systems Center, (U.S.); Foster-Miller, Inc.

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Testing and analysis of flat and curved panels with multiple cracks

1994-08-01
By Broek, David ; Jeong, David Y. ; Thomson, Douglas

[PDF-718.16 KB]

English

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Details:

Creators:

Broek, David ; Jeong, David Y. ; Thomson, Douglas

Broek, David ; Jeong, David Y. ; Thomson, Douglas Less -
Corporate Creators:

John A. Volpe National Transportation Systems Center, (U.S.) ; Foster-Miller, Inc.

John A. Volpe National Transportation Systems Center, (U.S.) ; Foster-Miller, Inc. Less -
Subject/TRT Terms:

[+]

Aircraft Structural Components Cracking Fatigue Cracking Fuselages Laboratory Tests Panels Residual Strength Static Loads
Resource Type:

Tech Report
Geographical Coverage:

United States
Corporate Publisher:

United States. Federal Aviation Administration
NTL Classification:

NTL-SAFETY AND SECURITY-Vehicle Design;NTL-SAFETY AND SECURITY-SAFETY AND SECURITY;NTL-SAFETY AND SECURITY-Aviation Safety/Airworthiness;NTL-AVIATION-AVIATION;NTL-AVIATION-Aviation Safety/Airworthiness;
Abstract:

An experimental and analytical investigation of multiple cracking in various types of test specimens is described in this paper. The testing phase is comprised of a flat unstiffened panel series and curved stiffened and unstiffened panel series. The test specimens contained various configurations for initial damage. Static loading was applied to these specimens until ultimate failure, while loads and crack propagation were recorded. This data provides the basis for developing and validating methodologies for predicting linkup of multiple cracks, progression to failure, and overall residual strength. The results from twelve flat coupon and ten full scale curved panel tests are presented. In addition, an engineering analysis procedure was developed to predict multiple crack linkup. Reasonable agreement was found between predictions and actual test results for linkup and residual strength for both flat and curved panels. The results indicate that an engineering analysis approach has the potential to quantitatively assess the effect of multiple cracks in the arrest capability of an aircraft fuselage structure.
Format:

PDF
Alternate URL:

http://adsabs.harvard.edu/abs/1994asim.nasa...85B
Collection(s):

Volpe Center
Main Document Checksum:

[+]

urn:sha256:3fe7f2858c599f1849e5786df457b99ab976d6f3c950deab35b013eb0a39bf92
Download URL:

https://rosap.ntl.bts.gov/view/dot/11759/dot_11759_DS1.pdf
File Type:

No Additional Files

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Testing and analysis of flat and curved panels with multiple cracks

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