Comparison of 2D finite element modeling assumptions with results from 3D analysis for composite skin-stiffener debonding

Composite Structures

Volumn 57, Issue 1-4, 2002, Pages 161-168

  Krueger, Ronald ^a   Paris, Isabelle L ^a   Kevin O'Brien, T ^a   Minguet, Pierre J ^b  

^a NASA LANGLEY RESEARCH CENTER   (United States)

^b BOEING COMPANY   (United States)

Author keywords

[No Author keywords available]

Indexed keywords

COMPUTER SIMULATION; DEBONDING; DELAMINATION; FINITE ELEMENT METHOD; STRAIN; STRESS CONCENTRATION; TENSILE STRESS;

ENERGY RELEASE RATES; SKIN-STIFFENERS;

COMPOSITE STRUCTURES;

COMPOSITE;

EID: 0036658948     PISSN: 02638223     EISSN: None     Source Type: Journal    
DOI: 10.1016/S0263-8223(02)00079-X     Document Type: Article

References (17)

1. Development of a structural test simulating pressure pillowing effects in bonded skin/stringer/frame configuration
2. Analysis of test methods for characterizing skin/stringer debonding failures in reinforced composite panels
3. Analysis of composite skin/stringer bond failures using a strain energy release rate approach
4. Analysis of the strength of the interface between frame and skin in a bonded composite fuselage panel
5. Fatigue debonding characterization in composite skin/stringer configurations
6. Testing and analysis of composite skin/stringer debonding under multiaxial loading
7. Fatigue life methodology for bonded composite skin/stringer configurations
8. A finite element calculation of stress intensity factors by a modified crack closure integral
9. Calculation of strain-energy release rates with higher order and singular finite elements
10. 2D- and 3D-applications of the improved and generalized modified crack closure integral method
11. A shell/3d modeling technique for the analysis of delaminated composite laminates
12. Strength and fatigue life modeling of bonded joints in composite structure
13. Convergence of strain energy release rate components for edge-delaminated composite laminates
14. Influence of specimen preparation and specimen size on composite transverse tensile strength and scatter