Panel stiffener debonding analysis using a shell/3D modeling technique
Source abstract
Abstract
A shear loaded, stringer reinforced composite panel is analyzed to evaluate the fidelity of computational fracture mechanics analyses of complex structures. Shear loading causes the panel to buckle. The resulting out-of-plane deformations initiate skin/stringer separation at the location of an embedded defect. The panel and surrounding load fixture were modeled with shell elements. A small section of the stringer foot, web and noodle as well as the panel skin near the delamination front were modeled with a local 3D solid model. Across the width of the stringer foot, the mixed-mode strain energy release rates were calculated using the virtual crack closure technique. A failure index was calculated by correlating the results with a mixed-mode failure criterion of the graphite/epoxy material. The objective was to study the effect of the fidelity of the local 3D finite element model on the computed mixed-mode strain energy release rates and the failure index.
Source: openaire · Quality: candidate unverified · Source record ↗
Research context
OpenAlex topics: Mechanical Behavior of Composites · Fatigue and fracture mechanics · Structural Response to Dynamic Loads
SciVX discovery tags are terminology-based. OpenAlex topics are source-provided classifications.
References (23)
Show source-provided references
1. Failure of thick-skinned stiffener runout sections loaded in uniaxial compression10.1016/S0263-8223(01)00006-X ↗
2. The analysis of skin-to-stiffener debonding in composite aerospace structures10.1016/S0263-8223(02)00110-1 ↗
3. Minguet PJ, Fedro MJ, O’Brien TK, Martin RH, Ilcewicz LB. Development of a structural test simulating pressure pillowing effects in bonded skin/stringer/frame configuration. In: Proceedings of the fourth NASA/DoD advanced composite technology conference, Salt Lake City, Utah; 1993.
4. Minguet PJ, O’Brien TK. Analysis of test methods for characterizing skin/stringer debonding failures in reinforced composite panels. In: Composite materials: testing and design (vol. 12), ASTM STP 1274; 1996. p. 105–24.10.1520/STP16541S ↗
5. Testing and analysis of composite skin/stringer debonding under multi-axial loading10.1177/002199830003401502 ↗
6. Fatigue life methodology for bonded composite skin/stringer configurations10.1520/CTR10971J ↗
7. O’Brien TK. Fracture mechanics of composite delamination. In: ASM handbook, vol. 21, composites: ASM international; 2001. p. 241–5.10.31399/asm.hb.v21.a0003380 ↗
8. Krueger R, Minguet PJ. Skin-stiffener debond prediction based on computational fracture analysis, NIA Report No. 2005–06, NASA/CR-2005–213915; 2005. .
9. Krueger R, Minguet PJ. Analysis of composite panel-stiffener debonding using a shell/3D modeling technique, NIA Report No. 2006–02, NASA/CR-2006–214299; 2006. .
10. A finite element calculation of stress intensity factors by a modified crack closure integral10.1016/0013-7944(77)90013-3 ↗
11. Virtual crack closure technique: history, approach and applications10.1115/1.1595677 ↗
12. ASTM D 5528-94a. Standard test method for mode I interlaminar fracture toughness of unidirectional fiber-reinforced polymer matrix composites. In: Annual book of ASTM standards, vol. 15.03; 2000.
13. ASTM D 6671-01. Standard test method for mixed-mode I–mode II interlaminar fracture toughness of unidirectional fiber-reinforced polymer matrix composites. In: Annual book of ASTM standards, vol. 15.03; 2000.
14. Mode II fracture toughness evaluation using a four point bend end notched flexure test10.1179/146580199101540565 ↗
15. Measurement of mixed-mode delamination fracture toughness of unidirectional glass/epoxy composites with mixed-mode bending apparatus10.1016/0266-3538(96)00005-X ↗
16. A new mode III delamination test for composites10.1177/096369359200100501 ↗
17. An edge crack torsion method for mode III delamination fracture testing10.1520/CTR10369J ↗
18. Nodal constraint shear deformation and continuity effects related to the modeling of debonding of laminates using plate elements
19. A shell/3D modeling technique for the analysis of delaminated composite laminates10.1016/S1359-835X(00)00133-0 ↗
20. Krueger R, Minguet PJ. Analysis of composite skin-stiffener debond specimens using a shell/3D modeling technique and submodeling, NIA Report No. 2004–04, NASA/CR-2004–212684; 2004. .
21. ABAQUS 6.6. Analysis user’s manual: ABAQUS, Inc.; 2005.
22. Minguet P. Boeing SARAP Status Report – Durability (2nd Quarter 2002); 2002.
23. Krueger R, Ratcliffe JG, Minguet PJ. Analysis of composite panel-stiffener debonding using a shell/3D modeling technique, NIA Report No. 2007–07, NASA/CR-2007–214879; 2007. .