Study on Damage Tolerance Behavior of Integrally Stiffened Panel and Conventional Stiffened Panel
The damage tolerance behavior of integrally and
conventional stiffened panel is investigated based on the fracture
mechanics and finite element analysis. The load bearing capability
and crack growth characteristic of both types of the stiffened panels
having same configuration subjected to distributed tensile load is
examined in this paper. A fourteen-stringer stiffened panel is
analyzed for a central skin crack propagating towards the adjacent
stringers. Stress intensity factors and fatigue crack propagation rates
of both types of the stiffened panels are then compared. The analysis
results show that integral stiffening causes higher stress intensity
factor than conventional stiffened panel as the crack tip passes
through the stringer and the integrally stiffened panel has less load
bearing capability than the riveted stiffened panel.
[1] R.G. Pettit, J. J. Wang, and C. Toh. Validated Feasibility Study of
Integrally Stiffened Metallic Fuselage Panels for Reducing
Manufacturing Costs, NASA/CR-2000-209342.
[2] B. R. Seshadri, J. C. Newman, Jr., D. S Dawicke and R. D. Young.
Fracture analysis of the FAA/NASA wide stiffened panels, NASA/TM-
1998-208976.
[3] Richard D. Young, Marshall Rouse, Damodar R. Ambur, and James H.
Starnes, Jr. Residual strength pressure tests and nonlinear analyses of
stringer- and frame-stiffened aluminum fuselage panels with longitudinal
cracks, NASA no. 19990021207, 1998.
[4] David Broek. Elementary Engineering Fracture Mechanics, Martinus
Nijhoff Publishers, 1982,pp.408-433.
[5] C. C. Poe. Crack Propagation in Stiffened Panels, ASTM STP 486,
1971.
[1] R.G. Pettit, J. J. Wang, and C. Toh. Validated Feasibility Study of
Integrally Stiffened Metallic Fuselage Panels for Reducing
Manufacturing Costs, NASA/CR-2000-209342.
[2] B. R. Seshadri, J. C. Newman, Jr., D. S Dawicke and R. D. Young.
Fracture analysis of the FAA/NASA wide stiffened panels, NASA/TM-
1998-208976.
[3] Richard D. Young, Marshall Rouse, Damodar R. Ambur, and James H.
Starnes, Jr. Residual strength pressure tests and nonlinear analyses of
stringer- and frame-stiffened aluminum fuselage panels with longitudinal
cracks, NASA no. 19990021207, 1998.
[4] David Broek. Elementary Engineering Fracture Mechanics, Martinus
Nijhoff Publishers, 1982,pp.408-433.
[5] C. C. Poe. Crack Propagation in Stiffened Panels, ASTM STP 486,
1971.
@article{"International Journal of Mechanical, Industrial and Aerospace Sciences:49714", author = "M. Adeel", title = "Study on Damage Tolerance Behavior of Integrally Stiffened Panel and Conventional Stiffened Panel", abstract = "The damage tolerance behavior of integrally and
conventional stiffened panel is investigated based on the fracture
mechanics and finite element analysis. The load bearing capability
and crack growth characteristic of both types of the stiffened panels
having same configuration subjected to distributed tensile load is
examined in this paper. A fourteen-stringer stiffened panel is
analyzed for a central skin crack propagating towards the adjacent
stringers. Stress intensity factors and fatigue crack propagation rates
of both types of the stiffened panels are then compared. The analysis
results show that integral stiffening causes higher stress intensity
factor than conventional stiffened panel as the crack tip passes
through the stringer and the integrally stiffened panel has less load
bearing capability than the riveted stiffened panel.", keywords = "Conventional Stiffened Structure, Damage
Tolerance, Finite Element Analysis, Integrally Stiffened Structure,
Stress Intensity Factor.", volume = "2", number = "9", pages = "1008-5", }