vcct(虛擬裂紋擴(kuò)展分析技術(shù)).doc

Vcct (Virtual crack closure technique)Interlaminar fracture mechanics characterizes the onset of delaminations in composites. Shear loading causes the panel to buckle and the resulting out-of-plane deformations initiate skin/stringer separation at the location of an embedded defect.METHOD: Finite Element AnalysisELEMENT: the panel and surrounding load fixture were modeled with shell elements. A small section of the stringer foot and the panel in the vicinity of the embedded defect were modeled with a local 3D soil model.1. BACKGROUNDAerospaces structures are made of flat or cured panels with co-cured or adhesively bonded frames and stiffeners computational stress analysis to determine the location of first matrix cracking.An artificial defect was placed at the termination of the center stiffener. The stiffened panel is subjected to pure shear loading which causes the panel to buckle.ANALYSIS: nolinear finite element analysisStrain energy release rates and mixed made ratios were computed using the virtual crack closure technique.2. METHODOLOGY2.1 Interlaminar fracture mechanicsThe total strain energy release rate The mode I component due to interlaminar tension The mode II component due to interlaminar sliding shear The mode III component due to interlaminar scissoring shear Purpose: to predict delamination onset or growth for two-dimensional problems, theses calculated G components are compared to interlaminar fracture toughness properties measured over a range of mode mixities from pure mode I loading to pure mode II loading.A quasi static mixed-mode fracture criterion is determined by plotting the interlaminar fracture toughness,versus the mixed-mode ratio, , determined from data generated using pure Mode I () Double Cantilever Bending (DCB) pure Mode II () four point End Notched Flexure (4ENF), and Mixed Mode Bending (MMB) tests of varying ratio for IM7/8852 carbon epoxy material. and are the fracture toughness data for mode I and II is a factor determined by the cure fit. Shown in figure 3 in this article.Failure is expected when, for a given mixed mode ratio, the calculated total energy release rate, exceeds the interlaminar fracture toughness, .2.2 . Analysis Tools2.2.1. Virtual Crack Closure TechniqueVCCT requires force and displacement input, which is obtained from continuum (2-D) and solid (3-D) finite element analyses of the cracked (2-D) or delaminated (3-D) component. and are calculated for four-noded elements is the length of the elements at the crack front; and are the forces at the crack tip (nodal point i);The relative displacements behind the crack tip are calculated from the nodal displaces For geometric nonlinear analysis where large deformations may occur, both forces and displacements obtained in the global coordinate system need to be transformed into a local coordinate system () which originates at the crack tip.For the two-dimensional eight-noded quadrilateral element with quadratic shape functions this yieldsThe total energy release rate is calculated from the individual mode components aswhere for the two-dimensional case discussed.In a finite element model made of three-dimensional solid elements the delamination of length a is represented as a two-dimensional discontinuity by two surfaces. (why does it is discontinuity?)The model I, mode II, and mode III components of the strain energy release rate,and are calculated as. Here is the area virtually closes, is the length of the elements at the delamination front, and b is the width of the elements.A local crack tip coordinate system is needed.2.2.2. A Global/Local Shell 3D Modeling TechniqueComputed mixed mode strain energy release rate components depend on many variables such as element order and shear deformation assumptions, kinematic constraints in the neighborhood of the delamination front, and continuity of material properties and section stiffness in the vicinity of the debond when delaminations or debonds are modeled with plate or shell finite elements.3. FINITE ELEMENT MODELING3.1. Global Shell Model of Stringer Stiffened PanelThe global model includes the steel load frame and attachments, the panel made of graphite/epoxy prepreg tape and the stringers made of graphite/epoxy fabric. The outer steel load frame and the attachment bolts were modeled with beam elements available in the element software ABAQUS. The inner steel load frame which overlaps the panel edge was modeled with standard shell S4 elements. The shell elements ate connected by beam elements designed to enforce plate theory constraints. In the sections containing the artificial defects the beam elements were replaced by gap elements. In preparation for the global/local modeling approach shell elements representing the foot of the stiffener and the panel were removed from the original shell model around the center stringer termination as shown in Figure 9. The shell elements used to model the stiffener web and hat were kept in place. At the boundaries shell edges in ABAQUAS were defined as shown which were used to connect the shell model with the local 3D insert model using the shell to solid coupling option in ABAQUS which allows the connection between non-conforming shell and solid models.3.2 Local 3D Insert Model for Solid Modeling of Stringer Foot and Panel SkinThe local 3D insert model was generated using C3D8I solid brick elements and consisted of an intact section and a delaminated section with a fine mesh around the delamination front. Surfaces were defined on the outer faces of the insert model to provide a connection with the global shell model using the shell to solid coupling option in ABAQUS. The initial defect is located at the bondline between stringer foot and the panel. This defect was treated as a delamination and modeled as a discrete discontinuity using two unconnected nodes with identical coordinates one on each side of the delamination. A refined mesh was used along the stringer boundary in order to capture edge effects. Using the finite sliding option available in ABAQUS contact was modeled between the delamination surfaces to avoid interpenetration during analysis.3.3. Combined Global/Local Shell/3D Model of Stringer Stiffned PanelUniform displacements u, v were applied at one corner node to introduce shear as shown in Figure 11a. The inplane displacements u, v were suppressed at the diagonally opposite corner and the out of plane displacement w were suppressed along all four edges across the entire width of the inner and outer steel load frame.The global shell model was connected to the local 3D insert model using the shell to solid coupling option in ABAQUS which allows the connection between non-conforming shell and solid models. For the entire analyses the non-linear solution option was used in ABAQUS. A total of eight delamination lengths were modeled. Additional lengths were chosen to study the change in energy release rate distribution across the width (b) of the stringer with increasing delamination length (a).4. ANALYSIS RESULTS4.1 Deformed PanelThe longer caused a change in the stiffness which resulted in an altered buckling pattern.Early in the analysis (increment 5) a mode I opening was observed only near one edge. With increasing applied external displacement the deformation changed locally and for increment 15 mode I disappeared completely and the delamination appeared closed over the entire delaminated length. A small scissoring shear (mode III) could be observed. Further increasing the external displacement resulted in a small mode I opening across the entire width of the stringer as observed for increment 20. For the last step of the analysis (increment 41) after the entire external displacement u=v=6.35mm had been applied mode I opening was observed across the entire width of the stringer over the entire delaminated length.The figure reveals that not the entire delaminated section opens under mode I. After initial opening, the section below the web termination closes and the delaminated surfaces contact. This closing is caused by a change in the local buckling pattern, due to stiffness changes caused by the longer delamination, as discussed above. It was observed that the local buckling pattern in the immediate surrounding of the delaminated stringer is dependent on thedelamination length modeled, which made convergence difficult.4.2 Calculation of Mixed-Mode Strain Energy Release Rates and Failure IndicesVCCT was used to calculate the mode contributions ，and the total energy release rate ,as well as the mixed mode ratios along the dela