• <tr id="yyy80"></tr>
  • <sup id="yyy80"></sup>
  • <tfoot id="yyy80"><noscript id="yyy80"></noscript></tfoot>
  • 99热精品在线国产_美女午夜性视频免费_国产精品国产高清国产av_av欧美777_自拍偷自拍亚洲精品老妇_亚洲熟女精品中文字幕_www日本黄色视频网_国产精品野战在线观看 ?

    Influence of Shim Layers on Progressive Failure of a Composite Component in Composite-Aluminum Bolted Joint in Aerospace Structural Assembly

    2018-03-29 07:36:09,*,,

    ,*,,

    1.Department of Aerospace Manufacturing Engineering,Jiangsu Key Laboratory of Precision and Micro-Manufacturing Technology,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,P.R.China;

    2.AVIC Xi′an Aircraft Industry(Group)Company LTD,Xi′an 710089,P.R.China

    0 Introduction

    Due to their high specific stiffness,higher specific strength and other better performances,composite materials are hugely being utilized in the aerospace industries for both civil and military applications[1,2].Although composite materials are extensively being used because of the aforementioned reasons,composite structures are susceptible to damage as a result of their brittle nature and other technical issues like shimming[3,4].Aluminum alloys,however,are still being used in the aerospace industry despite the growing usage of composite materials.An example of the use of hybrid materials (that is composite-metal structures)is the fighter jet JAS39Gripenas shown in Fig.1[5].Furthermore,some aircraft manufacturers like Airbus still maintain a significant percentage of aluminum alloys in its manufactured aircrafts(A320′s airframe is composed of aluminum alloy)which make the assembly of hybrid structures(composite-aluminum)inevitable.In the assembly of aerospace structural components,there are several mechanical fasteners employed and as a result,holes have to be drilled for the installation of these mechanical fasteners.Before starting to drill the hole and with subsequent fastener installation,it is imperative to check all joints for the presence of gaps.This is because the presence of gaps can needlessly preload the metallic members when fasteners are installed prompting a condition that can cause premature fatigue cracking and even stress corrosion cracking of an aluminum component.Howbeit,gaps in structures containing composites can cause even more serious problems than in metallic structures.Since composites do not yield and are more brittle and less lenient than metals,excessive gaps can result in delaminations when they are pulled out during fastener installation.

    Fig.1 Composite and metal materials in JAS39Gripen

    This phenomenon put the composite in a bending due to the exerted force by the fastener drawing the parts together and can develop matrix cracks and/or delaminations around the holes.Cracks and delaminations normally occur in multiple layers through the thickness and can significantly affect the joint strength[6].

    There have been several studies into the progressive failure of composite materials.Tsai and Wu[7]; Reddy and Pandey[8]; Turvey[9];and Hashin[10]revolutionized the studies into the progressive failures of composite materials.Other authors like Chang and Chang[11]developed the progressive damage analysis of notched laminated composites subjected to tensile loading.The progressive failure method employed in Ref.[11]was a nonlinear FEA that used the modified Newton-Raphson iteration technique to develop the state of stresses in a composite component.Also,Chang and Lessard[12]conducted an investigation into the damage in laminated composites containing an open hole subjected to a compressive loading.Contributing to the advances in failure theories of composite materials,Reddy et al.[13]evaluated both linear and non-linear first-ply failure loads of composite plates for different edge conditions and load cases.The apparent complexities associated with composite materials made the aforementioned failure theories to have had limitations which necessitated and motivated other authors to further refine these existing theories.An example of a refined theory for the progressive failure analysis of composite materials has been developed and successfully implemented in the works of Ref.[14].

    There has been some published literature on shimming[15-17],but most studies were skewed toward liquid shims[18-22].With regard to the analysis of failure of composite materials with ashim,the authors Hühne et al.[18];Dho^te et al.[19];Comer et al.[20];and Liu[22]conducted studies using single-lap bolted joints with a liquid shim.In investigations of Ref.[22],in particular,it was concluded that the stiffness of the joints decreased due to the presence of liquid shim,and the joint stiffness decreased with an increasing liquid shim thickness.Comer et al.[20]investigated thermomechanical fatigue tests on hybrid joints with liquid shim layers and concluded that there was no degradation in respect to the mechanical stiffness for the liquid shim.Zhai et al.[23]studied the effect of solid shim and liquid shim on compositealuminum bolted joints by using a 3DDigital Image Correlation.Although,the investigation of Ref.[23]was″supposed″to be about solid shim and liquid shim,however,it was carried out ex-perimentally hence the objective of this research to investigate the influence of both liquid and solid peelable fiberglass shim using finite element analysis and experimental study.

    1 Materials for Experimental Testing and Finite Element Modeling of Composite-Aluminum Bolted Joint

    The 3Dfinite element(FE)assembled model and the test specimens were an idealization of an aircraft′s wingbox sub-structural components.That is a composite wing panel and an aluminum rib.Aluminum alloy 7075-T651was chosen for this study because of its use in the aerospace industry for highly stressed and critical structural parts[6,7].The test specimens,as well as the FE model,were composed of the parts(Figs.2,3):A hi-shear corporation fastener with a protruding head(HST-12-8)and a washer all composed of aerospace grade titanium alloy (Ti-6Al-4VSTA);one plate made of the carbon fiber-reinforced polymer (CFRP) material-carbon-epoxy IMS-977-2(Cytec Industries Inc.)with the quasiisotropic stacking sequence being[+45/90/-45/0/90/0/-45/90/+45/-45]sand with a total ply thickness of 0.188mm for 20plies;the other plate is made of a high strength aerospace grade aluminum alloy,7075T651.Two CFRP support plates were adhesively bonded to the main plates to avoid excessive bending.Commercially available liquid shim material-Hysol EA9394of Henkel Corporation and a solid peelable fiberglass of LAMECO group manufactured under the COMAC standard CMS-MT-301were the other materials utilized.The FE model and the test specimens were based on the test standards of American Society for Testing and Materials(ASTM),D5961/D5961M-13[24]and recommendations in Ref.[20].The single-lap model of the composite-aluminum bolted joint specimen is shown in Figs.2,3.

    Fig.2 Dimensions in millimeter of the single-lap

    Fig.3 Dimensions in millimeter of the single-lap composite-composite-aluminum bolted joint without shim aluminum bolted joint with shim

    2 Finite Element Model

    A non-linear 3Dsolid elements model of a single-lap composite-aluminum assembled structure with and without shim layers under a quasistatic tensile loading was developed using the commercial FE program ABAQUS/Standard 6.13[25]and in accordance with Refs.[20,24].The developed model was without the doublers as shown in Fig.4.The bolt,collar,and the washer were modeled as a unit as shown in Fig.5because they were engaged together and they are composed of the same titanium material.There were nine different kinds of composite-aluminum bolted joints.Namely,without a shim,with a liquid shim (0.3,0.5,0.7and 0.9mm thickness)and with solid peelable fiberglass(0.3,0.5,0.7and 0.9mm thickness).

    The strength and elastic properties[26]for the carbon-epoxy IMS-977-2substrate are shown in Table 1.The meshed CFRP had a total number of 37 040elements after it has been seeded with 20 elements in the thickness direction,15elements equally distributed in the area covered by the fastener head and 20elements equally distributed on the half periphery of each fastener hole along the circumferential direction.Structured hexagonal mesh controls were assigned and a stack direction assigned in the isometric view.The meshed CFRP plate as shown in Fig.6was developed using the element type C3D8R:An eight-node linear brick,reduced integration,hourglass control in Abaqus.

    Fig.4 Developed model

    Fig.5 FE model of bolt-collar-washer

    Table 1 CFRP elastic and strength properties

    Fig.6 CFRP meshed FE model

    The aluminum plate and titanium parts were modeled using their elasto-plastic material behaviors as shown in Table 2.The AA7075-T651was modeled same as the CFRP with the only differences being the seeding in the thickness direction where 10elements were used and there was no assigning of stacking direction.The meshed AA7075-T651plate in Fig.7has a total number of 17 520elements.Titanium parts(meshed Ti-6Al-4VSTA is shown in Fig.8)were modeled same as the CFRP but with different approximate global size(0.6used)and mesh controls(sweep used).

    Fig.7 AA7075-T651meshed FE model

    The Hysol EA9394of Henkel Corporation and the solid peelable fiberglass were modeled using their elastic properties as shown in Table 3.The shim materials(an example shown in Fig.9is a meshed model of a shim with a thickness of 0.3mm)were also modeled same as the CFRP but with an approximate global size of 0.7and seeded with 3elements in the thickness direction for a shim thickness of 0.3mm (5elements and 7elements for shim thickness of 0.5mm and 0.7mm,respectively).

    Fig.8 Bolt-collar-washer meshed FE model

    Fig.9 Shim material meshed FE model

    Table 2 Elasto-plastic properties of AA7075-T651[27]and Ti-6Al-4VSTA[14]

    Table 3 Elastic properties of Hysol EA9394[28]and solid peelable fiberglass[29]

    The boundary conditions of the FE model in Fig.10has the″Reference Node 2″(RP-2)which is the aluminum plate held fixed in all six degrees of freedom (Ux,Uy,Uz,Rx,RyandRz)because it is clamped and the″Reference Node 1″(RP-1)which is the CFRP plate held fixed in two translational directions(UyandUz)and in all three rotational directions(Rx,RyandRz).A pull distance of 10mm was then applied to RP-1in theUxdirection.

    Fig.10 Boundary conditions on the plates

    Fig.11 Bolt load application

    The clamping force of 10kN[30]produced by the tightening torque was applied through a bolt load function as shown in Fig.11in ABAQUS.The contact relationships were defined for contact pairs interacting with each other using a stringent master-to-slave rule[25].A total of six contact pairs were defined and implemented in the FE model under the interaction section in Abaqus.Contact was modeled between (a)the main plates,(b)between fastener(shanks)and plate holes,(c)between shim,plates,fastener shanks and plate holes,(d)between aluminum plate and washer(bottom surface)and(e)between collar(upper surface)and composite plate.The contacts were defined using the penalty method with hard contact,friction,and finite sliding.″Finite-Sliding″allows for any arbitrary motions of the faying surfaces and the active contact constraints any changes during the analysis.″Small-Sliding″is used if there is a relatively little sliding of any surfaces interacting with each other.A surface-tosurface contact option was used for all contacts,several coefficients of friction were used in the model and their value depended on the components in contact.The frictional coefficient for the interaction between the composite plate and the titanium parts:0.16[30].Frictional coefficients of 0.288[31]and 0.235[32]were used for interactions between aluminum plate and titanium parts,and between composite plate and aluminum plate,respectively.The additional frictional coefficient which is 0.2(assumed),was assigned to all other parts interacting with the shim materials.The surface of the modeled shim was tied onto the composite plate and as shown in Fig.12,special elements(springs/dashpots)were used to connect points to ground.RP-1was used to create a set(set-coupling)and with set-coupling as the control points,a constraint(coupling kinematictype)was created using the surface on which RP-1was situated.

    With this done,the set-coupling was used to generate the needed FEA results for analysis.

    Fig.12 Boundary conditions on the assembled model

    3 Progressive Damage Modeling of CFRP

    Damage in composite structures is internally initiated and accumulated over a period of time before structural failure.The use of failure criteria alone to predict the ultimate failure is not enough because the failure criteria predict the onset of the damage occurring hence there is the need to develop an algorithm to simulate the nonlinear material behavior in the composite structure.The developed algorithm:The progressive damage,is based on the ply-discount method.The failure modes with their criterion;and the material property degradation rules used in the progressive damage model(PDM)are adequately documented in Ref.[14].The PDM is an integration of the stress analysis,failure analysis,and material property degradation.The flowchart for the progressive failure algorithm[33]is shown in Fig.13and the following steps give a detailed explanation of the flowchart:

    Step 1The development of the 3Dsolid FE model of the composite-aluminum bolted structure by inputting the various material properties,boundary conditions,contacts,initial load and final load step.

    Step 2Non-linear stress analysis is performed.

    Step 3Failure analysis is performed by applying the failure criteria.

    Step 4Ply failures are checked:

    (1)If no failure is predicted,the applied load,F(xiàn)mis increased by an increment,ΔFaccording to the equation:Fm=Fm=1+ΔF,and the program goes back to Step 2.

    (2)If there is a mode of failure being predicted,then the program moves on to the next step.

    Step 5The degradation of the material properties of the plies that had failed.

    Step 6Final failure checking:

    (1)If the final failure is reached,the program stops.

    (2)If not,the program goes back to Step 2 and the non-linear stress analysis is carried out again so as to calculate the redistributed stresses.Convergence at a load step is assumed(is proved to be a good compromise between accuracy and time consumption)[34]when no additional failure is detected.

    The PDM written in FORTRAN was implemented into Abaqus/Standard as a user-defined subroutine,USDFLD.The degradation rules were implemented using the field variables(FV)which are dependent on the failure criterion of each failure mode.The USDFLD, within ABAQUS,provides the user a method to write a program that updates the FV at every integration point for each increment in the analysis according to the failure criteria values obtained during the solution.

    At the beginning of each increment,the USDFLD,using the utility subroutine GETVRM,accesses the material point quantities for every integration point in the model and these solutiondependent field variables(SDV)are then used to create an array of FVs to define the material properties of the next iteration[34].Additional,solution-dependent state variables (STATEV),which provide a dependence of each material point on its history,may be updated in this subroutine and the updated values are then passed to another user subroutines that are called at the material point.These state variables are eventually transferred back into the main Abaqus program.According to the different failure modes,there are four different state variables which are defined to display the progression of damage during the post-processing.The failure modes simulated are matrix failure(FV1),fiber failure(FV2),fibermatrix shear failure(FV3)and shear non-linearity(FV4).After the stress analysis,the generated stress values are then used to compute the failure criterion values.If any of the values are greater or equal to 1,the related field variable for the integration point with the highest failure criterion value is set permanently to 1,which indicates failure(it is important to note that the degradation models implemented within ABAQUS degrade at the integration points rather than elements).And these solution-dependent field variables are then used to define the material properties of the next iteration.

    Fig.13 Flowchart of the progressive damage algorithm

    4 Experimental Work

    The test specimens consisted of two plates(composite and aluminum),shim materials(liquid shim-Hysol EA9394and solid shim-peelable fiberglass)and a prestressed titanium bolt with a protruding head.The experiment was performed under quasi-static tensile loading using an electronic universal testing machine (SANS 4105).The test machine was manufactured in accordance with the GB/T 228-2002code of Chinese National Standards.The tests were conducted at a loading velocity of 10mm/s at room temperature.

    4.1 Test specimen preparation

    The specimen in Fig.14was prepared in accordance with the configurations in Refs.[20,24].The liquid shim was prepared in accordance with the manufacturer′s instructions and applied to the composite plate.The prepared specimens were clamped and allowed at least four days to cure at room temperature.Finally,the plates were fastened together by the torquing off of the collars with finger-tightening.

    Fig.14 Composite-aluminum bolted structure

    Fig.15 Test specimen with a liquid shim

    Fig.16 Test specimen with a solid shim

    For the specimen with shim materials,the shim adhered to the mating surface of the composite plate,as shown in Figs.15,16,for a specimen with a liquid shim and a solid shim,respectively.The specimen without any shim is also shown in Fig.17.

    Fig.17 Test specimen without shim

    4.2 Test set-up and procedure

    The test specimens were rigidly clamped into the testing machine as shown in Fig.18.The load application was carried out with a constant traverse speed until structural collapse occurred.

    Fig.18 Test specimen rigidly clamped into the testing machine

    The force against the displacement of the specimens was recorded by a computer.Fig.1 9 shows the experimental arrangement.

    Fig.19 Test set-up for the experiment

    The experiments were stopped after the load had dropped to 15%of its peak load or after the occurrence of an excessive displacement.Each test configuration was repeated with three test specimens and the results that corresponded accurately with the FE results has been presented in this paper.

    5 Results and Discussion

    The numerically simulated results were compared with the experimental data and they were in agreement very well with each other.Subsequently discussed are the load-displacement behavior and the influence of the shim layers on the damage behavior of the composite component.The test results are shown in Figs.20(a—e)and Figs.21(a—e).

    5.1 Load-displacement evaluation

    The numerically simulated load-displacement behavior of the composite component was very similar with the experimentally determined data.Figs.20(a—e)show the load-displacement curves for specimen without shims,0.3,0.5,0.7and 0.9 mm shim thickness,respectively(both liquid and solid shim).

    The maximum experimentally determined load for a specimen without any shims was 16.09 kN at a displacement of 6.1mm but the maximum experimentally determined load for a specimen with a 0.3mm liquid shim thickness was 19.83kN at a displacement of 9.7mm.And also,the maximum experimentally determined load for a specimen with a 0.3mm solid shim thickness was 18.60kN at a displacement of 7.9mm.This kind of trend where all the maximum experimentally determined loads and displacements for specimens with shims being higher than the maximum experimentally determined loads and displacements for specimen without any shims is also obviously seen in Fig.20.The reason for such an observation is the presence of shim.The presence of shims increased the amount of load needed for failure and also increased the strength of the component by increasing the displacement at which failure occurs.

    A further examination of the test results reveals that,with regard to the load-displacement evaluation,the simulated load values were higher than the experimentally determined load values at the same displacement and the differences in these values could be as a result of several factors but predominately,it could be the:(1)Differences in material properties used in the FE modeling and the″actual properties″of the test specimen;(2)Inherent limitations of the failure method used to simulate the damage;and(3)Degradation rules being somewhat different from the″actual failure progression″of the test specimen.

    The progression of the load-displacement curves for the simulated conditions and the experimental conditions were as a result of friction so,the choice of the frictional coefficient to be used for modeling is very important.It has been observed that there is a linearity in the behavior of the composite component initially before reaching the peak loads and subsequently experiencing large displacements before failure.The progressive damage causes such a non-linear curve pattern until the ultimate load was reached.However,the ultimate load identified in the experiments could not be achieved exactly numerically.In comparison,the specimens with liquid shim series were a better fit for gap thickness of 0.3,0.5,0.7mm whereas specimens with solid shim series were better situated for the gap thickness of 0.9mm.

    5.2 Influence of shim layer

    Fig.20 Load-displacement trends for specimens without shim and with different shim thicknesses

    Fig.21 Stiffness-load trends for specimens without shim and with different shim thicknesses

    To be able to estimate the influence of the shim layers on the damage of the composite component,it is imperative to plot the stiffness-load curves.Figs.21 (a—e)show the stiffness-load curves for specimen without shims,with 0.3,0.5,0.7,0.9mm (both liquid and solid shim)shim thickness,respectively.As shown in Figs.21(a—d),generally,the stiffness for both the experiment and that of the numerical simulation decreased with an increasing load up to the failure point of the component before gradually also decreasing with a decreasing load.As for Fig.21(e),the stiffness for both the experiment and that of the numerical simulation decreased with an increasing load up to the failure point of the component before gradually also decreasing with a decreasing load for the liquid shim specimen but for the solid shim specimen,the stiffness gradually increased with an increasing load up to about a displacement of 2.0mm before eventually decreasing with an increasing load up to the component′s failure point and then finally decreased with a decreasing load.Probing further the curves in Fig.20,it was obvious that with regard to the stiffness-load evaluation,the simulated stiffness values were higher than the experimentally determined stiffness values and it is much significantly higher for the about first six stiffness values.The differences in these values could be as a result of the factors discussed in Section 5.1.

    The variations observed in Figs.21(a—e)are predominately due to the dissipation of friction which magnifies the fact that the choice of the coefficient of friction for the FE modeling is important.Afterward,the damage evolution starts and the linear stiffness decreases yield meant that some elements were completely damaged while others still had some stiffness in them.The specimen without any shim material generally exhibited higher stiffness than all liquid shim series(with the exception of 0.9mm shim thickness)and all solid shim series(with the exception of 0.3mm shim thickness and 0.5mm shim thickness).

    It is also clear from Figs.21(a—e)that,the use of liquid shim generally caused a reduction in the joint stiffness for 0.3,0.5,0.7mm shim thickness.It is worth noticing that the solid shim was a better fit for the 0.9mm shim thickness because it considerably gave a better stiffness degradation performance and this may be as a result of the higher tensile modulus of the solid peelable fiberglass shim.Fig.22shows the damaged specimens after the experiments.

    Fig.22 Damaged specimens

    To demonstrate the″somewhat limitations″of the PDM used in simulating the damages,a closer look was taken at the damages for the test specimen without any shim material and the 0.3 mm shim thickness(both liquid and solid shim)as an illustration.The damages for the test specimen without any shim material and the 0.3mm shim thickness(both liquid and solid shim)are shown in Figs.23(a—c),respectively.

    Fig.23 Damaged specimens without shim and with liquid and solid shims

    In the numerical simulation,the failure modes matrix failure,fiber failure as well as the fiber-matrix failure could be displayed but the shear non-linearity could not be″adequately″displayed because the FE-model is an idealization of the reality hence some assumptions were made.Those assumptions definitely had an effect on the actual damage.The view taken for the simulated damaged images is shown in Fig.24.

    Fig.24 View used for taking FV1,F(xiàn)V2,F(xiàn)V3and FV4 damages

    Fig.25 FV1damage for specimens without shim and with liquid and solid shim thicknesses

    Fig.26 FV2damages for specimens without shim and with liquid and solid shim thicknesses

    Figs.25(a—c),F(xiàn)igs.26 (a—c),F(xiàn)igs.27(a—c)and Figs.2 8(a—c)show the simulated four damages(FV1,F(xiàn)V2,F(xiàn)V3,and FV4,respectively)for the specimen with no shim material,with a 0.3mm liquid shim thickness,and with a 0.3mm solid shim thickness.

    In addition to an earlier explanation as to why the shear non-linearity damages in Figs.28(a—c)could not be″adequately″ displayed,it should be noted that it has been assumed in the theory being used in simulating the shear non-linearity that,the non-linearity mainly was caused by the micro-cracking in the matrix and the PDM could not simulate″such microcracking″.

    6 Conclusions

    Fig.27 FV3damages for specimens without shim andwith liquid and solid shim thicknesses

    A three-dimensional finite element model of a single-lap,single-bolt composite-aluminum assembled structure has been developed to investigate the influence of varying shim layers on the progressive damage/failure of a composite component in a bolted composite-aluminum aerospace structural assembly and the numerical results validated against the experimental results were generally in good agreement.From the analysis,the following was discovered:

    (1)The shimming procedure as agreed upon by the aerospace industry for the resolution of assembly gaps in bolted joints for composite materials is same as that for a composite-aluminum structure:liquid shim series prolonged the service life of the composite component for the assembly gaps of 0.3,0.5and 0.7mm;and a solid peelable fiberglass shim most had a better influence on the 0.9mm assembly gap.

    (2)The shim layers considerably influenced the structural strength of the composite component by delaying its failure,thereby increasing its service life.

    Fig.28 FV4damages for specimens without shim and with liquid and solid shim thicknesses

    (3)Increasing the shim layer′s thickness led to a significant corresponding effect on the stiffness but with minimal effect on the ultimate load.

    The aforementioned observations cannot be definitive because other factors,such as thermal expansion coefficients,failure, and fracture mechanisms,and degree of plasticity,might influence the trend observed in this paper for a composite-aluminum structure.

    Acknowledgements

    The authors wish to acknowledge the Innovation Foundation of National Research Center for Commercial Aircraft Manufacturing Engineering Technology in China (No.SAMC13-JS-13-021)and Jiangsu Key Laboratory of Precision and Micro-Manufacturing Technology for the provision of financial support.

    [1] MALLICK P K.Fiber-reinforced composites:Mate-rials,manufacturing,and design[M].3rd Edition.New York:CRC Press,2007:1-12.

    [2] LAURIN F,CARRERE N,MAIRE J F.Strength analysis methods for high stress gradient parts in composite structures ensuring design office requirements[J].Proc IMechE,Part G:J Aerospace Engineering,2011,225(3):291-301.

    [3] WALKER K.EASA widens AD for A380cracks;Boeing confirms 787shims[EB/OL].[2012-02 08]/(2016-10-18).http://atwonline.com/aircraft-ampengines/easa-widens-ad-a380-cracks-boeing-confirms-787-shims.

    [4] FALZON B.The airbus A380wing cracks:an engineer′s perspective [EB/OL].http://the conversation.com/the-airbus-a380-wing-cracks-an-engineersperspective-5318.[2012-2-10](2016-10-18).

    [5] KAPIDZIC Z.Strength analysis and modeling of hybrid composite-aluminum aircraft structures [D].Link ping:Link ping University,2013:3.

    [6] CAMPBELL F C.Manufacturing technology for aerospace structural materials[M].1st Edition.Oxford:Elsevier Science and Technology,2006:498-499.

    [7] TSAI S W,WU E M.A general theory of strength for anisotropic materials[J].J Comp Mater,1971,5(1):58-80.

    [8] REDDY J N,PANDEY A K.A first ply failure analysis of composite laminates[J].Computers Struct,1987,25(3):371-393.

    [9] TURVEY G V.An initial flexural failure analysis of symmetrically laminated cross-ply rectangular plates[J].Int J Solids Struct,1980,16(5):451-463.

    [10]HASHIN Z.Analysis of cracked laminates:A variationalapproach[J].Mech Mater,1985,4(2):121-136.

    [11]CHANG F K,CHANG K Y.A progressive damage model for laminated composites containing stress concentrations[J].J Comp Mater,1987,21(9):834-855.

    [12]CHANG F K,LESSARD L B.Damage tolerance of laminated composites containing an open hole and subjected to compressive loadings:Part I—Analysis[J].J Comp Mater,1991,25(1):2-43.

    [13]REDDY Y N S,REDDY J N.Linear and non-linear failure analysis of composite laminates with transverse shear[J].Compos Sci Tech,1992,44(3):227-255.

    [14]KAPIDZIC Z,NILSSON L,ANSELL H.Finite element modeling of mechanically fastened composite-aluminum joints in aircraft structures[J].Compos Struct,2014,109:198-210.

    [15]SMITH J.Concept development of an automated shim cell for F-35forward fuselage outer mold line control[D].Menomonie:University of Wisconsin-Stout,2011.

    [16]LEE R.Evaluation of shimming options with applications to JSF [EB/OL].[1999-12]/(2016-11-21).http:∥ materialchemistry.com/DreamHC/Download/JSF%20Shimming%20Analysis.pdf.

    [17]CARACCIOLO P,KUHLMANN G. Reliability analysis in bolted composite joints with shimming material[C]∥25th international congress of the aeronautical sciences.Hamburg,Germany,2006:524.

    [18]H HNE C,ZERBST A K,KUHLMANN G,et al.Progressive damage analysis of composite bolted joints with liquid shim layers using constant and continuous degradation models [J].ComposStruct,2010,92(2):189-200.

    [19]DH TE J X,COMER A J,STANLEY W F,et al.Study of the effect of liquid shim on single-lap joint using 3Ddigital image correlation[J].ComposStruct,2013,96:216-225.

    [20]COMER A J,DH TE J X,STANLEY W F,et al.Thermo-mechanical fatigue analysis of liquid shim in mechanically fastened hybrid joints for aerospace applications[J].Compos Struct,2012,94(7):2181-2187.

    [21]DH TE J X,COMER A J,STANLEY W F,et al.Investigation into compressive properties of liquid shim for aerospace bolted joints[J].Compos Struct,2014,109:224-230.

    [22]LIU L.The influence of the substrate′s stiffness on the liquid shim effect in composite to titanium hybrid bolted joints[J].Proc IMechE,Part G:J Aerospace Engineering,2014,228(3):470-479.

    [23]ZHAI Y,LI D,LI X,et al.An experimental study on the effect of joining interface condition on bearing response of single-lap,countersunk composite-aluminum bolted joints[J].Compos Struct,2015,134:190-198.

    [24]ASTM Standard D5961/D 5961M-13.Standard test method for bearing response of polymer matrix composite laminates[S].West Conshohocken,PA,USA:ASTM International,2013.

    [25]ABAQUS.Inc.ABAQUS version 6.13Documentation[M].Velizy-Villacoublay:Dassault Systemes/SIMULIA,2013.

    [26]de LUCA,CAPUTO F,LAMANNA G,et al.Study of analytical models for predicting impact damage to composite structures[C]∥Italian Association for Stress Analysis 42nd National Congress.Salerno,Italy:University of Salerno,2013:11-14.(in Italian)

    [27]ZHAO T W,JIANG Y.Fatigue of 7075-T651aluminum alloy[J].Int J Fatigue,2008,30(5):834-849.

    [28]SUN C T.Adhesively bonded joints,Part 1:bondline thickness effects and hybrid design of adhesively bonded joints[R].DOT/FAA/AR-11/1,P1,USA:FAA report,F(xiàn)ebruary 2014.

    [29]HARTMAN D R,GREENWOOD M E,MILLER D M.High Strength Glass Fibers:1-Pl-19025-A[R].Owens Corning Inc.,Technical Paper Ref.July 1996.Reprinted by AGY LLC as Pub.No.LIT-2006-111,F(xiàn)ebruary 2006.

    [30]STOCCHI C,ROBINSON P,PINHO S T.A detailed finite element investigation of composite bolted joints with countersunk fasteners[J].Compos Struct:Part A,2013,52:143-150.

    [31]CHAKHERLOU T N,OSKOUEI R H,VOGWELL J.Experimental and numerical investigation of the effect of clamping force on the fatigue behaviour of bolted plates[J].Eng Fail Anal,2008,15(5):563-574.

    [32]EKH J,SCHON J,MELIN L G.Secondary bending in multi fastener,composite-to-aluminium single shear lap joints[J].Compos Struct:Part B,2005,36(3):195-208.

    [33]TSERPES K I,PAPANIKO P,KERMANIDIS T H.A three-dimensional progressive damage model for bolted joints in composite laminates subjected to tensile loading[J].Fat Fract Engng Mater Struct,2001,24:663-675.

    [34]LIU L,ZHANG J,CHEN K,et al.Combined and interactive effects of interference fit and preloads on composite joints[J].Chin J Aero,2014,27(3):716-729.

    亚洲美女黄色视频免费看| 性色av乱码一区二区三区2| 51午夜福利影视在线观看| 看十八女毛片水多多多| 日韩视频在线欧美| 黑人巨大精品欧美一区二区蜜桃| 国产精品一二三区在线看| 美女福利国产在线| 日日摸夜夜添夜夜爱| 免费人妻精品一区二区三区视频| 黄色视频不卡| 日本黄色日本黄色录像| 人人妻人人澡人人爽人人夜夜| 亚洲男人天堂网一区| 男女床上黄色一级片免费看| 国产av一区二区精品久久| 成年人免费黄色播放视频| 精品人妻在线不人妻| 18禁国产床啪视频网站| 亚洲av电影在线进入| av有码第一页| 免费看十八禁软件| 亚洲欧美成人综合另类久久久| 青草久久国产| 最黄视频免费看| 国产色视频综合| 午夜福利在线免费观看网站| 亚洲精品久久成人aⅴ小说| 超碰97精品在线观看| 每晚都被弄得嗷嗷叫到高潮| 777久久人妻少妇嫩草av网站| 亚洲欧美激情在线| 欧美日韩黄片免| 韩国精品一区二区三区| 男人舔女人的私密视频| 97在线人人人人妻| 国产日韩欧美亚洲二区| 在线观看www视频免费| 国产精品99久久99久久久不卡| 久久人人97超碰香蕉20202| 免费在线观看影片大全网站 | 午夜福利在线免费观看网站| 一本—道久久a久久精品蜜桃钙片| 丝袜美足系列| 免费少妇av软件| 欧美激情高清一区二区三区| 高清av免费在线| 日本欧美国产在线视频| 少妇被粗大的猛进出69影院| 亚洲人成电影观看| av在线播放精品| 悠悠久久av| www.999成人在线观看| 大香蕉久久成人网| 脱女人内裤的视频| 日本五十路高清| 成在线人永久免费视频| 精品久久蜜臀av无| 国产视频一区二区在线看| 久久久欧美国产精品| 亚洲一区二区三区欧美精品| 精品一区二区三区av网在线观看 | 777米奇影视久久| 无限看片的www在线观看| 乱人伦中国视频| 性高湖久久久久久久久免费观看| 亚洲免费av在线视频| 一区二区三区乱码不卡18| 精品人妻一区二区三区麻豆| 黄频高清免费视频| 国产高清videossex| 欧美精品亚洲一区二区| 精品少妇黑人巨大在线播放| 精品国产乱码久久久久久小说| 久久99热这里只频精品6学生| 999精品在线视频| 日本黄色日本黄色录像| 视频区图区小说| 国产免费一区二区三区四区乱码| 男女午夜视频在线观看| 日本a在线网址| 中文精品一卡2卡3卡4更新| 欧美国产精品va在线观看不卡| 无遮挡黄片免费观看| 欧美xxⅹ黑人| 国产精品人妻久久久影院| 无限看片的www在线观看| 男人添女人高潮全过程视频| 一区二区三区精品91| 久久ye,这里只有精品| 国产精品一二三区在线看| www.999成人在线观看| 18禁黄网站禁片午夜丰满| 免费一级毛片在线播放高清视频 | 免费看av在线观看网站| 欧美日韩综合久久久久久| 亚洲免费av在线视频| 婷婷色综合www| 男女无遮挡免费网站观看| 亚洲黑人精品在线| 天堂8中文在线网| 女人被躁到高潮嗷嗷叫费观| 久久中文字幕一级| 老司机靠b影院| 蜜桃在线观看..| 久久99精品国语久久久| 日日爽夜夜爽网站| 国产真人三级小视频在线观看| 亚洲黑人精品在线| 亚洲色图综合在线观看| 国产又爽黄色视频| 久久九九热精品免费| 久久精品久久精品一区二区三区| 精品亚洲乱码少妇综合久久| 伊人亚洲综合成人网| 欧美大码av| 欧美精品啪啪一区二区三区 | 亚洲国产日韩一区二区| 亚洲欧美成人综合另类久久久| 日韩免费高清中文字幕av| 十八禁高潮呻吟视频| 免费在线观看完整版高清| 亚洲av美国av| 亚洲精品自拍成人| 亚洲精品久久久久久婷婷小说| 丝瓜视频免费看黄片| www.av在线官网国产| 天堂中文最新版在线下载| 两性夫妻黄色片| 亚洲情色 制服丝袜| 手机成人av网站| 成年动漫av网址| 日韩人妻精品一区2区三区| 国产人伦9x9x在线观看| 免费在线观看视频国产中文字幕亚洲 | 亚洲一卡2卡3卡4卡5卡精品中文| 黄色怎么调成土黄色| 免费在线观看影片大全网站 | 日本vs欧美在线观看视频| 欧美大码av| 一二三四在线观看免费中文在| 巨乳人妻的诱惑在线观看| 欧美激情高清一区二区三区| 七月丁香在线播放| 久久 成人 亚洲| 晚上一个人看的免费电影| 黄片小视频在线播放| 欧美黄色片欧美黄色片| 欧美在线一区亚洲| 可以免费在线观看a视频的电影网站| av国产精品久久久久影院| 久久人人爽人人片av| 男女无遮挡免费网站观看| 性色av乱码一区二区三区2| 老司机午夜十八禁免费视频| 男女国产视频网站| 国产片特级美女逼逼视频| 女人高潮潮喷娇喘18禁视频| 美女高潮到喷水免费观看| 亚洲熟女精品中文字幕| 男女国产视频网站| 成年人午夜在线观看视频| 女人被躁到高潮嗷嗷叫费观| 亚洲第一青青草原| 大话2 男鬼变身卡| 亚洲欧美成人综合另类久久久| 色播在线永久视频| 欧美成人精品欧美一级黄| 久久天堂一区二区三区四区| 高清黄色对白视频在线免费看| 欧美黄色淫秽网站| 国产免费视频播放在线视频| 999精品在线视频| 亚洲精品美女久久久久99蜜臀 | 老司机深夜福利视频在线观看 | 精品亚洲乱码少妇综合久久| kizo精华| 亚洲欧美一区二区三区黑人| 少妇人妻久久综合中文| 精品第一国产精品| 天堂俺去俺来也www色官网| 少妇被粗大的猛进出69影院| 永久免费av网站大全| 日韩一卡2卡3卡4卡2021年| 亚洲精品久久午夜乱码| 日韩一区二区三区影片| 国产午夜精品一二区理论片| 天堂中文最新版在线下载| 日韩一卡2卡3卡4卡2021年| 丁香六月欧美| 每晚都被弄得嗷嗷叫到高潮| 人妻一区二区av| 久久性视频一级片| 久久久久久久久免费视频了| 午夜两性在线视频| 久久天堂一区二区三区四区| 亚洲av欧美aⅴ国产| 亚洲精品国产一区二区精华液| 国产1区2区3区精品| 久久久精品区二区三区| 亚洲,欧美精品.| a级毛片在线看网站| 狂野欧美激情性xxxx| 夜夜骑夜夜射夜夜干| 欧美+亚洲+日韩+国产| a级片在线免费高清观看视频| 亚洲精品日韩在线中文字幕| 成人三级做爰电影| 国产在视频线精品| 天天躁狠狠躁夜夜躁狠狠躁| 国产有黄有色有爽视频| 七月丁香在线播放| 欧美乱码精品一区二区三区| 97在线人人人人妻| 精品国产乱码久久久久久男人| 一级毛片 在线播放| 亚洲精品国产av成人精品| 狠狠精品人妻久久久久久综合| 欧美日本中文国产一区发布| 久久99一区二区三区| 久久久久久亚洲精品国产蜜桃av| 中文字幕高清在线视频| 国产亚洲av高清不卡| 国产午夜精品一二区理论片| 亚洲激情五月婷婷啪啪| 欧美中文综合在线视频| 激情视频va一区二区三区| tube8黄色片| 欧美日本中文国产一区发布| 国产一区二区三区av在线| 亚洲欧洲精品一区二区精品久久久| 国产精品久久久久久精品电影小说| av在线老鸭窝| 黄频高清免费视频| 精品欧美一区二区三区在线| 亚洲欧美清纯卡通| 久久久国产欧美日韩av| 成在线人永久免费视频| 老司机午夜十八禁免费视频| 亚洲国产欧美网| 十八禁高潮呻吟视频| 欧美日韩亚洲综合一区二区三区_| 精品久久久久久电影网| 99九九在线精品视频| 国产在线观看jvid| 国产亚洲精品久久久久5区| 老司机午夜十八禁免费视频| 久久青草综合色| 一边摸一边做爽爽视频免费| 欧美变态另类bdsm刘玥| 亚洲激情五月婷婷啪啪| 成人18禁高潮啪啪吃奶动态图| 一边摸一边做爽爽视频免费| kizo精华| 视频在线观看一区二区三区| 久久午夜综合久久蜜桃| 欧美性长视频在线观看| 国产又爽黄色视频| 日韩人妻精品一区2区三区| 国产高清国产精品国产三级| 亚洲熟女毛片儿| 久久天堂一区二区三区四区| 如日韩欧美国产精品一区二区三区| 久久精品久久精品一区二区三区| 好男人电影高清在线观看| 亚洲av日韩精品久久久久久密 | 日日摸夜夜添夜夜爱| 丝瓜视频免费看黄片| 少妇裸体淫交视频免费看高清 | a级毛片黄视频| 国产日韩欧美在线精品| 亚洲九九香蕉| 色综合欧美亚洲国产小说| 97人妻天天添夜夜摸| 1024香蕉在线观看| 久9热在线精品视频| 啦啦啦在线免费观看视频4| 亚洲图色成人| 波野结衣二区三区在线| 国产一区二区在线观看av| 午夜福利影视在线免费观看| av在线老鸭窝| 天天操日日干夜夜撸| 亚洲欧洲日产国产| 亚洲精品一卡2卡三卡4卡5卡 | 日韩制服丝袜自拍偷拍| 90打野战视频偷拍视频| 两人在一起打扑克的视频| av不卡在线播放| 国产xxxxx性猛交| 国产女主播在线喷水免费视频网站| 在线观看国产h片| 悠悠久久av| 亚洲人成77777在线视频| 免费不卡黄色视频| 我要看黄色一级片免费的| 精品国产一区二区三区四区第35| 欧美xxⅹ黑人| 国产精品三级大全| 亚洲精品国产区一区二| 久久鲁丝午夜福利片| 美女主播在线视频| 咕卡用的链子| 精品国产一区二区三区四区第35| 久久精品亚洲av国产电影网| 色播在线永久视频| 国产精品久久久av美女十八| 日韩一本色道免费dvd| 91老司机精品| 激情视频va一区二区三区| 国产精品.久久久| 一本—道久久a久久精品蜜桃钙片| 97人妻天天添夜夜摸| 亚洲精品美女久久久久99蜜臀 | 悠悠久久av| 国产精品.久久久| 99热网站在线观看| 亚洲国产精品成人久久小说| 亚洲av美国av| 日本一区二区免费在线视频| 亚洲欧美清纯卡通| 亚洲国产精品999| 欧美日韩福利视频一区二区| 亚洲国产最新在线播放| 欧美av亚洲av综合av国产av| 精品福利永久在线观看| 精品一区在线观看国产| 晚上一个人看的免费电影| 天堂中文最新版在线下载| 两个人看的免费小视频| 嫩草影视91久久| 久久久久久久久久久久大奶| 黄色a级毛片大全视频| 亚洲精品一区蜜桃| 国产免费福利视频在线观看| 午夜激情久久久久久久| 亚洲欧美激情在线| 性高湖久久久久久久久免费观看| 日韩大片免费观看网站| 黄色视频在线播放观看不卡| 欧美日本中文国产一区发布| 成年女人毛片免费观看观看9 | 一区二区三区激情视频| 人妻 亚洲 视频| 欧美人与性动交α欧美精品济南到| av国产久精品久网站免费入址| 日韩欧美一区视频在线观看| 91国产中文字幕| 天天躁日日躁夜夜躁夜夜| 亚洲第一青青草原| 国产97色在线日韩免费| 黄色视频在线播放观看不卡| 看免费成人av毛片| 午夜激情久久久久久久| 欧美日韩黄片免| 看免费成人av毛片| 成人国产av品久久久| 五月开心婷婷网| 91麻豆av在线| 亚洲av综合色区一区| 精品免费久久久久久久清纯 | 精品少妇一区二区三区视频日本电影| 欧美黑人欧美精品刺激| 中文欧美无线码| 啦啦啦中文免费视频观看日本| 亚洲成人免费av在线播放| 亚洲精品日韩在线中文字幕| 在线观看免费高清a一片| 成人午夜精彩视频在线观看| 两人在一起打扑克的视频| 性色av一级| 国产欧美亚洲国产| 国产精品成人在线| 精品高清国产在线一区| 宅男免费午夜| 18禁裸乳无遮挡动漫免费视频| 999久久久国产精品视频| 女人久久www免费人成看片| 精品第一国产精品| 国产av一区二区精品久久| 久久这里只有精品19| 久热爱精品视频在线9| 看免费成人av毛片| 国产一卡二卡三卡精品| 中国美女看黄片| 欧美乱码精品一区二区三区| av视频免费观看在线观看| 亚洲av男天堂| 妹子高潮喷水视频| 性高湖久久久久久久久免费观看| 久久ye,这里只有精品| 精品亚洲成国产av| 国产精品秋霞免费鲁丝片| 免费看av在线观看网站| 狠狠婷婷综合久久久久久88av| 免费久久久久久久精品成人欧美视频| 天天躁夜夜躁狠狠躁躁| 一区二区三区精品91| 国产成人av激情在线播放| 少妇粗大呻吟视频| 国产有黄有色有爽视频| av网站在线播放免费| 久久精品久久久久久久性| 日本a在线网址| 国产免费视频播放在线视频| 男女无遮挡免费网站观看| 国产成人91sexporn| 蜜桃国产av成人99| 电影成人av| 国产在视频线精品| 成年人免费黄色播放视频| 激情五月婷婷亚洲| 国产成人系列免费观看| bbb黄色大片| 国产精品久久久久久精品古装| 国产成人精品久久二区二区91| 国产1区2区3区精品| 国产伦理片在线播放av一区| 免费久久久久久久精品成人欧美视频| 精品亚洲成a人片在线观看| 亚洲人成电影观看| 中文乱码字字幕精品一区二区三区| 最近中文字幕2019免费版| 日韩免费高清中文字幕av| 国产成人精品久久二区二区91| 久热爱精品视频在线9| 成人手机av| 天天躁夜夜躁狠狠躁躁| 爱豆传媒免费全集在线观看| 成人午夜精彩视频在线观看| 国产精品一区二区免费欧美 | 国产熟女午夜一区二区三区| 老熟女久久久| 日韩中文字幕视频在线看片| av欧美777| 久久国产精品人妻蜜桃| 久久精品人人爽人人爽视色| 老司机亚洲免费影院| 亚洲精品自拍成人| 久久久久久人人人人人| 99热网站在线观看| 精品人妻在线不人妻| 人人澡人人妻人| 成人亚洲精品一区在线观看| 在线 av 中文字幕| 91国产中文字幕| 自线自在国产av| 各种免费的搞黄视频| 午夜免费观看性视频| 久久久久久久久免费视频了| 老司机影院毛片| 久久精品亚洲熟妇少妇任你| 18在线观看网站| 蜜桃国产av成人99| 成人国产av品久久久| 久久99热这里只频精品6学生| 制服人妻中文乱码| 精品人妻在线不人妻| 黄色a级毛片大全视频| 久久精品人人爽人人爽视色| 美女国产高潮福利片在线看| 欧美日韩视频精品一区| 亚洲精品国产av蜜桃| 18禁裸乳无遮挡动漫免费视频| 国产av一区二区精品久久| 精品少妇久久久久久888优播| 五月开心婷婷网| 99国产精品一区二区三区| 男女边摸边吃奶| 飞空精品影院首页| 各种免费的搞黄视频| 国产精品久久久人人做人人爽| 久久99热这里只频精品6学生| 99精国产麻豆久久婷婷| 国产精品99久久99久久久不卡| 后天国语完整版免费观看| 悠悠久久av| 成人国产av品久久久| 天天躁夜夜躁狠狠躁躁| 亚洲综合色网址| kizo精华| 国产免费一区二区三区四区乱码| 一级片免费观看大全| 欧美成人精品欧美一级黄| 18禁裸乳无遮挡动漫免费视频| 热99久久久久精品小说推荐| 亚洲中文日韩欧美视频| 久久久久久久久久久久大奶| 中文字幕制服av| 成年女人毛片免费观看观看9 | 国产激情久久老熟女| 欧美黑人欧美精品刺激| 亚洲欧美清纯卡通| 大香蕉久久成人网| 丁香六月天网| 亚洲国产精品一区三区| 成人亚洲欧美一区二区av| 亚洲欧美中文字幕日韩二区| 别揉我奶头~嗯~啊~动态视频 | 男女下面插进去视频免费观看| 精品国产超薄肉色丝袜足j| 精品一区二区三区四区五区乱码 | 国产麻豆69| 涩涩av久久男人的天堂| 国产成人欧美在线观看 | 九色亚洲精品在线播放| 久久99一区二区三区| 欧美日韩av久久| cao死你这个sao货| 亚洲精品日本国产第一区| a级毛片在线看网站| 亚洲精品国产一区二区精华液| 国产又色又爽无遮挡免| 美女大奶头黄色视频| 精品少妇一区二区三区视频日本电影| 女人久久www免费人成看片| 一级毛片我不卡| 精品国产乱码久久久久久男人| 亚洲精品日本国产第一区| 天天操日日干夜夜撸| 亚洲熟女毛片儿| 欧美精品一区二区免费开放| 欧美日韩黄片免| 久久久精品国产亚洲av高清涩受| tube8黄色片| 99久久精品国产亚洲精品| 丝袜喷水一区| 美女扒开内裤让男人捅视频| 欧美精品高潮呻吟av久久| 日本猛色少妇xxxxx猛交久久| 黄片播放在线免费| 91麻豆精品激情在线观看国产 | 亚洲欧美日韩另类电影网站| 男人操女人黄网站| 午夜精品国产一区二区电影| 中文字幕人妻熟女乱码| 亚洲精品一区蜜桃| av又黄又爽大尺度在线免费看| 免费少妇av软件| 可以免费在线观看a视频的电影网站| 亚洲第一av免费看| av又黄又爽大尺度在线免费看| 日韩精品免费视频一区二区三区| svipshipincom国产片| 18禁国产床啪视频网站| 黄色a级毛片大全视频| 国产亚洲欧美在线一区二区| 国产成人精品久久二区二区免费| 久久国产精品大桥未久av| 婷婷色综合www| 亚洲黑人精品在线| 国产精品国产三级国产专区5o| 一区在线观看完整版| www.自偷自拍.com| 亚洲免费av在线视频| 青春草视频在线免费观看| 免费久久久久久久精品成人欧美视频| 欧美变态另类bdsm刘玥| 亚洲情色 制服丝袜| 美女高潮到喷水免费观看| 精品久久久精品久久久| 大型av网站在线播放| 精品福利观看| 超色免费av| 久久久久久久国产电影| 桃花免费在线播放| 男女无遮挡免费网站观看| 国产视频首页在线观看| 老汉色av国产亚洲站长工具| 色播在线永久视频| 满18在线观看网站| 日韩 亚洲 欧美在线| 午夜老司机福利片| 国产欧美日韩一区二区三 | 99热全是精品| 少妇的丰满在线观看| 看免费成人av毛片| 久久国产精品影院| 两人在一起打扑克的视频| 99国产精品免费福利视频| 曰老女人黄片| 久久久精品国产亚洲av高清涩受| 久久亚洲国产成人精品v| 老司机亚洲免费影院| 视频区图区小说| 欧美激情 高清一区二区三区| 国产精品熟女久久久久浪| 18禁黄网站禁片午夜丰满| 18禁国产床啪视频网站| www日本在线高清视频| 少妇人妻 视频| 黄片小视频在线播放| 亚洲精品日本国产第一区| 精品国产一区二区久久| 人人妻人人爽人人添夜夜欢视频| 一边摸一边抽搐一进一出视频| 精品久久久久久电影网| 99国产精品免费福利视频| 欧美精品亚洲一区二区| 成人国产av品久久久| 精品人妻一区二区三区麻豆| 午夜免费鲁丝| 久久久亚洲精品成人影院| 丝袜喷水一区| 真人做人爱边吃奶动态| 国产黄频视频在线观看| 欧美在线黄色| 亚洲欧美一区二区三区久久| 午夜av观看不卡| 少妇被粗大的猛进出69影院| 老司机深夜福利视频在线观看 | 午夜91福利影院| 日本午夜av视频| 国产不卡av网站在线观看| 我要看黄色一级片免费的|