CN111597716A - Fatigue life prediction method for composite material laminated plate containing layered damage - Google Patents

Fatigue life prediction method for composite material laminated plate containing layered damage Download PDF

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CN111597716A
CN111597716A CN202010422428.0A CN202010422428A CN111597716A CN 111597716 A CN111597716 A CN 111597716A CN 202010422428 A CN202010422428 A CN 202010422428A CN 111597716 A CN111597716 A CN 111597716A
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赵丽滨
骈瑢
王康康
刘丰睿
王林娟
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Abstract

The invention discloses a fatigue life prediction method for a composite material laminated plate containing layered damage, which comprises the following steps: (1) carrying out fatigue tests on the composite laminated plate under different stress ratios, and fitting based on fatigue test data to construct an expression of the material modulus along with the fatigue cycle number; (2) establishing a mathematical model of the composite material laminated plate containing the layered damage based on the boundary condition and the layered damage parameters of the composite material laminated plate under the fatigue load working condition; (3) under any cycle number, updating the modulus parameter of the material according to an expression of the modulus of the material along with the fatigue cycle number; (4) predicting the expansion of the internal delamination damage of the laminated plate and the residual strength of the laminated plate based on a Ritz method, a first-order shear deformation theory and a fracture mechanics method; (5) the number of cycles that the residual strength of the laminate is first below the peak stress of fatigue loading is the fatigue life of the laminate containing delamination damage. The method is used for predicting the fatigue life of the composite material laminated plate containing the layered damage based on a theoretical method, and only fatigue test is carried out on a composite material basic performance test piece to obtain related parameters before application, so that the calculation efficiency can be obviously improved, the test period is shortened, and the test cost is reduced.

Description

Fatigue life prediction method for composite material laminated plate containing layered damage
Technical Field
The invention relates to the field of damage tolerance of composite material laminated plates, in particular to a fatigue life prediction method of a composite material laminated plate containing layered damage.
Background
Delamination damage is a critical damage mode that severely affects the load bearing performance of a composite, and its presence can significantly reduce the structural integrity, with a high propensity for premature buckling and failure of the structure during the life cycle. Meanwhile, the delamination damage is an internal damage mode of the composite material laminated structure and is not easy to detect in practical engineering use, so that the potential risk brought to the composite material structure by the damage mode is greatly improved.
In the existing research work aiming at the laminated structure of the composite material containing the delamination damage, students all aim to analyze the influence of the delamination damage on the bearing performance of the laminated structure of the composite material under the static load working condition. However, the design of the aircraft structure not only needs to consider the static load-bearing capacity, but also needs to consider the safe service life. Under fatigue loading conditions, even if the maximum stress level is significantly lower than the corresponding stress level under static conditions, delamination damage within the composite may propagate and lead to fatigue failure of the structure. This means that the result of covering the fatigue load condition with the layered extension rule under the static load condition inevitably leads to a larger error, which affects the safe use of the composite material structure in the engineering practice. With the continuous development of the composite material structure design technology, it is a necessary trend to fully develop the potential of advanced composite materials, further reduce the structural weight of the composite materials, and improve the design service life of the composite materials.
Therefore, the accurate and efficient prediction method for the fatigue life of the composite material laminated plate containing the layered damage is the key content of the design and analysis work of the composite material laminated structure in engineering practice, and has important theoretical significance and engineering guidance value for the damage tolerance research of the aircraft composite material structure in the engineering practice. Meanwhile, from the perspective of reducing research and development cost in the field of industrial production, a fatigue life prediction model of a composite material laminated structure containing layered damage is urgently required to be developed to partially or completely replace a test so as to realize safety evaluation of the composite material structure under a fatigue load working condition. Under the background, the method provides a fatigue life prediction method for the laminated plate containing the layered damage composite material.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: the method overcomes the defects of the prior art, firstly establishes a fatigue life prediction method of the composite material laminated plate containing the layered damage based on a Ritz method, a first-order shear deformation theory and a fracture mechanics method, realizes the prediction of the fatigue life of the composite material laminated plate containing the layered damage, and only needs to carry out fatigue tests under different stress ratios on the composite material laminated plate before application to provide input parameters, thereby obviously improving the calculation efficiency and reducing the test cost.
The technical scheme adopted by the invention for solving the technical problems is as follows: a fatigue life prediction method for a composite material laminated plate containing layered damage comprises the following steps:
a, carrying out fatigue tests on the composite laminated plate under different stress ratios, and fitting based on fatigue test data to construct an expression of material modulus along with fatigue cycle number;
Figure BDA0002497413970000021
where E (N) is the fatigue modulus at the nth cycle, E (0) is the initial modulus of the composite, q is the load ratio, N is the fatigue life, and c is a fitting constant related to the composite properties. For unidirectional carbon fiber reinforced composites, which typically have a linear relationship between the logarithmic fatigue life lgN and the load ratio q, the fitting can be performed according to basic fatigue test data, i.e., lgN ═ a-q)/B, where A, B is the fitting constant. Equation (1) can thus be updated as:
Figure BDA0002497413970000022
b, establishing a mathematical model of the composite material laminated plate containing the layered damage based on the boundary conditions and the layered damage parameters of the composite material laminated plate under the fatigue load working condition;
step C, inputting fatigue load cycle number, and updating the modulus parameter of the material according to the formula (2);
step D, predicting the expansion of the internal delamination damage of the laminated plate and the residual strength of the internal delamination damage of the laminated plate based on a Ritz method, a first-order shear deformation theory and a fracture mechanics method;
and E, judging whether the residual strength of the laminated plate is lower than the fatigue load stress peak value. If so, the current cycle number is the fatigue life of the laminated plate containing the delamination damage; if not, a cycle number increment is applied and the process returns to step (C).
2. The method for predicting fatigue life of a composite material laminate containing a delamination damage as set forth in claim 1, wherein:
the concrete implementation process for predicting the expansion of the internal delamination damage of the laminated plate and the residual strength of the laminated plate based on the Ritz method, the first-order shear deformation theory and the fracture mechanics method in the step D is as follows:
(D1) based on a Ritz method, assuming that a shape function of a deformation field of the laminated plate is an expression containing undetermined coefficients;
Figure BDA0002497413970000023
wherein k represents the displacement field component at any point in the neutral plane of the laminate and the corner field component of the neutral plane. KmnRespectively representing the undetermined coefficients, f, in each equationk(x, y) represents the boundary condition function, and M and N represent the highest order in the equation.
(D2) The strain energy U and the total potential energy pi of the whole laminated plate can be calculated based on a first-order shear deformation theory;
Figure BDA0002497413970000031
Π＝U+W (5)
W＝-P× (6)
wherein, W is the external work of the laminated plate, P is the external load, and is the corresponding displacement.
(D3) Based on the principle of minimum potential energy, the total potential energy pi is corresponding to each coefficient K to be determinedmnThe variation is solved to obtain a series of nonlinear equations, and each undetermined coefficient K can be determined by solving the equationsmnThen, the deformation field of the laminated plate can be obtained;
Figure BDA0002497413970000032
(D4) solving the strain energy release rate G on the delamination damage boundary in the laminated plate based on a fracture mechanics method;
Figure BDA0002497413970000033
wherein a is the area of the stratified lesion.
(D5) When the strain energy release rate G of a certain point on the boundary of the layered damage is larger than the critical strain energy release rate G of the materialCThe layered lesion begins to expand, adding an area increment △ A at the corresponding expansion point, and realizing iteration of layered expansion;
(D6) with the continuous expansion of the delamination damage, when the reduction range of the support force on the laminated plate exceeds 20%, the laminated plate is considered to be in failure, and the maximum strength value in the loading process is the residual strength of the laminated plate under the current cycle number.
Compared with the prior art, the invention has the advantages that:
1. a universal prediction method is provided aiming at the limitation that the fatigue life of the composite material laminated plate containing delamination damage cannot be predicted by the existing theoretical method research.
2. Before the composite material laminated structure fatigue life evaluation method is applied, only fatigue tests under different stress ratios are needed to be carried out on the composite material laminated structure to provide input parameters, and the test workload in the fatigue life evaluation work of the composite material laminated structure containing layered damage in engineering practice can be reduced, so that the test cost can be obviously reduced, and the engineering application is more convenient.
3. The prediction result of the invention is verified by tests, and the prediction result is consistent with the test result, so the prediction method of the invention has higher precision.
Drawings
FIG. 1 is a flow chart of an implementation of the present invention;
FIG. 2 is a composite laminate model containing a circular delamination damage;
FIG. 3 is a schematic diagram of a composite material basic fatigue performance test specimen;
FIG. 4 is a q-N curve and a stiffness degradation curve of basic performance parameters of a composite material;
FIG. 5 is a q-N curve of fatigue life for a laminate containing delamination damage.
Detailed Description
The invention is described in further detail below with reference to the figures and specific examples.
The invention relates to a fatigue life prediction method for a composite material laminated plate containing layered damage, which is implemented as the following steps as shown in figure 1:
example 1: fatigue life prediction for composite laminates containing circular layered damage
As shown in fig. 2, a rectangular laminate having a geometric size of L (length) × B (width) × H (thickness) has a circular segment having a radius r at an interlayer center portion in the thickness direction. The laminate is subjected to fatigue compressive loading in the x-direction while constraining all degrees of freedom except in the x-direction to a constraint area.
1. Basic performance test pieces for 0 degree tensile, ± 45 degree cross-shear and 90 degree tensile were designed according to ASTM D3039 test standards in conjunction with the T300/QY8911 composite system and are shown in fig. 3. Fatigue tests under different stress ratios are carried out, and a q-N curve and a rigidity degradation curve of a test piece are obtained and are shown in figure 4. The median life of the three test pieces in FIG. 4 are respectively subjected to linear fitting to obtain q-N curve fitting equations of basic performances of 0-degree stretching, +/-45-degree longitudinal and transverse shearing and 90-degree stretching, wherein the q-N curve fitting equations are respectively as follows:
q＝0.956-0.043lgN (1a)
q＝1.099-0.088lgN (1b)
q＝1.097-0.085lgN (1c)
and fitting by combining the rigidity degradation results of the three types of test pieces given in the figure 4, so that the normalized residual rigidity equation of the composite material system is as follows:
Figure BDA0002497413970000041
Figure BDA0002497413970000042
Figure BDA0002497413970000043
2. in order to establish a mathematical model of this problem, the entire composite laminate is divided into three parts, namely, a perforated plate, an upper sub-laminate and a lower sub-laminate, by using the boundary of the laminate and the position of the laminate in the thickness direction as the boundary, and the three parts are respectively numbered as 1, 2 and 3. On the basis, boundary conditions and continuity conditions of mathematical models of all parts of the laminated plate can be given;
boundary conditions:
Figure BDA0002497413970000051
continuity conditions:
Figure BDA0002497413970000052
wherein h is2Or h3Indicating the distance between the neutral plane of the orifice plate and the neutral plane of the upper or lower sub-layer plate,Drepresenting a layered lesion boundary.
3. Based on a Ritz method, assuming that a shape function of deformation fields of three positions of the laminated plate is an expression containing undetermined coefficients;
the mid-plane displacement fields u and v of the three sub-slabs may be expressed as a series as in equation (5):
Figure BDA0002497413970000053
Figure BDA0002497413970000054
middle displacement field w and corner field phi of three sub-layer platesxAnd phiyCan be expressed in the form of a number of steps as in formula (6) and formula (6), when-L0/2<x<+L0At the time of/2, the ratio of the total amount of the carbon atoms,
Figure BDA0002497413970000055
Figure BDA0002497413970000061
Figure BDA0002497413970000062
when x is less than or equal to-L0/2 or x is not less than + L0At the time of/2, the ratio of the total amount of the carbon atoms,
Figure BDA0002497413970000063
in the formula of Umn，Vmn，Wmn，φXmnAnd phiYmnRespectively represent the undetermined coefficients in each equation,D(x, y) represents a hierarchical lesion boundary function for a circular hierarchical lesionD(x,y)＝x2+y2-r2。
4. Given the number n of cycles, updating the modulus parameter of the composite material at the current number of cycles by combining the formula (2);
5. strain energy U and total potential energy pi of the whole laminated plate can be obtained by combining a first-order shear deformation theory;
Figure BDA0002497413970000064
Π＝U+W (9)
6. based on the principle of minimum potential energy, the total potential energy pi is corresponding to each coefficient K to be determinedmn(Umn，Vmn，Wmn，φXmnAnd phiYmn) Solving the variation to obtain a series of nonlinear equation sets, and solving the equation sets to determine the deformation field of the laminated plate;
Figure BDA0002497413970000065
7. solving the strain energy release rate G on the delamination damage boundary in the laminated plate according to a fracture mechanics method;
Figure BDA0002497413970000066
8. if the strain energy release rate G of a certain point on the boundary of the layered damage is larger than the critical strain energy release rate G of the materialCIf so, the layered damage starts to expand, and a radius increment △ r is added at a corresponding expansion point to represent the change of the layered area, so that the iteration of layered expansion is realized;
9. with the continuous expansion of the delamination damage, when the reduction amplitude of the support force on the laminated plate exceeds 20%, the laminated plate is considered to have final failure, and the maximum strength in the loading process is the residual strength of the laminated plate under the current cycle number n;
10. if the residual strength of the lower plywood in the current cycle number n is larger than the stress peak value of the fatigue load, applying a cycle number increment delta n and returning to the step 4; otherwise, the current cycle number n is the fatigue life of the laminate. The S-N curve of the delamination damage-containing laminate obtained in this step is shown in FIG. 5, and the results of the preliminary experiments substantially match.
The invention has not been described in detail and is part of the common general knowledge of a person skilled in the art.
Although illustrative embodiments of the present invention have been described above to facilitate the understanding of the present invention by those skilled in the art, it should be understood that the present invention is not limited to the scope of the embodiments, and that various changes may be apparent to those skilled in the art as long as they are within the spirit and scope of the present invention as defined and defined by the appended claims, and all inventions utilizing the inventive concept are protected.

Claims (2)

1. A fatigue life prediction method for a composite material laminated plate containing layered damage is characterized by comprising the following steps:
a, carrying out fatigue tests on the composite laminated plate under different stress ratios, and fitting based on fatigue test data to construct an expression of material modulus along with fatigue cycle number;
Figure FDA0002497413960000011
where E (N) is the fatigue modulus at the nth cycle, E (0) is the initial modulus of the composite, q is the load ratio, N is the fatigue life, and c is a fitting constant related to the composite properties. For unidirectional carbon fiber reinforced composites, which typically have a linear relationship between the logarithmic fatigue life lgN and the load ratio q, the fitting can be performed according to basic fatigue test data, i.e., lgN ═ a-q)/B, where A, B is the fitting constant. Equation (1) can thus be updated as:
Figure FDA0002497413960000012
b, establishing a mathematical model of the composite material laminated plate containing the layered damage based on the boundary conditions and the layered damage parameters of the composite material laminated plate under the fatigue load working condition;
step C, inputting fatigue load cycle number, and updating the modulus parameter of the material according to the formula (2);
d, predicting the expansion of the internal delamination damage of the laminated plate and the residual strength of the internal delamination damage of the laminated plate based on a Ritz method, a first-order shear deformation theory and a fracture mechanics method;
and E, judging whether the residual strength of the laminated plate is lower than the fatigue load stress peak value. If so, the current cycle number is the fatigue life of the laminated plate containing the delamination damage; if not, a cycle number increment is applied and the process returns to step (C).
2. The method for predicting fatigue life of a composite material laminate containing a delamination damage as set forth in claim 1, wherein:
the concrete implementation process for predicting the expansion of the internal delamination damage of the laminated plate and the residual strength of the laminated plate based on the Ritz method, the first-order shear deformation theory and the fracture mechanics method in the step D is as follows:
(D1) based on a Ritz method, assuming that a shape function of a deformation field of the laminated plate is an expression containing undetermined coefficients;
Figure FDA0002497413960000013
wherein k represents the displacement field component at any point in the neutral plane of the laminate and the corner field component of the neutral plane. KmnRespectively representing undetermined coefficients, f, in each equationk(x, y) represents the boundary condition function, and M and N represent the highest order in the equation.
(D2) The strain energy U and the total potential energy pi of the whole laminated plate can be calculated based on a first-order shear deformation theory;
Figure FDA0002497413960000021
Π＝U+W (5)
W＝-P× (6)
wherein, W is the external work of the laminated plate, P is the external load, and is the corresponding displacement.
(D3) Based on the principle of minimum potential energy, the total potential energy pi is corresponding to each coefficient K to be determinedmnCalculating variation to obtain a series of nonlinear equations, and solving the equations to determine undetermined coefficients KmnThen, the deformation field of the laminated plate can be obtained;
Figure FDA0002497413960000022
(D4) solving the strain energy release rate G on the delamination damage boundary in the laminated plate based on a fracture mechanics method;
Figure FDA0002497413960000023
wherein a is the area of the stratified lesion.
(D5) When the strain energy release rate G of a certain point on the boundary of the layered damage is larger than the critical strain energy release rate G of the materialCThe layered lesion begins to expand, adding an area increment △ A at the corresponding expansion point, and realizing iteration of layered expansion;
(D6) with the continuous expansion of the delamination damage, when the support force on the laminated plate is reduced by more than 20%, the laminated plate is considered to be in failure, and the maximum strength value in the loading process is the residual strength of the laminated plate under the current cycle number.
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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112580170A (en) * 2020-12-29 2021-03-30 南京航空航天大学 Bayesian online diagnosis and prediction method for fatigue delamination damage of composite material
CN112733324A (en) * 2020-12-17 2021-04-30 重庆大学 Composite material laminate fatigue layering expansion behavior prediction method considering stress ratio and fiber bridging influence

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20150053017A1 (en) * 2013-08-23 2015-02-26 Michael M. Khonsari Fatigue assessment
CN105447316A (en) * 2015-12-01 2016-03-30 北京航空航天大学 Gradual damage method for predicting residual life of composite blade with initial defects
CN105488310A (en) * 2016-01-22 2016-04-13 重庆大学 Prediction method for normalized fatigue delamination propagation rate of CFRP (carbon fiber-reinforced plastic) multi-directional laminated plate
CN109858152A (en) * 2019-01-29 2019-06-07 广州大学 A method of remanent fatigue life of the prediction containing initial delamination damage composite material
CN110705163A (en) * 2019-09-30 2020-01-17 北京航空航天大学 Fatigue system reliability analysis method for composite material laminated structure

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20150053017A1 (en) * 2013-08-23 2015-02-26 Michael M. Khonsari Fatigue assessment
CN105447316A (en) * 2015-12-01 2016-03-30 北京航空航天大学 Gradual damage method for predicting residual life of composite blade with initial defects
CN105488310A (en) * 2016-01-22 2016-04-13 重庆大学 Prediction method for normalized fatigue delamination propagation rate of CFRP (carbon fiber-reinforced plastic) multi-directional laminated plate
CN109858152A (en) * 2019-01-29 2019-06-07 广州大学 A method of remanent fatigue life of the prediction containing initial delamination damage composite material
CN110705163A (en) * 2019-09-30 2020-01-17 北京航空航天大学 Fatigue system reliability analysis method for composite material laminated structure

Non-Patent Citations (4)

* Cited by examiner, † Cited by third party
Title
KANGKANG WANG 等: "An analytical model for evaluating the buckling, delamination propagation, and failure behaviors of delaminated composites under uniaxial compression", 《COMPOSITE STRUCTURES》 *
KANGKANG WANG 等: "An extended analytical model for predicting the compressive failure behaviors of composite laminate with an arbitrary elliptical delamination", 《INTERNATIONAL JOURNAL OF SOLIDS AND STRUCTURES》 *
任鹏，夏峰: "复合材料层合板冲击后疲劳寿命试验研究与数值模拟", 《工程与试验》 *
李峰等: "含圆形分层损伤复合材料层合板在弯曲载荷作用下的屈曲行为研究", 《宇航材料工艺》 *

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112733324A (en) * 2020-12-17 2021-04-30 重庆大学 Composite material laminate fatigue layering expansion behavior prediction method considering stress ratio and fiber bridging influence
CN112580170A (en) * 2020-12-29 2021-03-30 南京航空航天大学 Bayesian online diagnosis and prediction method for fatigue delamination damage of composite material
CN112580170B (en) * 2020-12-29 2024-05-24 南京航空航天大学 Bayesian online diagnosis and prediction method for fatigue layered damage of composite material

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