# Micro-Macro Simulation Technique Combined with Multilevel Damage Assessment Methodology for RC Building Structures

Authors: Jianguang Yue
Journal: Advances in Materials Science and Engineering
 (2015)

---

## Abstract

In order to assess the inherent damage mechanism of reinforced concrete (RC) structures, a micro-macro simulation technique combined with multilevel damage assessment methodology is presented. An element-coupling model is developed by combining mixed dimensional finite elements with the aid of multipoint constraint equations, which could be achieved from the energy conservation principle. Thus, the micro-scale damage details could be obtained in a macro-scale setting of the global structure. Furthermore, using different damage indicators, a generalized damage model is combined with the multilevel damage performance to assess the damage evolution. Finally, an in situ lateral loading test of a real RC frame structure was analyzed to verify this proposed damage assessment methodology. The finite element method utilizing the proposed damage model products results in good agreement with those of the tests. It shows that the proposed methodology is a very helpful tool to assess and reveal the inherent damage mechanism of RC structures.


---

## Body

## 1. Introduction

Many earthquake disasters indicate that seismic damage of buildings normally begins at material level, develops or cumulates at section level, member level, and storey level, and finally ends at the failure state of structure level. However, it is difficult to monitor or measure the damage behavior of structures subjected to real ground motions as well as during shaking table testing. Since the size and weight of the specimen is restricted by the capacity of the shaking table, the pseudo-dynamic testing to existing structures in site or full-scale structures in the laboratory to acquire realistic data about performance, evolution of damage, and strength deterioration has been widely and successfully employed. A full-scale pseudo-dynamic test of a three-storey, two-by-two bays, irregular reinforced concrete (RC) frame was performed at the European Laboratory for Structural Assessment of the Joint Research Centre of the European Commission [1]. It aimed to study the coupled translational-torsional dynamic response of an irregular multistorey building under bidirectional earthquake loading. Some in situ tests on five existing structures show that ambient vibration measurements constitute a very efficient method to obtain information on the seismic behavior of most existing buildings [2]. On the other hand, an advanced numerical simulation technique is an efficient, inexpensive, widely used way to evaluate the damage behavior of structures. The most usually used method is the finite element method (FEM). The one-dimensional (1D), at macro-scale, FEM based on the fiber-beam-element model [3] is already widely accepted as a suitable method for proper simulation of RC structures. However, it has some difficulties to acquire the damage details at micro-scale. The three-dimensional (3D), at micro-scale, FEM can predict the micro-scale damage details but requires more computational efforts, especially for a global or complex structure. Therefore, the mixed-elements numerical model [4–9] or transition-element model [10] in FEM is presented to capture the micro-scale damage at reasonable calculation cost.The damage data like stiffness, strength, deformation, and energy dissipation from material level to structure level could be represented in damage assessment models. Damage models are defined on the basis of four types of measurements, that is, measurements based on remaining life or residual strength, micro-structural measurements, measurements of physical parameters, and measurements of changes in mechanical behavior. Many proposed damage models are defined by mechanical behavior indicators, like deformation, bearing capacity or dynamic characteristics, dissipation hysteretic energy indicators, and the combination of deformation and energy indicators [11, 12]. For example, the plastic dissipation energy of members [13] and the deformation characterized by drift ratio or plastic rotation were used to define damage models [14, 15]. The widely known Park-Ang damage model [16] is presented by combining both maximum plastic displacement and plastic dissipated energy. However, it cannot evaluate damage at material level and section level. An energy and low-cycle fatigue-based hysteresis damage model has also been developed for deteriorating systems [17]. Taking into account axial force-bending moment, a section-level-based damage model was proposed to assess the damage behavior of steel structures [18]. By integrating multilayered finite elements at a section, a global damage model was constructed from local damage of concrete and reinforcement [19], which depends on the probable collapse mechanism of the structure. In a local/global damage model for RC structures [20], the damage internal variable of the constitutive model was taken as the local damage indicator. This model was further modified by introducing a two-parameter concrete damage constitutive model and taking into account the concrete plastic strain and reinforcement buckling effect [21]. It could be seen that most of the abovementioned damage models are only available for one or a few structural levels which cannot completely assess the multilevel damage evolution.Another important hand of performance-based design (PBD) relies on the performance-based limit. A seismic performance level is normally determined on the basis of structural member damage states [22, 23]. Provisions and codes for performance assessment of RC structures, such as FEMA356 [24], Eurocode 8 [25], and ASCE/SEI 41 [26], include deformation limits to estimate the performance of members or structures. Basically all deformation-based provisions employ similar damage state definitions for reinforced concrete members. Section chord rotation and material strain limits have also been used to evaluate the performance of structural members. Furthermore, strain limits are defined for concrete and steel at damage limit states as a vital component of PBD. Thus it can be found that there are no performance criteria that could cover all structural levels, that is, material level, section level, member level, storey level, and structure level.In this work, an element-coupling model, which consisted of mixed dimensional elements coupled by multipoint constraint equation, is presented to capture the micro-scale damage details and global structure behavior together. A generalized damage model is combined with multilevel performance to assess the damage evolution from material level to structure level. The proposed methodology is verified by the analysis of an in situ lateral loading test of a real RC frame structure.


## 2. Micro-Macro-Coupling FEM

All structures in the real world are three-dimensional, but in ordinary strength of materials, approximations are made to facilitate simple analysis of a problem. In FEM, reduced element types are defined in terms of a reduced geometric representation, with properties that account for the dimensions not included. These element types produce more computationally efficient models, thus reducing analysis costs.Many structural applications of the finite element method contain long slender regions, thin zones, and complex chunky portions. Long slender regions can be represented appropriately using beam elements, thin zones can usually be modeled using shell elements, and chunky portions are best represented as three-dimensional elements. However, practical models usually contain a mixture of more than one of the above region categories. In order that each region is represented by an appropriate element type, some sort of coupling scheme is required to form a link between the meshes of different types.Multipoint constraint equations define a relationship between sets of displacements within a finite element model. With the aid of ABAQUS software [27], mixed dimensional elements could be coupled together by the multipoint constraint equations. The normal form is given in the following:(1)u=∑i=1nXiu′,where u is the nodal freedom of the lower dimension element, u′ is the higher dimension element, n is the number of higher dimension elements on the interface, and Xi is the constraint coefficients of node i.This solution was arrived at by equating the work of the interface stresses in terms of the lower dimension interface rotations and transverse displacements to the work of the boundary stresses on the higher dimension side of the interface, namely, the energy conservation principle here. Coupling is achieved by introducing the assumed variation of the stresses, given by the appropriate beam, plate, or shell theory, over the cross-section of the interface. The coupling can be achieved for arbitrary transitions so long as the stress distribution due to any given load can be determined at each interface.


### 2.1.
1D and 3D Elements Coupling

According to the energy conservation principle, the work done of the nodal stress of 3D solid elements on the interface should be equal to the work done of the nodal force of the 1D beam element which is coupled on the interface (see Figure1). Thus, the relationship of nodal forces of beam element and nodal stresses of solid elements can be obtained as(2)
F
i
u
i
,
b
e
a
m
=
∫
A
σ
3
i
u
i
,
s
o
l
i
d
′
d
A
,
i
=
1,2
,
3
∫
A
σ
33
u
3
,
s
o
l
i
d
′
d
A
,
i
=
4,5
∫
A
σ
31
u
1
,
s
o
l
i
d
′
+
σ
32
u
2
,
s
o
l
i
d
′
d
A
,
i
=
6
,where A is the interface area; Fi is the nodal force of beam element along axis i; σ3i is the nodal stress component of solid elements on interface along axis i; ui is the nodal displacement component of beam element connected with interface along axis i; ui′ is the nodal displacement component of solid elements on interface along axis i.Figure 1
Coupling of 1D element with 3D elements.For thin-walled circular section, the stress on interface can be obtained from the theory of materials mechanics,(3)
σ
3
i
=
F
i
A
+
6
F
6
b
2
3
h
-
b
,
i
=
1,2
F
i
A
+
F
4
y
I
1
+
F
5
x
I
2
,
i
=
3
,where x or y is the nodal coordinates of the solid elements on interface; axis 1 is the x direction and axis 2 is the y direction; the origin point of this coordinate system is located at the beam node on interface; I1 and I2 are the principal moment of inertia of the interface with respect to axis 1 and axis 2, respectively; A0 is the area which is bounded by the middle line of the section wall; t is the thickness of cross-section wall; R0 is the average radius of cross section.By substituting (3) into (2), the multipoint constraint equations can be achieved as(4)
u
i
,
b
e
a
m
=
1
A
∑
j
=
1
n
∫
A
j
N
s
o
l
i
d
u
i
,
s
o
l
i
d
′
d
A
=
X
i
u
i
′
,
i
=
1,2
,
3
1
I
i
-
3
∑
j
=
1
n
∫
A
j
y
N
s
o
l
i
d
u
3
,
s
o
l
i
d
′
d
A
=
X
i
u
i
,
s
o
l
i
d
′
,
i
=
4
1
I
i
-
3
∑
j
=
1
n
∫
A
j
x
N
s
o
l
i
d
u
3
,
s
o
l
i
d
′
d
A
=
X
i
u
i
,
s
o
l
i
d
′
,
i
=
5
6
b
2
3
h
-
b
∑
j
=
1
n
∫
A
j
N
s
o
l
i
d
u
1
′
+
u
2
′
d
A
=
X
1
,
i
u
1
,
s
o
l
i
d
′
+
X
2
,
i
u
2
,
s
o
l
i
d
′
,
i
=
6
,where Ai is the element area on the interface; [N] is shape function matrix of solid elements on the interface; [X] is coefficient matrix of multipoint constraint equations; {u′}i is nodal freedom matrix of elements i on the interface; [u′] is the nodal freedom matrix on the interface.


### 2.2.
1D and 2D Elements Coupling

Figure2 shows the coupling interface of one-dimensional (1D) beam elements and two-dimensional (2D) shell elements. In this figure, ui,beam and ui,shell are the nodal displacement components of beam element and shell elements, respectively, on the interface along the axis i. According to the energy conservation principle, the work done of the nodal stress of shell elements should be equal to the work done of the nodal force of beam element on interface. Then, the relationship of nodal forces of beam element and nodal stresses of shell elements can be achieved as(5)
F
i
u
i
,
b
e
a
m
=
∫
A
σ
3
i
,
s
h
e
l
l
u
i
,
s
h
e
l
l
d
A
,
i
=
1,2
,
3
∫
A
σ
33
,
s
h
e
l
l
u
3
,
s
h
e
l
l
d
A
+
∫
S
M
s
x
u
4
,
s
h
e
l
l
d
s
+
∫
S
M
s
y
u
5
,
s
h
e
l
l
d
s
,
i
=
4,5
∫
A
σ
31
,
s
h
e
l
l
u
1
,
s
h
e
l
l
+
σ
32
,
s
h
e
l
l
u
2
,
s
h
e
l
l
d
A
,
i
=
6
,where A is the interface area; Fi is the nodal force of beam element along the axis i; σ3i,shell is the nodal stress component of shell element on interface along axis i; ui,shell is the nodal displacement component of shell elements on interface along axis i; Msx and Msy are additional bending moment on the interface along axes x and y, respectively, induced by the nonuniform stress of shell elements.Figure 2
Coupling of 1D element with 2D elements.In (5), the solution method of the multipoint constraint equations about u1,beam, u2,beam, and u6,beam is the same as the method for (4). Thus, the multipoint constraint equations corresponding to u3,beam, u4,beam, and u5,beam are summarized as follows. By substituting the simplified form of stress σ33,shell=F3/A into (5), the multipoint constraint equation for u3,beam can be given as(6)u3,beam=1A∑in∫AiNshelldAu3,shell=X3u3,shell.According to the energy conservation principle, the work done of the nodal stress of shell elements should be equal to the work done of the nodal forceF4 of the beam element. Taking into account the work done of the additional bending momentMs, the relationship of nodal forces of beam element and nodal stresses of shell elements can be expressed as(7)F4u4,beam=∫Aσ33u3,shelldA+∫SMsxu4,shellds+∫SMsyu5,shellds,σ33=F4I12I122-I1I2x+I2I1I2-I122y,Msx=∫-t/2t/2σ33ydydxds=2∫0t/2F4I2I1I2-I122yydxds=t312F4I2I1I2-I122dxds,Msy=∫-t/2t/2σ33xdxdyds=2∫0t/2F4I12I122-I1I2xxdyds=t312F4I12I122-I1I2dyds,where Ms is the bending moment in unit length induced by the normal stresses along the thickness t (see Figure 3) of shell elements; Msx and Msy are the component ofMs on the interface along axes x and y, respectively; I12 is the product of inertia for axis 1 and axis 2.Figure 3
Bending moment of shell elements.From (7), the multipoint constraint equation for u4,beam can be expressed as(8)u4,beam=∑i=1n∫AiI12I122-I1I2x+I2I1I2-I122yNshellu3,shelldA+∑i=1n∫lit312I2I1I2-I122dxdsNshellu4,shelldl+∑i=1n∫lit312I12I122-I1I2dxdsNshellu5,shelldl.By the same way, the multipoint constraint equation foru5,beam can be expressed as(9)u5,beam=∑i=1n∫AiI1I122-I1I2x+I12I1I2-I122yNshellu3,shelldA+∑i=1n∫lit312I12I1I2-I122dxdsNshellu4,shelldl+∑i=1n∫lit312I1I122-I1I2dxdsNshellu5,shelldl.


### 2.3.
2D and 3D Elements Coupling

Figure4 shows the coupling interface of 2D shell elements and 3D solid elements. In this figure, ui′ and ui,shell are the nodal displacement components of solid elements and shell elements, respectively, on the interface along axis i. According to the energy conservation principle, the work done of the force of shell elements should be equal to the work done of the nodal stresses of solid elements. Thus, the relationship of force of shell elements and nodal stresses of solid elements is given by(10)
∫
L
F
i
′
u
i
,
s
h
e
l
l
d
x
=
∫
A
σ
3
i
u
i
′
d
A
,
i
=
1,2
,
3
∫
A
σ
33
u
3
′
d
A
,
i
=
4,5
∫
A
σ
31
u
1
′
d
A
,
i
=
6
,where Fi′ is force component of shell elements in unit length along axis i; σ3i is nodal stress component of solid elements along axis i; A is coupling interface area and L is the coupling interface length (see Figure 4); ui,shell and ui′ are the displacement component of shell element and solid element on interface along axis i, respectively.Figure 4
Coupling of 2D elements with 3D elements.The force componentFi′ can be formulated by the nodal stress on interface as(11)
F
i
′
=
∫
-
t
/
2
t
/
2
σ
3
i
d
y
,
i
=
1,2
,
3
∫
-
t
/
2
t
/
2
σ
33
y
d
y
,
i
=
4
∫
-
L
/
2
L
/
2
σ
33
x
d
x
,
i
=
5
∫
-
t
/
2
t
/
2
σ
31
y
d
y
,
i
=
6
,where t is the thickness of shell element.On the coupling interface, the nodal stresses of shell elements can be expressed as one-degree linear term and parabolic-quadratic term, respectively, as follows:(12)σ31=a+by,(13)σ32=f1-4y2t2,(14)σ33=c+dy+ex,where a, b, c, d, e, and f are parameters.The nodal stressσ3i of shell element can be obtained by substituting (15), (13), and (14) into (11) as(15)σ31=F1t+12F6t3y,(16)σ32=3F22t1-4y2t2,(17)σ33=F3t+12F4t3y+12F5L3x.By substituting (15), (16), and (17) with F1~6=[Nshell]{F1~6}=F1~6TNshellT, u1~6=[Nshell]{u1~6}, and u1~3′=[Nsolid]{u1~3′} into (10), the multipoint constraint equations for shell elements and solid elements can be written as(18)
u
i
=
∫
A
N
s
h
e
l
l
T
N
s
o
l
i
d
d
A
t
∫
L
N
s
h
e
l
l
T
N
s
h
e
l
l
d
x
u
1
′
=
X
1
u
1
′
,
i
=
1
3
∫
A
1
-
4
y
2
/
t
2
N
s
h
e
l
l
T
N
s
o
l
i
d
d
A
2
t
∫
L
N
s
h
e
l
l
T
N
s
h
e
l
l
d
x
u
2
′
=
X
2
u
2
′
,
i
=
2
∫
A
N
s
h
e
l
l
T
N
s
o
l
i
d
d
A
t
∫
L
N
s
h
e
l
l
T
N
s
h
e
l
l
d
x
u
2
′
=
X
3
u
2
′
,
i
=
3
12
∫
A
y
N
s
h
e
l
l
T
N
s
o
l
i
d
d
A
t
3
∫
L
N
s
h
e
l
l
T
N
s
h
e
l
l
d
x
u
3
′
=
X
4
u
3
′
,
i
=
4
12
∫
A
x
N
s
h
e
l
l
T
N
s
o
l
i
d
d
A
L
3
∫
t
N
s
h
e
l
l
T
N
s
h
e
l
l
d
y
u
3
′
=
X
5
u
3
′
,
i
=
5
12
∫
A
y
N
s
h
e
l
l
T
N
s
o
l
i
d
d
A
t
3
∫
L
N
s
h
e
l
l
T
N
s
h
e
l
l
d
x
u
1
′
=
X
6
u
1
′
,
i
=
6
,where {u1~6} and {u1~3′} are nodal displacement matrixes for shell elements and solid elements, respectively; [Nshell] and [Nsolid] are shape functions for shell elements and solid elements, respectively; {F1~6} is nodal force matrix for shell elements; [u1~3′] is nodal displacement matrix for solid elements on the coupling interface.


## 2.1.
1D and 3D Elements Coupling

According to the energy conservation principle, the work done of the nodal stress of 3D solid elements on the interface should be equal to the work done of the nodal force of the 1D beam element which is coupled on the interface (see Figure1). Thus, the relationship of nodal forces of beam element and nodal stresses of solid elements can be obtained as(2)
F
i
u
i
,
b
e
a
m
=
∫
A
σ
3
i
u
i
,
s
o
l
i
d
′
d
A
,
i
=
1,2
,
3
∫
A
σ
33
u
3
,
s
o
l
i
d
′
d
A
,
i
=
4,5
∫
A
σ
31
u
1
,
s
o
l
i
d
′
+
σ
32
u
2
,
s
o
l
i
d
′
d
A
,
i
=
6
,where A is the interface area; Fi is the nodal force of beam element along axis i; σ3i is the nodal stress component of solid elements on interface along axis i; ui is the nodal displacement component of beam element connected with interface along axis i; ui′ is the nodal displacement component of solid elements on interface along axis i.Figure 1
Coupling of 1D element with 3D elements.For thin-walled circular section, the stress on interface can be obtained from the theory of materials mechanics,(3)
σ
3
i
=
F
i
A
+
6
F
6
b
2
3
h
-
b
,
i
=
1,2
F
i
A
+
F
4
y
I
1
+
F
5
x
I
2
,
i
=
3
,where x or y is the nodal coordinates of the solid elements on interface; axis 1 is the x direction and axis 2 is the y direction; the origin point of this coordinate system is located at the beam node on interface; I1 and I2 are the principal moment of inertia of the interface with respect to axis 1 and axis 2, respectively; A0 is the area which is bounded by the middle line of the section wall; t is the thickness of cross-section wall; R0 is the average radius of cross section.By substituting (3) into (2), the multipoint constraint equations can be achieved as(4)
u
i
,
b
e
a
m
=
1
A
∑
j
=
1
n
∫
A
j
N
s
o
l
i
d
u
i
,
s
o
l
i
d
′
d
A
=
X
i
u
i
′
,
i
=
1,2
,
3
1
I
i
-
3
∑
j
=
1
n
∫
A
j
y
N
s
o
l
i
d
u
3
,
s
o
l
i
d
′
d
A
=
X
i
u
i
,
s
o
l
i
d
′
,
i
=
4
1
I
i
-
3
∑
j
=
1
n
∫
A
j
x
N
s
o
l
i
d
u
3
,
s
o
l
i
d
′
d
A
=
X
i
u
i
,
s
o
l
i
d
′
,
i
=
5
6
b
2
3
h
-
b
∑
j
=
1
n
∫
A
j
N
s
o
l
i
d
u
1
′
+
u
2
′
d
A
=
X
1
,
i
u
1
,
s
o
l
i
d
′
+
X
2
,
i
u
2
,
s
o
l
i
d
′
,
i
=
6
,where Ai is the element area on the interface; [N] is shape function matrix of solid elements on the interface; [X] is coefficient matrix of multipoint constraint equations; {u′}i is nodal freedom matrix of elements i on the interface; [u′] is the nodal freedom matrix on the interface.


## 2.2.
1D and 2D Elements Coupling

Figure2 shows the coupling interface of one-dimensional (1D) beam elements and two-dimensional (2D) shell elements. In this figure, ui,beam and ui,shell are the nodal displacement components of beam element and shell elements, respectively, on the interface along the axis i. According to the energy conservation principle, the work done of the nodal stress of shell elements should be equal to the work done of the nodal force of beam element on interface. Then, the relationship of nodal forces of beam element and nodal stresses of shell elements can be achieved as(5)
F
i
u
i
,
b
e
a
m
=
∫
A
σ
3
i
,
s
h
e
l
l
u
i
,
s
h
e
l
l
d
A
,
i
=
1,2
,
3
∫
A
σ
33
,
s
h
e
l
l
u
3
,
s
h
e
l
l
d
A
+
∫
S
M
s
x
u
4
,
s
h
e
l
l
d
s
+
∫
S
M
s
y
u
5
,
s
h
e
l
l
d
s
,
i
=
4,5
∫
A
σ
31
,
s
h
e
l
l
u
1
,
s
h
e
l
l
+
σ
32
,
s
h
e
l
l
u
2
,
s
h
e
l
l
d
A
,
i
=
6
,where A is the interface area; Fi is the nodal force of beam element along the axis i; σ3i,shell is the nodal stress component of shell element on interface along axis i; ui,shell is the nodal displacement component of shell elements on interface along axis i; Msx and Msy are additional bending moment on the interface along axes x and y, respectively, induced by the nonuniform stress of shell elements.Figure 2
Coupling of 1D element with 2D elements.In (5), the solution method of the multipoint constraint equations about u1,beam, u2,beam, and u6,beam is the same as the method for (4). Thus, the multipoint constraint equations corresponding to u3,beam, u4,beam, and u5,beam are summarized as follows. By substituting the simplified form of stress σ33,shell=F3/A into (5), the multipoint constraint equation for u3,beam can be given as(6)u3,beam=1A∑in∫AiNshelldAu3,shell=X3u3,shell.According to the energy conservation principle, the work done of the nodal stress of shell elements should be equal to the work done of the nodal forceF4 of the beam element. Taking into account the work done of the additional bending momentMs, the relationship of nodal forces of beam element and nodal stresses of shell elements can be expressed as(7)F4u4,beam=∫Aσ33u3,shelldA+∫SMsxu4,shellds+∫SMsyu5,shellds,σ33=F4I12I122-I1I2x+I2I1I2-I122y,Msx=∫-t/2t/2σ33ydydxds=2∫0t/2F4I2I1I2-I122yydxds=t312F4I2I1I2-I122dxds,Msy=∫-t/2t/2σ33xdxdyds=2∫0t/2F4I12I122-I1I2xxdyds=t312F4I12I122-I1I2dyds,where Ms is the bending moment in unit length induced by the normal stresses along the thickness t (see Figure 3) of shell elements; Msx and Msy are the component ofMs on the interface along axes x and y, respectively; I12 is the product of inertia for axis 1 and axis 2.Figure 3
Bending moment of shell elements.From (7), the multipoint constraint equation for u4,beam can be expressed as(8)u4,beam=∑i=1n∫AiI12I122-I1I2x+I2I1I2-I122yNshellu3,shelldA+∑i=1n∫lit312I2I1I2-I122dxdsNshellu4,shelldl+∑i=1n∫lit312I12I122-I1I2dxdsNshellu5,shelldl.By the same way, the multipoint constraint equation foru5,beam can be expressed as(9)u5,beam=∑i=1n∫AiI1I122-I1I2x+I12I1I2-I122yNshellu3,shelldA+∑i=1n∫lit312I12I1I2-I122dxdsNshellu4,shelldl+∑i=1n∫lit312I1I122-I1I2dxdsNshellu5,shelldl.


## 2.3.
2D and 3D Elements Coupling

Figure4 shows the coupling interface of 2D shell elements and 3D solid elements. In this figure, ui′ and ui,shell are the nodal displacement components of solid elements and shell elements, respectively, on the interface along axis i. According to the energy conservation principle, the work done of the force of shell elements should be equal to the work done of the nodal stresses of solid elements. Thus, the relationship of force of shell elements and nodal stresses of solid elements is given by(10)
∫
L
F
i
′
u
i
,
s
h
e
l
l
d
x
=
∫
A
σ
3
i
u
i
′
d
A
,
i
=
1,2
,
3
∫
A
σ
33
u
3
′
d
A
,
i
=
4,5
∫
A
σ
31
u
1
′
d
A
,
i
=
6
,where Fi′ is force component of shell elements in unit length along axis i; σ3i is nodal stress component of solid elements along axis i; A is coupling interface area and L is the coupling interface length (see Figure 4); ui,shell and ui′ are the displacement component of shell element and solid element on interface along axis i, respectively.Figure 4
Coupling of 2D elements with 3D elements.The force componentFi′ can be formulated by the nodal stress on interface as(11)
F
i
′
=
∫
-
t
/
2
t
/
2
σ
3
i
d
y
,
i
=
1,2
,
3
∫
-
t
/
2
t
/
2
σ
33
y
d
y
,
i
=
4
∫
-
L
/
2
L
/
2
σ
33
x
d
x
,
i
=
5
∫
-
t
/
2
t
/
2
σ
31
y
d
y
,
i
=
6
,where t is the thickness of shell element.On the coupling interface, the nodal stresses of shell elements can be expressed as one-degree linear term and parabolic-quadratic term, respectively, as follows:(12)σ31=a+by,(13)σ32=f1-4y2t2,(14)σ33=c+dy+ex,where a, b, c, d, e, and f are parameters.The nodal stressσ3i of shell element can be obtained by substituting (15), (13), and (14) into (11) as(15)σ31=F1t+12F6t3y,(16)σ32=3F22t1-4y2t2,(17)σ33=F3t+12F4t3y+12F5L3x.By substituting (15), (16), and (17) with F1~6=[Nshell]{F1~6}=F1~6TNshellT, u1~6=[Nshell]{u1~6}, and u1~3′=[Nsolid]{u1~3′} into (10), the multipoint constraint equations for shell elements and solid elements can be written as(18)
u
i
=
∫
A
N
s
h
e
l
l
T
N
s
o
l
i
d
d
A
t
∫
L
N
s
h
e
l
l
T
N
s
h
e
l
l
d
x
u
1
′
=
X
1
u
1
′
,
i
=
1
3
∫
A
1
-
4
y
2
/
t
2
N
s
h
e
l
l
T
N
s
o
l
i
d
d
A
2
t
∫
L
N
s
h
e
l
l
T
N
s
h
e
l
l
d
x
u
2
′
=
X
2
u
2
′
,
i
=
2
∫
A
N
s
h
e
l
l
T
N
s
o
l
i
d
d
A
t
∫
L
N
s
h
e
l
l
T
N
s
h
e
l
l
d
x
u
2
′
=
X
3
u
2
′
,
i
=
3
12
∫
A
y
N
s
h
e
l
l
T
N
s
o
l
i
d
d
A
t
3
∫
L
N
s
h
e
l
l
T
N
s
h
e
l
l
d
x
u
3
′
=
X
4
u
3
′
,
i
=
4
12
∫
A
x
N
s
h
e
l
l
T
N
s
o
l
i
d
d
A
L
3
∫
t
N
s
h
e
l
l
T
N
s
h
e
l
l
d
y
u
3
′
=
X
5
u
3
′
,
i
=
5
12
∫
A
y
N
s
h
e
l
l
T
N
s
o
l
i
d
d
A
t
3
∫
L
N
s
h
e
l
l
T
N
s
h
e
l
l
d
x
u
1
′
=
X
6
u
1
′
,
i
=
6
,where {u1~6} and {u1~3′} are nodal displacement matrixes for shell elements and solid elements, respectively; [Nshell] and [Nsolid] are shape functions for shell elements and solid elements, respectively; {F1~6} is nodal force matrix for shell elements; [u1~3′] is nodal displacement matrix for solid elements on the coupling interface.


## 3. Generalized Damage Model Combined with Performance Levels

The generalized damage model and multilevel performance are shown in Figure5. In this figure, δ is the generalized deformation for every level, while δi, δi,e, and δi,u represent the deformation, elastic limit deformation, and ultimate deformation for level i, respectively; F is the generalized force which corresponds to the generalized deformation δ; Fi′ and Fi represent the force for undamaged and damaged configuration, respectively, while Fi,u′ and Fi,u are the ultimate bearing capacity for undamaged and damaged configuration, respectively; K is the generalized stiffness which is the ratio of the generalized force F to the generalized deformation δ and Ki,0, Ki, and Ki,eq are the initial stiffness, secant stiffness, and equivalent stiffness, respectively. The equivalent stiffness Ki,eq represents the effect of the damage on the stiffness of the undamaged configuration and can be expressed as Ki,eq=(δi·Ki-δi,e·Ki,0)/(δi-δi,e). As shown in Figure 5, the loss of bearing capacity of the damage configuration is used to define the generalized multilevel damage model as(19)Di=δi,d·diαi,(20)di=1-Ki,eqKi,0,(21)δi,d=δi-δi,eδi,u-δi,e,where Di is the generalized multilevel damage model; di is the generalized stiffness damage; δi,d is the generalized deformation damage; αi is the corresponding parameter, which are obtained by plenty statistical analysis based on (19) and (21), as shown in Table 1.Table 1
Suggested values ofαi for each level.
Structural levels
Material level
Section level
Member level
Storey level
Structure level
Concrete in compression
Concrete in tension
Steel reinforcement
α
i
0.189
0.205
1.000
0.507
0.548
0.209
0.251Figure 5
Generalized damage model combined with multiperformance levels.Figure5 also shows the generalized performance with five levels as follows: slight damage level (SD or I), minor damage level (MD or II), moderate damage level (SE or III), severe damage level (SE or IV), and collapse damage level (CO or V). The limit damage values of I, II, III, IV, and V are 0.2, 0.4, 0.6, 0.8, and 1.0, respectively, for every structural level (e.g., material, member, and structure level). For each structural level, the deformation variables are taken as the damage indicators as shown in Figure 5.At structure level,Δe,Δy,Δsp,Δc,Δbu,Δu are the structure top displacement and correspond to elastic limit, onset of first yield, concrete spalling in weaker elements, onset of concrete crushing, onset of disclosing of buckled reinforcement, and structure collapse, respectively.At storey level,θe,θy,θsp,θc,θbu,θu  are the interstorey drift ratio and correspond to elastic behavior limit, onset of first yield, concrete spalling in weaker elements, onset of concrete crushing, onset of disclosing of buckled reinforcement, and storey failure, respectively.At member level,ue,uy,usp,uc,ubu,uu  are the element (beam or column) drift and correspond to elastic behavior limit, first yield of steel reinforcement, spalling of exterior concrete, crushing of core concrete, buckling of steel reinforcement, and element failure, respectively.At section level,ϕe,ϕy,ϕsp,ϕc,ϕbu,ϕu  are the section curvature and correspond to elastic behavior limit, first yield of steel reinforcement, spalling of exterior concrete, crushing of core concrete, buckling of steel reinforcement, and element failure, respectively.At material level, the values of the corresponding stresses of strain damage indicators for concrete and reinforcement are listed in Table2. As shown in Figure 5, εcu, εtu  are the concrete ultimate compressive, tensile strain; ε1.5s denotes the steel reinforcement strain corresponding to stress of 1.5fy, in which fy is the reinforcement yield strength. In Table 2, εc, εtdenote the concrete compressive, tensile strain damage indicator, respectively; σc, σtdenote the concrete compressive, tensile stress corresponding to εc, εt, respectively; εs is the reinforcement strain damage indicator corresponding to stress σs.Table 2
The values of corresponding stresses of strain damage indicators at material level.
ε
c
ε
c
e
ε
0.5
c
ε
0.75
c
ε
1.0
c
ε
-
0.25
c
σ
c
0.3
f
c
′
0.5
f
c
′
0.75
f
c
′
f
c
′
0.75
f
c
′
ε
t
ε
t
e
ε
0.75
t
ε
1.0
t
ε
-
0.25
t
ε
-
0.4
t
σ
t
0.6
f
t
0.75
f
t
f
t
0.75
f
t
0.6
f
t
ε
s
ε
s
y
ε
1.1
s
ε
1.2
s
ε
1.3
s
ε
1.4
s
σ
s
f
y
1.1
f
y
1.2
f
y
1.3
f
y
1.4
f
yIt is clear that the generalized multilevel damage model (Equation (19)) covers all the performance and structural levels using different damage indicators. Thus, the proposed generalized damage model combined with multilevel performance can be used here to study damage evolution at various structural levels.


## 4. Multiscale Analysis for a Real RC Structure

### 4.1. Test and Micro-Macro-Coupling FEM

The test structure and loading system are shown in Figure6. The original RC frame structure was built at the beginning of the 1980s in Shanghai, China, with three floors, five-by-five bays, exterior walls, and grillage foundation. The test structure was separated from the original building with one-by-one bay and the remainder structure was used as the loading reaction. Figure 6 gives the geometry of the test structure. The floor structure was made of precast concrete slabs of 120 × 830 mm2 and 120 × 430 mm2 cross sections. The Young modulus of concrete is measured as 2.68 × 104 N/mm2. The test strength of concrete is measured as 22.69 N/mm2. The yielding strength and limit strength of the longitudinal reinforcement are measured as 325.93 N/mm2 and 482.79 N/mm2, respectively. The yielding strength and limit strength of the stirrups reinforcement are measured as 251.27 N/mm2 and 349.91 N/mm2, respectively.Figure 6
The test structure and loading method (unit: ×10−3 m).The earthquake action is assumed to be lateral forces that acted on each storey as an inverted triangle distribution. In the test, the lateral loading was applied on six beam-column joints by six hydraulic jacks as shown in Figure6. A scaffold was fixed on the ground and six displacement gauges were installed on it to measure the absolute displacements of the six joints separately during the test. The vector of lateral loading {F1,F2,F3,F4,F5,F6}, as shown in Figure 6, was achieved as 0.535,0.414,0.898,0.699,1.000,0.732Vy according to the distribution of the concentrated mass of each joint. Vy is the lateral force of F5, which was taken as the referential loading. At the beginning, the loading was force-controlled mode with force increment 15 kN of F6. At last, the loading was displacement-controlled mode with the displacement increment 20 mm of F5.Three numerical models are used to simulate test as shown in Figure7. In those finite element models, the concrete behavior was described by concrete plastic-damage model [28]. The masonry walls were also described by concrete plastic-damage model by equating the ratio of the biaxial compressive strength to the uniaxial compressive strength to 2.0. Although each numerical model could reflect the global structure response, not all models could capture the damage details at micro-scale. In the macro-scale finite element model (see Figure 7(a)), the beams and columns were modeled by B31 element, which is a Timoshenko 2-node linear beam element in space. The walls and floors were modeled by S3 element, which is a three-node triangular general-purpose shell element. There are total 12885 nodes in this model, so it has a low computational cost. However, obviously, this model could not capture the damage details at micro-scale.Figure 7
Numerical computational model: (a) macro-scale FEM; (b) micro-scale FEM; (c) element-coupling model.
(a)
(b)
(c)In order to capture the damage details at micro-scale, the micro-scale finite element model (see Figure7(b)) was established using ANSYS package [29, 30]. The columns and beams were modeled by 3D element SOLID65. The floors were assumed to be in elasticity and modeled by SHELL143 element. Longitudinal rebars and transverse stirrups were modeled by 1D truss element LINK8. Because the shell element could not simulate the fracture behavior under tension action, an equivalent concrete model was used for brick masonry with 3D element SOLID65. The total number of nodes in this model is 102331, which indicate that it has higher computational cost than macro-scale finite element model. Aiming to obtain the damage details at micro-scale with good computational cost, a mixed-micro-macro-scale finite element model, that is, the element-coupling model shown in Figure 7(c), was proposed with the aid of (1) to (18). It includes the advantages of the macro-scale and micro-scale finite element model. In major damage regions, the concrete and masonry were modeled by C3D8R elements, which is the 8-node linear brick, reduced integration with hourglass control continuum element. The steel reinforcement was modeled by the T3D2 elements, which is the 3D stress/displacement 2-node linear displacement truss element. Steel reinforcement elements were embedded in the concrete elements. In minor damage regions, the beams and columns were modeled by B31 elements, and the floors and walls were modeled by S3 elements. The plastic-damage model was used for concrete material. Using the same mesh refinements of micro-scale FEM, the total number of nodes in the model is 80544, which indicate that its computational cost is between the macro-scale and micro-scale FEM.Figure8 shows the comparisons between test and numerical results of total base shear versus top drift angle of K1 and K2 single frame. At the beginning, no visible cracks were observed on the structural members. Until the displacements ofF5 and F6 reached 17.3 mm and 43.9 mm, respectively, some minor cracks appeared mainly at the ends of bottom columns. After that, the structure had plastic deformation. Thus, this state was taken as the elastic limit state. When the displacement ofF5 and F6 reached 52.9 mm and 146.6 mm, the structure got the peak base shear of 859 kN. At this state, some inclined cracks occurred at the ends of the bottom columns. While the displacement ofF6 and F6 reached 166.5 mm, the cracks on top of column Z41 expanded and fractured suddenly. Finally, column Z31 also fractured at top end when the displacement of F5 reached 111.1 mm. It is the collapse level state. The displacement differences ofF5 and F6 at failure state indicates that torsional deformation effected heavily the structure behavior due to the asymmetry walls. The failure damages are shown in Figure 9. It can be seen that the element-coupling model could capture the damage details in micro-scale with a relatively good computational cost.Figure 8
The primarily calculated bearing capacity results compared with the test results.Figure 9
The calculation failure damage states ofK1/K2 frames and test damage results.


### 4.2. Multiscale Damage Assessment

Using (19), the generalized damage at different structural level could be obtained. Figure 10 shows the calculated generalized damage evolution at different levels. The results of damage indicators, that is, structural drift, interstorey drift ratio, member drift, curvature and strain or stress, and generalized damage at different levels of states S1, S2, and S3, are listed separately in Table 3. In this table, ΔF5 means the drift of loading point F5 (see Figure 6) and D means the damage of the structure; θstorey-1 means the interstorey drift ration of storey-1 and Dstorey-1 means the damage of storey-1; uZ31 means the drift of column Z31 (see Figure 7); DZ31 means the damage of column Z31; ϕA means the curvature of section A (see Figure 9), and DA means the damage of section A; εA1 means the strain of concrete point A1, and DA1 means the damage of concrete point A1; σAS2 means the stress of reinforcement point AS2 (see Figure 9), and DAS2 means the damage of reinforcement point AS2.Table 3
The values of damage indicators and generalized damage at different level.
Damage state
Structure level
Storey level
Member level
Section level
Material level
Δ
F
5  (×10−3 m)
D
θ
storey-1
D
storey-1
u
Z
31  (×10−3 m)
D
Z
31
ϕ
A  (×10−6)
D
A
ε
A1  (×10−3)
D
A1
σ
AS2  (MPa)
D
AS2
S1
19.6
0.56
0.001
0.69
10.7
0
0.9
0
0.29
0.12
114.7
0
S2
59.5
0.80
0.005
0.88
50.5
0.54
2.6
0
0.48
0.31
329.4
0.02
S3
113.7
0.84
0.016
0.88
88.7
0.69
5.9
0.3
0.83
0.44
337.9
0.08Figure 10
The calculated multilevel damage evolutions.
(a)
Damage evolutions at structure level and storey level
(b)
Damage evolutions at member level and section level
(c)
Damage evolutions at material levelAt damage state S1, Figure9 shows that the damage performances of K2 frame, storey-1, storey-2, and structure reached to moderate damage level, while K1 frame and storey-3 almost had no damage. The damage value of global structure and storey-1 is 0.56 and 0.69, respectively, as shown in Table 3. The damage performances of column Z21 and Z41 reached minor damage level, while sections C and D almost had no damage. At material level, the damage performances of concrete points C1 (in tension) and C2 (in compression) reached ultimate damage level and minor damage level, respectively, while the damage of reinforcement points CS1 and CS2 was very minor.At state S2, Figure9 shows that the damage performances of K2 frame, storey-1, storey-2, and structure reached ultimate damage level, while K1 frame and storey-3 reached moderate damage level. The damage value of structure and storey-2 is 0.80 and 0.88, respectively, as shown in Table 3. The damage performances of columns Z21 and Z41 reached moderate damage level. At material level, the damage performances of concrete points C1 (in tension) and C2 (in compression) reached ultimate damage level and moderate damage level, respectively, while the damage of reinforcement points CS1 and CS2 was very minor.At state S3, Figure9 shows that the damage performance of K1 frame reached ultimate damage level. The damage performances of columns Z11 and column Z31 reached moderate damage level. The damage value of column Z31 is 0.69 as shown in Table 3. At material level, the damage performances of concrete points A1 (in tension) and A2 (in compression) reached ultimate damage level and moderate damage level, respectively, while the damage of reinforcement points AS1 and AS2 was very small.It can be seen that the multilevel damage evolution analysis gives a complete explanation of damage mechanism from material level to structure level for this RC structure. This method also helps to find the damage process and damage state for every level (i.e., structure, storey, member, section, or material). Therefore, this method could provide more damage performance details (not only at macro-scale but also at micro-scale) for the performance-based design.


## 4.1. Test and Micro-Macro-Coupling FEM

The test structure and loading system are shown in Figure6. The original RC frame structure was built at the beginning of the 1980s in Shanghai, China, with three floors, five-by-five bays, exterior walls, and grillage foundation. The test structure was separated from the original building with one-by-one bay and the remainder structure was used as the loading reaction. Figure 6 gives the geometry of the test structure. The floor structure was made of precast concrete slabs of 120 × 830 mm2 and 120 × 430 mm2 cross sections. The Young modulus of concrete is measured as 2.68 × 104 N/mm2. The test strength of concrete is measured as 22.69 N/mm2. The yielding strength and limit strength of the longitudinal reinforcement are measured as 325.93 N/mm2 and 482.79 N/mm2, respectively. The yielding strength and limit strength of the stirrups reinforcement are measured as 251.27 N/mm2 and 349.91 N/mm2, respectively.Figure 6
The test structure and loading method (unit: ×10−3 m).The earthquake action is assumed to be lateral forces that acted on each storey as an inverted triangle distribution. In the test, the lateral loading was applied on six beam-column joints by six hydraulic jacks as shown in Figure6. A scaffold was fixed on the ground and six displacement gauges were installed on it to measure the absolute displacements of the six joints separately during the test. The vector of lateral loading {F1,F2,F3,F4,F5,F6}, as shown in Figure 6, was achieved as 0.535,0.414,0.898,0.699,1.000,0.732Vy according to the distribution of the concentrated mass of each joint. Vy is the lateral force of F5, which was taken as the referential loading. At the beginning, the loading was force-controlled mode with force increment 15 kN of F6. At last, the loading was displacement-controlled mode with the displacement increment 20 mm of F5.Three numerical models are used to simulate test as shown in Figure7. In those finite element models, the concrete behavior was described by concrete plastic-damage model [28]. The masonry walls were also described by concrete plastic-damage model by equating the ratio of the biaxial compressive strength to the uniaxial compressive strength to 2.0. Although each numerical model could reflect the global structure response, not all models could capture the damage details at micro-scale. In the macro-scale finite element model (see Figure 7(a)), the beams and columns were modeled by B31 element, which is a Timoshenko 2-node linear beam element in space. The walls and floors were modeled by S3 element, which is a three-node triangular general-purpose shell element. There are total 12885 nodes in this model, so it has a low computational cost. However, obviously, this model could not capture the damage details at micro-scale.Figure 7
Numerical computational model: (a) macro-scale FEM; (b) micro-scale FEM; (c) element-coupling model.
(a)
(b)
(c)In order to capture the damage details at micro-scale, the micro-scale finite element model (see Figure7(b)) was established using ANSYS package [29, 30]. The columns and beams were modeled by 3D element SOLID65. The floors were assumed to be in elasticity and modeled by SHELL143 element. Longitudinal rebars and transverse stirrups were modeled by 1D truss element LINK8. Because the shell element could not simulate the fracture behavior under tension action, an equivalent concrete model was used for brick masonry with 3D element SOLID65. The total number of nodes in this model is 102331, which indicate that it has higher computational cost than macro-scale finite element model. Aiming to obtain the damage details at micro-scale with good computational cost, a mixed-micro-macro-scale finite element model, that is, the element-coupling model shown in Figure 7(c), was proposed with the aid of (1) to (18). It includes the advantages of the macro-scale and micro-scale finite element model. In major damage regions, the concrete and masonry were modeled by C3D8R elements, which is the 8-node linear brick, reduced integration with hourglass control continuum element. The steel reinforcement was modeled by the T3D2 elements, which is the 3D stress/displacement 2-node linear displacement truss element. Steel reinforcement elements were embedded in the concrete elements. In minor damage regions, the beams and columns were modeled by B31 elements, and the floors and walls were modeled by S3 elements. The plastic-damage model was used for concrete material. Using the same mesh refinements of micro-scale FEM, the total number of nodes in the model is 80544, which indicate that its computational cost is between the macro-scale and micro-scale FEM.Figure8 shows the comparisons between test and numerical results of total base shear versus top drift angle of K1 and K2 single frame. At the beginning, no visible cracks were observed on the structural members. Until the displacements ofF5 and F6 reached 17.3 mm and 43.9 mm, respectively, some minor cracks appeared mainly at the ends of bottom columns. After that, the structure had plastic deformation. Thus, this state was taken as the elastic limit state. When the displacement ofF5 and F6 reached 52.9 mm and 146.6 mm, the structure got the peak base shear of 859 kN. At this state, some inclined cracks occurred at the ends of the bottom columns. While the displacement ofF6 and F6 reached 166.5 mm, the cracks on top of column Z41 expanded and fractured suddenly. Finally, column Z31 also fractured at top end when the displacement of F5 reached 111.1 mm. It is the collapse level state. The displacement differences ofF5 and F6 at failure state indicates that torsional deformation effected heavily the structure behavior due to the asymmetry walls. The failure damages are shown in Figure 9. It can be seen that the element-coupling model could capture the damage details in micro-scale with a relatively good computational cost.Figure 8
The primarily calculated bearing capacity results compared with the test results.Figure 9
The calculation failure damage states ofK1/K2 frames and test damage results.


## 4.2. Multiscale Damage Assessment

Using (19), the generalized damage at different structural level could be obtained. Figure 10 shows the calculated generalized damage evolution at different levels. The results of damage indicators, that is, structural drift, interstorey drift ratio, member drift, curvature and strain or stress, and generalized damage at different levels of states S1, S2, and S3, are listed separately in Table 3. In this table, ΔF5 means the drift of loading point F5 (see Figure 6) and D means the damage of the structure; θstorey-1 means the interstorey drift ration of storey-1 and Dstorey-1 means the damage of storey-1; uZ31 means the drift of column Z31 (see Figure 7); DZ31 means the damage of column Z31; ϕA means the curvature of section A (see Figure 9), and DA means the damage of section A; εA1 means the strain of concrete point A1, and DA1 means the damage of concrete point A1; σAS2 means the stress of reinforcement point AS2 (see Figure 9), and DAS2 means the damage of reinforcement point AS2.Table 3
The values of damage indicators and generalized damage at different level.
Damage state
Structure level
Storey level
Member level
Section level
Material level
Δ
F
5  (×10−3 m)
D
θ
storey-1
D
storey-1
u
Z
31  (×10−3 m)
D
Z
31
ϕ
A  (×10−6)
D
A
ε
A1  (×10−3)
D
A1
σ
AS2  (MPa)
D
AS2
S1
19.6
0.56
0.001
0.69
10.7
0
0.9
0
0.29
0.12
114.7
0
S2
59.5
0.80
0.005
0.88
50.5
0.54
2.6
0
0.48
0.31
329.4
0.02
S3
113.7
0.84
0.016
0.88
88.7
0.69
5.9
0.3
0.83
0.44
337.9
0.08Figure 10
The calculated multilevel damage evolutions.
(a)
Damage evolutions at structure level and storey level
(b)
Damage evolutions at member level and section level
(c)
Damage evolutions at material levelAt damage state S1, Figure9 shows that the damage performances of K2 frame, storey-1, storey-2, and structure reached to moderate damage level, while K1 frame and storey-3 almost had no damage. The damage value of global structure and storey-1 is 0.56 and 0.69, respectively, as shown in Table 3. The damage performances of column Z21 and Z41 reached minor damage level, while sections C and D almost had no damage. At material level, the damage performances of concrete points C1 (in tension) and C2 (in compression) reached ultimate damage level and minor damage level, respectively, while the damage of reinforcement points CS1 and CS2 was very minor.At state S2, Figure9 shows that the damage performances of K2 frame, storey-1, storey-2, and structure reached ultimate damage level, while K1 frame and storey-3 reached moderate damage level. The damage value of structure and storey-2 is 0.80 and 0.88, respectively, as shown in Table 3. The damage performances of columns Z21 and Z41 reached moderate damage level. At material level, the damage performances of concrete points C1 (in tension) and C2 (in compression) reached ultimate damage level and moderate damage level, respectively, while the damage of reinforcement points CS1 and CS2 was very minor.At state S3, Figure9 shows that the damage performance of K1 frame reached ultimate damage level. The damage performances of columns Z11 and column Z31 reached moderate damage level. The damage value of column Z31 is 0.69 as shown in Table 3. At material level, the damage performances of concrete points A1 (in tension) and A2 (in compression) reached ultimate damage level and moderate damage level, respectively, while the damage of reinforcement points AS1 and AS2 was very small.It can be seen that the multilevel damage evolution analysis gives a complete explanation of damage mechanism from material level to structure level for this RC structure. This method also helps to find the damage process and damage state for every level (i.e., structure, storey, member, section, or material). Therefore, this method could provide more damage performance details (not only at macro-scale but also at micro-scale) for the performance-based design.


## 5. Conclusions

Based on the energy conservation principle, the coupling of mixed dimensional elements could be established in finite element model. This mixed-micro-macro-scale finite element model could capture the damage details at micro-scale and global structural nonlinear behavior together. When using the same mesh refinements of macro-scale finite element models, it qualitatively has a relative good computational cost. It is available for the damage numerical analysis for RC structures even for some high-rise or complex RC structures.Aiming to assess the damage evolution from micro-scale to macro-scale, a generalized damage model combined with multilevel performance is proposed. By using element-coupling model, it has been used to evaluate the damage of a real RC frame structure subjected by lateral loading in situ. The very good agreement between the calculation and test results shows that the proposed generalized damage model can correctly evaluate the damage states or evolutions for different structural and performance levels. It is a very useful tool for analyzing damage mechanisms from material level to structure level of RC structures.



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*Source: 764517-2015-10-18.xml*