METHOD FOR STATIC IDENTIFICATION OF DAMAGE TO SIMPLY SUPPORTED BEAM UNDER UNCERTAIN LOAD

Abstract

The present disclosure provides a method for static identification of damage to a simply supported beam under an uncertain load. In this identification method, a beam body is first segmented, and the relationships between key measured sectional rotation angles and the flexural rigidities of segments of a structure under the action of a load are established by using a mechanics principle; then, an applied static load is removed by means of a division operation, and the relative relationships between the flexural rigidities of the segments of the structure are obtained; and finally, these relative relationships are compared with the corresponding relative relationships when the structure is not damaged, so as to determine the position of damage to the structure and assess the amount of damage, such that the static identification for damage to a simply supported beam structure can be completed without calibrating a load in advance.

Claims

1. A method for static identification of damage to a simply supported beam under an uncertain load, comprising: step 1, applying a concentrated load to the simply supported beam by three-point bending, wherein the applied concentrated load is set to p.sub.1, and acts on a midspan of the beam structure; step 2, dividing the beam structure into eight equal segments along a key section according to a span l, and assuming that the eight segments have particular flexural rigidities of EI.sub.r1, $\frac{1}{k_2}E{I}_{r1},\frac{1}{k_3}E{I}_{r1},\frac{1}{k_4}E{I}_{r1},\frac{1}{k_5}E{I}_{r1},\frac{1}{k_6}E{I}_{r1},\frac{1}{k_7}E{I}_{r1}\text{and}\frac{1}{k_8}E{I}_{r1},$ respectively, wherein k.sub.2, k.sub.3, k.sub.4, k.sub.5, k.sub.6, k.sub.7 and k.sub.8 each denote a reciprocal of a ratio of the flexural rigidity of each of the second segment, the third segment, the fourth segment, the fifth segment, the sixth segment, the seventh segment and the eighth segment to the flexural rigidity of the first segment; step 3, arranging a tilt angle sensor at a segment section of the beam structure and at sections of fulcrums at both ends of the beam structure, wherein the tilt angle sensor is used to measure a rotation angle at which the beam body rotates around a horizontal axis, a measured sectional rotation angle at the fulcrum close to the first segment is θ.sub.0, a measured sectional rotation angle between the first segment and the second segment is θ.sub.1, a measured sectional rotation angle between the second segment and the third segment is θ.sub.2, by analogy, a measured sectional rotation angle between the third segment and the fourth segment is θ.sub.3, a measured sectional rotation angle between the fourth segment and the fifth segment is θ.sub.4, a measured sectional rotation angle between the fifth segment and the sixth segment is θ.sub.5, a measured sectional rotation angle between the sixth segment and the seventh segment is θ.sub.6, a measured sectional rotation angle between the seventh segment and the eighth segment is θ.sub.7, and a measured sectional rotation angle at the fulcrum close to the eighth segment is θ.sub.8; step 4, solving the following formula by substituting the foregoing measured sectional rotation angles θ.sub.0 - θ.sub.8 to obtain k.sub.2, k.sub.3, k.sub.4, k.sub.5, k.sub.6, k.sub.7 and k.sub.8: $\begin{array}{l}\left\{\begin{array}{l}{k}_2=\frac{1}{3}\left(\frac{{\theta }_1-{\theta }_2}{{\theta }_0-{\theta }_1}\right);k_3=\frac{1}{5}\left(\frac{{\theta }_2-{\theta }_3}{{\theta }_0-{\theta }_1}\right);\text{}\text{}\text{}{k}_4=\frac{1}{7}\left(\frac{{\theta }_3-{\theta }_4}{{\theta }_0-{\theta }_1}\right);k_5=\frac{1}{7}\left(\frac{{\theta }_4-{\theta }_5}{{\theta }_0-{\theta }_1}\right);\\ k_6=\frac{1}{5}\left(\frac{{\theta }_5-{\theta }_6}{{\theta }_0-{\theta }_1}\right);k_7=\frac{1}{3}\left(\frac{{\theta }_6-{\theta }_7}{{\theta }_0-{\theta }_1}\right);k_8=\left(\frac{{\theta }_7-{\theta }_8}{{\theta }_0-{\theta }_1}\right)\end{array}\right)\\ ;\end{array}$ step 5, establishing a finite element numerical model of the simply supported beam in a damage-free state under a concentrated load P.sub.2 acting on the midspan, extracting the corresponding measured sectional rotation angles in step 3 and setting the same as θ.sub.0d, θ.sub.1d, θ.sub.2d, θ.sub.3d, θ.sub.4d, θ.sub.5d, θ.sub.6d, θ.sub.7d and θ.sub.8d, and calculating, according to the following formula, theoretical values k.sub.2d, k.sub.3d, k.sub.4d, k.sub.5d, k.sub.6d, k.sub.7d and k.sub.8d of the structure in the damage-free state: $\begin{array}{l}\left\{\begin{array}{l}{k}_{2d}=\frac{1}{3}\left(\frac{{\theta }_{1d}-{\theta }_{2d}}{{\theta }_{0d}-{\theta }_{1d}}\right);k_{3d}=\frac{1}{5}\left(\frac{{\theta }_{2d}-{\theta }_{3d}}{{\theta }_{0d}-{\theta }_{1d}}\right);k_{4d}=\frac{1}{7}\left(\frac{{\theta }_{3d}-{\theta }_{4d}}{{\theta }_{0d}-{\theta }_{1d}}\right);k_{5d}=\frac{1}{7}\left(\frac{{\theta }_{4d}-{\theta }_{5d}}{{\theta }_{0d}-{\theta }_{1d}}\right);\\ k_{6d}=\frac{1}{5}\left(\frac{{\theta }_{5d}-{\theta }_{6d}}{{\theta }_{0d}-{\theta }_{1d}}\right);k_7=\frac{1}{3}\left(\frac{{\theta }_{6d}-{\theta }_{7d}}{{\theta }_{0d}-{\theta }_{1d}}\right);k_8=\left(\frac{{\theta }_{7d}-{\theta }_{8d}}{{\theta }_{0d}-{\theta }_{1d}}\right)\end{array}\right)\\ ;\end{array}$ step 6, calculating, according to the following formula, a variation of the flexural rigidity of each segment with respect to the structure in the damage-free state: $\left\{\begin{array}{l}{\Delta }_2=\left(\frac{1}{k_2}-\frac{1}{k_{2d}}\right)/\left(\frac{1}{k_{2d}}\right)\times 100\%;{\Delta }_3=\left(\frac{1}{k_3}-\frac{1}{k_{3d}}\right)/\left(\frac{1}{k_{3d}}\right)\times 100\%;\\ {\Delta }_4=\left(\frac{1}{k_4}-\frac{1}{k_{4d}}\right)/\left(\frac{1}{k_{4d}}\right)\times 100\%;{\Delta }_5=\left(\frac{1}{k_5}-\frac{1}{k_{5d}}\right)/\left(\frac{1}{k_{5d}}\right)\times 100\%;\\ {\Delta }_6=\left(\frac{1}{k_6}-\frac{1}{k_{6d}}\right)/\left(\frac{1}{k_{6d}}\right)\times 100\%;{\Delta }_7=\left(\frac{1}{k_7}-\frac{1}{k_{7d}}\right)/\left(\frac{1}{k_{7d}}\right)\times 100\%;\\ {\Delta }_8=\left(\frac{1}{k_8}-\frac{1}{k_{8d}}\right)/\left(\frac{1}{k_{8d}}\right)\times 100\%;;\end{array}\right)$ wherein Δ.sub.2, Δ.sub.3, Δ.sub.4, Δ.sub.5, Δ.sub.6, Δ.sub.7 and Δ.sub.8 respectively denote variations of the flexural rigidities of the second segment, the third segment, the fourth segment, the fifth segment, the sixth segment, the seventh segment and the eighth segment with respect to the structure in the damage-free state; and step 7, solving following formulas to obtain amounts of damage D.sub.1, D.sub.2, D.sub.3, D.sub.4, D.sub.5, D.sub.6, D.sub.7 and D.sub.8 of the first segment, the second segment, the third segment, the fourth segment, the fifth segment, the sixth segment, the seventh segment and the eighth segment, respectively: $\left\{\begin{array}{l}{D}_1=\max \left\{{\Delta }_2,{\Delta }_3,{\Delta }_4,{\Delta }_5,{\Delta }_6,{\Delta }_7,{\Delta }_8\right\};\\ D_2=\left|{\Delta }_2-D_1\right|;D_3=\left|{\Delta }_3-D_1\right|;D_4=\left|{\Delta }_4-D_1\right|;D_5=\left|{\Delta }_5-D_1\right|;\\ D_6=\left|{\Delta }_6-D_1\right|;D_7=\left|{\Delta }_7-D_1\right|;D_8=\left|{\Delta }_8-D_1\right|\end{array}\right)$ .

2. The method for static identification of damage to a simply supported beam under an uncertain load according to claim 1, wherein the concentrated load p.sub.1 applied in step 1 and the concentrated load p.sub.2 applied in the finite element model in step 5 both take an optional value in accordance with a following principle: a maximum value is taken as far as possible under the condition of keeping the structure in an elastic working state; and it is possible that p.sub.1 and p.sub.2 have unequal values.

3. The method for static identification of damage to a simply supported beam under an uncertain load according to claim 1, wherein the measurement accuracy of each sectional rotation angle is not lower than 0.001°.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0022] FIG. 1 is a schematic diagram of an identification method provided by the present disclosure.

[0023] FIG. 2 is a schematic diagram of a simply supported beam structure with a uniform section (in a unit of cm).

[0024] FIG. 3 is a diagram of a finite element numerical model for a simply supported beam structure with a uniform section (condition 1).

[0025] FIG. 4 is a schematic diagram of a simply supported beam structure with a variable section (in a unit of cm).

[0026] FIG. 5 is a diagram of a finite element numerical model of a beam structure with a variable section in a damage-free state (concentrated force of 80 kN, and the elastic modulus of C50).

DETAILED DESCRIPTION OF THE EMBODIMENTS

[0027] The present disclosure will be further described with reference to the accompanying drawings and the embodiments below.

[0028] Referring to FIG. 1, the present disclosure provides a method for static identification of damage to a simply supported beam under an uncertain load, including:

[0029] step 1, apply a concentrated load to the simply supported beam by three-point bending, where the applied concentrated load is set to p.sub.1, and acts on a midspan of the beam structure.

[0030] step 2, divide the beam structure into eight equal segments along a key section according to a span l, and assume that the eight segments have particular flexural rigidities of EI.sub.r1,

[00006]$\frac{1}{k_2}E{I}_{r1},\frac{1}{k_3}E{I}_{r1},\frac{1}{k_4}E{I}_{r1},\frac{1}{k_5}E{I}_{r1},\frac{1}{k_6}E{I}_{r1},\frac{1}{k_7}E{I}_{r1}\text{and}\frac{1}{k_8}E{I}_{r1},$

and respectively, where k.sub.2, k.sub.3, k.sub.4, k.sub.5, k.sub.6, k.sub.7 and k.sub.8 each denote a reciprocal of a ratio of the flexural rigidity of each of the second segment, the third segment, the fourth segment, the fifth segment, the sixth segment, the seventh segment and the eighth segment to the flexural rigidity of the first segment.

[0031] step 3, arrange a tilt angle sensor at a segment section of the beam structure and at sections of fulcrums at both ends of the beam structure, where the tilt angle sensor is used to measure a rotation angle at which the beam body rotates around a horizontal axis, a measured sectional rotation angle at the fulcrum close to the first segment is θ.sub.0, a measured sectional rotation angle between the first segment and the second segment is θ.sub.1, a measured sectional rotation angle between the second segment and the third segment is θ.sub.2, by analogy, a measured sectional rotation angle between the third segment and the fourth segment is θ.sub.3, a measured sectional rotation angle between the fourth segment and the fifth segment is θ.sub.4 , a measured sectional rotation angle between the fifth segment and the sixth segment is θ.sub.5, a measured sectional rotation angle between the sixth segment and the seventh segment is θ.sub.6, a measured sectional rotation angle between the seventh segment and the eighth segment is θ.sub.7, and a measured sectional rotation angle at the fulcrum close to the eighth segment is θ.sub.8. Further, in this step, the measurement accuracy of each sectional rotation angle is not lower than 0.001°.

[0032] step 4, solve the following formula by substituting the foregoing measured sectional rotation angles θ.sub.0, - θ.sub.8, to obtain k.sub.2, k.sub.3, k.sub.4, k.sub.5, k.sub.6, k.sub.7 and k.sub.8:

[00007]$\left\{\begin{array}{l}\begin{array}{l}{k}_2=\frac{1}{3}\left(\frac{{\theta }_1-{\theta }_2}{{\theta }_0-{\theta }_1}\right);k_3=\frac{1}{5}\left(\frac{{\theta }_2-{\theta }_3}{{\theta }_0-{\theta }_1}\right);k_4=\frac{1}{7}\left(\frac{{\theta }_3-{\theta }_4}{{\theta }_0-{\theta }_1}\right);\\ k_5=\frac{1}{7}\left(\frac{{\theta }_4-{\theta }_5}{{\theta }_0-{\theta }_1}\right);\end{array}\hfill \\ k_6=\frac{1}{5}\left(\frac{{\theta }_5-{\theta }_6}{{\theta }_0-{\theta }_1}\right);k_7=\frac{1}{3}\left(\frac{{\theta }_6-{\theta }_7}{{\theta }_0-{\theta }_1}\right);k_8=\left(\frac{{\theta }_7-{\theta }_8}{{\theta }_0-{\theta }_1}\right);\hfill \end{array}\right)$

[0033] step 5, establish a finite element numerical model of the simply supported beam in a damage-free state under a concentrated load p.sub.2 rotation angle acting on the midspan, extract the corresponding measured sectional rotation angles in step 3 and set the same as θ.sub.0d, θ.sub.1d, θ.sub.2d, θ.sub.3d, θ.sub.4d, θ.sub.5d, θ.sub.6d, θ.sub.7d and θ.sub.8d with a precision of not lower than 0.001°, and calculate, according to the following formula, theoretical values k.sub.2d, k.sub.3d, k.sub.4d, k.sub.5d, k.sub.6d, k.sub.7d and k.sub.8d of the structure in the damage-free state:

[00008]$\left\{\begin{array}{l}\begin{array}{l}{k}_{2d}=\frac{1}{3}\left(\frac{{\theta }_{1d}-{\theta }_{2d}}{{\theta }_{0d}-{\theta }_{1d}}\right);k_{3d}=\frac{1}{5}\left(\frac{{\theta }_{2d}-{\theta }_{3d}}{{\theta }_{0d}-{\theta }_{1d}}\right);\\ k_{4d}=\frac{1}{7}\left(\frac{{\theta }_{3d}-{\theta }_{4d}}{{\theta }_{0d}-{\theta }_{1d}}\right);k_{5d}=\frac{1}{7}\left(\frac{{\theta }_{4d}-{\theta }_{5d}}{{\theta }_{0d}-{\theta }_{1d}}\right);\end{array}\hfill \\ \begin{array}{l}{k}_{6d}=\frac{1}{5}\left(\frac{{\theta }_{5d}-{\theta }_{6d}}{{\theta }_{0d}-{\theta }_{1d}}\right);k_7=\frac{1}{3}\left(\frac{{\theta }_{6d}-{\theta }_{7d}}{{\theta }_{0d}-{\theta }_{1d}}\right);\\ k_8=\left(\frac{{\theta }_{7d}-{\theta }_{8d}}{{\theta }_{0d}-{\theta }_{1d}}\right);\end{array}\hfill \end{array}\right)$

[0034] step 6, calculating, according to the following formula, a variation of the flexural rigidity of each segment with respect to the structure in the damage-free state:

[00009]$\left\{\begin{array}{ll}{\Delta }_2=\left(\frac{1}{k_2}-\frac{1}{k_{2d}}\right)/\left(\frac{1}{k_{2d}}\right)\times 100\%;\hfill & \begin{array}{l}{\Delta }_3=\left(\frac{1}{k_3}-\frac{1}{k_{3d}}\right)/\left(\frac{1}{k_{3d}}\right)\\ \times 100\%;\end{array}\hfill \\ {\Delta }_4=\left(\frac{1}{k_4}-\frac{1}{k_{4d}}\right)/\left(\frac{1}{k_{4d}}\right)\times 100\%;\hfill & \begin{array}{l}{\Delta }_5=\left(\frac{1}{k_5}-\frac{1}{k_{5d}}\right)/\left(\frac{1}{k_{5d}}\right)\\ \times 100\%;\end{array}\hfill \\ {\Delta }_6=\left(\frac{1}{k_6}-\frac{1}{k_{6d}}\right)/\left(\frac{1}{k_{6d}}\right)\times 100\%;\hfill & \begin{array}{l}{\Delta }_7=\left(\frac{1}{k_7}-\frac{1}{k_{7d}}\right)/\left(\frac{1}{k_{7d}}\right)\\ \times 100\%;\end{array}\hfill \\ {\Delta }_8=\left(\frac{1}{k_8}-\frac{1}{k_{8d}}\right)/\left(\frac{1}{k_{8d}}\right)\times 100\%\hfill & ;\hfill \end{array}\right)$

where Δ.sub.2, Δ.sub.3, Δ.sub.4, Δ.sub.5, Δ.sub.6, Δ.sub.7 and Δ.sub.8 respectively denote variations of the flexural rigidities of the second segment, the third segment, the fourth segment, the fifth segment, the sixth segment, the seventh segment and the eighth segment with respect to the structure in the damage-free state; and

[0035] step 7, solving following formulas to obtain amounts of damage D.sub.1, D.sub.2, D.sub.3, D.sub.4, D.sub.5, D.sub.6, D.sub.7 and D.sub.8 of the first segment, the second segment, the third segment, the fourth segment, the fifth segment, the sixth segment, the seventh segment and the eighth segment, respectively:

[00010]$\left\{\begin{array}{l}{D}_1=\max \left\{{\Delta }_2,{\Delta }_3,{\Delta }_4,{\Delta }_5,{\Delta }_6,{\Delta }_7,{\Delta }_8\right\};\hfill \\ D_2=\left|{\Delta }_2-D_1\right|;D_3=\left|{\Delta }_3-D_1\right|;D_4=\left|{\Delta }_4-D_1\right|;D_5=\left|{\Delta }_5-D_1\right|;\hfill \\ D_6=\left|{\Delta }_6-D_1\right|;D_7=\left|{\Delta }_7-D_1\right|;D_8=\left|{\Delta }_8-D_1\right|\hfill \end{array}\right).$

[0036] Further, it should be noted that, the concentrated load p.sub.1 applied in step 1 and the concentrated load p.sub.2 applied in the finite element model in step 5 both take an optional value in accordance with a following principle: a maximum value is taken as far as possible under the condition of keeping the structure in an elastic working state; and it is possible that p.sub.1 and p.sub.2 have unequal values.

[0037] In the foregoing steps, step 4 and step 5 are key steps of the present disclosure, and the derivation process of the formulas involved in step 4 and step 5 is described in detail with reference to FIG. 1.

[0038] As shown in FIG. 1, known parameters include: a span l, a concentrated load p.sub.1, a measured sectional rotation angle θ.sub.0 at the fulcrum close to the first segment (on the left end of a support), a measured sectional rotation angle θ.sub.1 between the first segment and the second segment (at l / 8), a measured sectional rotation angle θ.sub.2 between the second segment and the third segment (at l / 4), by analogy, a measured sectional rotation angle θ.sub.3 between the third segment and the fourth segment (at 3l / 8), a measured sectional rotation angle θ.sub.4 between the fourth segment and the fifth segment (at l / 2), a measured sectional rotation angle θ.sub.5 between the fifth segment and the sixth segment (at 5l / 8), a measured sectional rotation angle θ.sub.6 between the sixth segment and the seventh segment (at 3l / 4), a measured sectional rotation angle θ.sub.7 between the seventh segment and the eighth segment (at 7l / 8), and a measured sectional rotation angle θ.sub.8 at the fulcrum close to the eighth segment (on the right end of a support); and unknown variables include a flexural rigidity EI.sub.r1 of the first segment, and a reciprocal of a ratio of the flexural rigidity of each of the second segment, the third segment, the fourth segment, the fifth segment, the sixth segment, the seventh segment and the eighth segment to the flexural rigidity of the first segment, which is denoted as k.sub.2, k.sub.3, k.sub.4, k.sub.5, k.sub.6, k.sub.7 and k.sub.8.

[0039] In order to solve the above unknown variables, an impulse function S(x) is adopted, which is expressed as:

[00011]$S\left(x\right)={.Math.x-a.Math.}^n$

[0040] Where <> is a Macaulay bracket, x is an unknown variable, a is an arbitrary constant, and n is an exponential. When each variable has different values, the impulse function exhibits different forms, as follows: when

[00012]$n\ge 0,S\left(x\right)={.Math.x-a.Math.}^n=\left\{\begin{array}{ll}{\left(x-a\right)}^n\hfill & x\ge a\hfill \\ 0\hfill & x<a\hfill \end{array}\right)$

when

[00013]$n<0,S\left(x\right)={.Math.x-a.Math.}^n=\left\{\begin{array}{ll}\infty \hfill & x=a\hfill \\ 0\hfill & x\ne a\hfill \end{array}\right)$

[0041] Because of the unique form and definition, the impulse function can avoid the solving of integral constants, which simplifies the workload of calculation in calculus operation. The calculus form of impulse function is summarized as follows:

[00014]$\frac{dS\left(x\right)}{dx}=\left\{\begin{array}{ll}n{.Math.x-a.Math.}^{n-1}\hfill & n>0\hfill \\ {.Math.x-a.Math.}^{n-1}\hfill & n\le 0\hfill \end{array}\right)$

[00015]${\displaystyle \int S\left(x\right)dx}=\left\{\begin{array}{ll}\frac{1}{n+1}{.Math.x-a.Math.}^{n+1}\hfill & n>0\hfill \\ {.Math.x-a.Math.}^{n+1}\hfill & n\le 0\hfill \end{array}\right)$

[0042] The bending rigidity of the beam member shown in FIG. 1 is represented by the pulse function as follows:

[00016]$\frac{1}{B\left(x\right)}=\frac{1}{E{I}_{r1}}\left[\begin{array}{l}1+\left(k_2-1\right){.Math.x-\frac{l}{8}.Math.}^0+\left(k_3-k_2\right){.Math.x-\frac{2l}{8}.Math.}^0+\\ \left(k_4-k_3\right){.Math.x-\frac{3l}{8}.Math.}^0+\left(k_5-k_4\right){.Math.x-\frac{4l}{8}.Math.}^0+\\ \left(k_6-k_5\right){.Math.x-\frac{5l}{8}.Math.}^0+\left(k_7-k_6\right){.Math.x-\frac{6l}{8}.Math.}^0+\\ \left(k_8-k_7\right){.Math.x-\frac{7l}{8}.Math.}^0\end{array}\right]$

[0043] Based on the Timoshenko beam theory, the basic differential equations of the beam considering the effect of shear deformation are as follows:

[00017]$-\frac{d}{dx}\left[C\left(x\right)\left(\frac{dy}{dx}-\phi \right)\right]=q\left(x\right)$

[00018]$-\frac{d}{dx}\left[B\left(x\right)\frac{d\phi }{dx}\right]-C\left(x\right)\left(\frac{dy}{dx}-\phi \right)=m\left(x\right)$

[0062]where y denotes a flexibility of a beam, φ denotes a rotation angle of a beam, C(x) denotes a shearing rigidity of a beam, B(x) denotes a bending rigidity of a beam, and q(x) and m(x) are both load density functions acting on a beam.

[0044] As shown in FIG. 1, the impulse function for the load density functions acting on a beam can be expressed as follows:

[00019]$q\left(x\right)=p_1{.Math.x-\frac{l}{2}.Math.}^{-1}-\frac{p_1}{2}\left({.Math.x-0.Math.}^{-1}+{.Math.x-l.Math.}^{-1}\right)$

[0065]

[00020]$m\left(x\right)=0$

[0045] Substitute Formula (9) into Formula (7), and integrate Formula (7) to obtain the following:

[00021]$-C\left(x\right)\left(\frac{dy}{dx}-\phi \right)=p_1{.Math.x-\frac{l}{2}.Math.}^0-\frac{p_1}{2}\left({.Math.x-0.Math.}^0+{.Math.x-l.Math.}^0\right)$

[0046] Substitute Formula (11) into Formula (8), and integrate Formula x to obtain the following:

[00022]$B\left(x\right)\frac{d\phi }{dx}=p_1{.Math.x-\frac{1}{2}.Math.}^1-\frac{p_1}{2}\left({.Math.x-0.Math.}^1+{.Math.x-1.Math.}^1\right)$

[0047] Obtain the following rotation angle Formula of the beam member by integrating Formula (12):

[00023]$\begin{array}{l}\phi \left(x\right)={\phi }_0+\left[p_1\frac{{.Math.x-\frac{1}{2}.Math.}^2}{2!}-\frac{p_1}{2}\left(\frac{{.Math.x-0.Math.}^2}{2!}+\frac{{.Math.x-l.Math.}^2}{2!}\right)\right]\left\{\frac{1}{E{I}_{r1}}\left[\begin{array}{l}1+\left(k_2-1\right){.Math.x-\frac{1}{8}.Math.}^0+\left(k_3-k_2\right){.Math.x-\frac{2l}{8}.Math.}^0+\left(k_4-k_3\right){.Math.x-\frac{3l}{8}.Math.}^0+\left(k_5-k_4\right){.Math.x-\frac{4l}{8}.Math.}^0\hfill \\ +\left(k_6-k_5\right){.Math.x-\frac{5l}{8}.Math.}^0+\left(k_7-k_6\right){.Math.x-\frac{6l}{8}.Math.}^0+\left(k_8-k_7\right){.Math.x-\frac{7l}{8}.Math.}^0\hfill \end{array}\right]\right\}\\ -\left\{\begin{array}{l}\left(k_2-1\right)\frac{1}{E{I}_{r1}}\frac{-\frac{p_1}{2}{\left(\frac{l}{8}-0\right)}^2}{2!}{.Math.x-\frac{1}{8}.Math.}^0+\left(k_3-k_2\right)\frac{1}{E{I}_{r1}}\frac{-\frac{p_1}{2}{\left(\frac{2l}{8}-0\right)}^2}{2!}{.Math.x-\frac{2l}{8}.Math.}^0+\left(k_4-k_3\right)\frac{1}{E{L}_{r1}}\frac{-\frac{p_1}{2}{\left(\frac{3l}{8}-0\right)}^2}{2!}{.Math.x-\frac{3l}{8}.Math.}^0\hfill \\ +\left(k_5-k_4\right)\frac{1}{E{I}_{r1}}\frac{-\frac{p_1}{2}{\left(\frac{4l}{8}-0\right)}^2}{2!}{.Math.x-\frac{4l}{8}.Math.}^0+\left(k_6-k_5\right)\frac{1}{E{I}_{r1}}\left[\frac{p_1{.Math.\frac{5l}{8}-\frac{1}{2}.Math.}^2}{2!}-\frac{\frac{p_1}{2}{\left(\frac{5l}{8}-0\right)}^2}{2!}\right]{.Math.x-\frac{5l}{8}.Math.}^0\hfill \\ +\left(k_7-k_6\right)\frac{1}{E{I}_{r1}}\left[\frac{p_1{.Math.\frac{6l}{8}-\frac{l}{2}.Math.}^2}{2!}-\frac{\frac{p_1}{2}{\left(\frac{6l}{8}-0\right)}^2}{2!}\right]{.Math.x-\frac{6l}{8}.Math.}^0+\left(k_8-k_7\right)\frac{1}{E{I}_{r1}}\left[\frac{p_1{.Math.\frac{7l}{8}-\frac{l}{2}.Math.}^2}{2!}-\frac{\frac{p_1}{2}{\left(\frac{7l}{8}-0\right)}^2}{2!}\right]{.Math.x-\frac{7l}{8}.Math.}^0\hfill \end{array}\right\}\end{array}$

[0048] By substituting into Formula (13) the measured rotation angles at the left-ended support and the right-ended support, and at the segments of the beam member, the following formulas can be obtained:

[00024]$\left\{\begin{array}{l}\phi \left(\frac{l}{8}\right)={\theta }_0-\frac{l^2{p}_1}{256E{L}_{r1}}={\theta }_1\hfill \\ \phi \left(\frac{2l}{8}\right)={\theta }_0-\frac{\left(1+3k_2\right)l^2{p}_1}{256E{I}_{r1}}={\theta }_2\hfill \\ \phi \left(\frac{3l}{8}\right)={\theta }_0-\frac{\left(1+3k_2+5k_3\right)l^2{p}_1}{256E{L}_{r1}}={\theta }_3\hfill \\ \phi \left(\frac{4l}{8}\right)={\theta }_0-\frac{\left(1+3k_2+5k_3+7k_4\right)l^2{p}_1}{256E{L}_{r1}}={\theta }_4\hfill \\ \phi \left(\frac{5l}{8}\right)={\theta }_0-\frac{\left(1+3k_2+5k_3+7k_4+7k_5\right)l^2{p}_1}{256E{L}_{r1}}={\theta }_5\hfill \\ \phi \left(\frac{6l}{8}\right)={\theta }_0-\frac{\left(1+3k_2+5k_3+7k_4+7k_5+5k_6\right)l^2{p}_1}{256E{L}_{r1}}={\theta }_6\hfill \\ \phi \left(\frac{7l}{8}\right)={\theta }_0-\frac{\left(1+3k_2+5k_3+7k_4+7k_5+5k_6+3k_7\right)l^2{p}_1}{256E{L}_{r1}}={\theta }_7\hfill \\ \phi \left(l\right)={\theta }_0-\frac{\left(1+3k_2+5k_3+7k_4+7k_5+5k_6+3k_7+k_8\right)l^2{p}_1}{256E{L}_{r1}}={\theta }_8\hfill \end{array}\right)$

[0049] Turn Formula (14) to Formula (15) through equivalent transformation

[00025]$\left\{\begin{array}{l}{\theta }_0-{\theta }_1=\frac{l^2{p}_1}{256E{L}_{r1}}(1)\hfill \\ {\theta }_0-{\theta }_2=\frac{\left(1+3k_2\right)l^2{p}_1}{256E{I}_{r1}}(2)\hfill \\ {\theta }_0-{\theta }_3=\frac{\left(1+3k_2+5k_3\right)l^2{p}_1}{256E{L}_{r1}}(3)\hfill \\ {\theta }_0-{\theta }_4=\frac{\left(1+3k_2+5k_3+7k_4\right)l^2{p}_1}{256E{L}_{r1}}(4)\hfill \\ {\theta }_0-{\theta }_5=\frac{\left(1+3k_2+5k_3+7k_4+7k_5\right)l^2{p}_1}{256E{L}_{r1}}(5)\hfill \\ {\theta }_0-{\theta }_6=\frac{\left(1+3k_2+5k_3+7k_4+7k_5+5k_6\right)l^2{p}_1}{256E{L}_{r1}}(6)\hfill \\ {\theta }_0-{\theta }_7=\frac{\left(1+3k_2+5k_3+7k_4+7k_5+5k_6+3k_7\right)l^2{p}_1}{256E{L}_{r1}}(7)\hfill \\ {\theta }_0-{\theta }_8=\frac{\left(1+3k_2+5k_3+7k_4+7k_5+5k_6+3k_7+k_8\right)l^2{p}_1}{256E{L}_{r1}}(8)\hfill \end{array}\right)$

[0050] As can be seen from Formula (15), each term contains and therefore, k.sub.2 can be solved by division operation, namely dividing Formula II by Formula I. Then obtain k.sub.3 by dividing Formula III by Formula II, and substituting into k.sub.2 solved aforesaid. Solve k.sub.4, k.sub.5, k.sub.6, k.sub.7 and k.sub.8 in sequence in this way, and the final result is shown in the following formula:

[00026]$\left\{\begin{array}{l}{k}_2=\frac{1}{3}\left(\frac{{\theta }_1-{\theta }_2}{{\theta }_0-{\theta }_1}\right);k_3=\frac{1}{5}\left(\frac{{\theta }_2-{\theta }_3}{{\theta }_0-{\theta }_1}\right);k_4=\frac{1}{7}\left(\frac{{\theta }_3-{\theta }_4}{{\theta }_0-{\theta }_1}\right);k_5=\frac{1}{7}\left(\frac{{\theta }_4-{\theta }_5}{{\theta }_0-{\theta }_1}\right);\hfill \\ k_6=\frac{1}{5}\left(\frac{{\theta }_5-{\theta }_6}{{\theta }_0-{\theta }_1}\right);k_7=\frac{1}{3}\left(\frac{{\theta }_6-{\theta }_7}{{\theta }_0-{\theta }_1}\right);k_8=\left(\frac{{\theta }_7-{\theta }_8}{{\theta }_0-{\theta }_1}\right)\hfill \end{array}\right)$

[0051] In the present disclosure, step 5 of the static identification method provided is also carried out in accordance with the above method, except that the rotation angle is extracted according to the finite element model in the damage-free state of the structure, rather than measured in practice. Therefore, by replacing the measured rotation angles in Formula (16) with the extracted values in the finite element model, obtain the ratio of flexural rigidity of each segment with respect to the first segment of structure in the damage-free state, namely, values k.sub.2d, k.sub.3d, k.sub.4d, k.sub.5d, k.sub.6d, k.sub.7d, and k.sub.8d in the theoretical state, as seen in Formula (17).

[00027]$\left\{\begin{array}{l}{k}_{2d}=\frac{1}{3}\left(\frac{{\theta }_{1d}-{\theta }_{2d}}{{\theta }_{0d}-{\theta }_{1d}}\right);k_{3d}=\frac{1}{5}\left(\frac{{\theta }_{2d}-{\theta }_{3d}}{{\theta }_{0d}-{\theta }_{1d}}\right);k_{4d}=\frac{1}{7}\left(\frac{{\theta }_{3d}-{\theta }_{4d}}{{\theta }_{0d}-{\theta }_{1d}}\right);k_{5d}=\frac{1}{7}\left(\frac{{\theta }_{4d}-{\theta }_{5d}}{{\theta }_{0d}-{\theta }_{1d}}\right);\hfill \\ k_{6d}=\frac{1}{5}\left(\frac{{\theta }_{5d}-{\theta }_{6d}}{{\theta }_{0d}-{\theta }_{1d}}\right);k_7=\frac{1}{3}\left(\frac{{\theta }_{6d}-{\theta }_{7d}}{{\theta }_{0d}-{\theta }_{1d}}\right);k_8=\left(\frac{{\theta }_{7d}-{\theta }_{8d}}{{\theta }_{0d}-{\theta }_{1d}}\right)\hfill \end{array}\right)$

[0052] When merely the relative relationship is considered, the flexural rigidity of the first segment is “1”, then the measured flexural rigidity of the second segment of the structure is 1 / k.sub.2, and the flexural rigidity of other segment can be calculated likewise. For the second segment of the structure in a damage-free state, the flexural rigidity is 1 / k.sub.2d, and the flexural rigidity of the other segment can be calculated in a similar way. At this time, the variation of the flexural rigidity of each segment of the structure can be obtained relative to the damage-free state, as given in Formula (18).

[00028]$\left\{\begin{array}{ll}{\Delta }_2=\left(\frac{1}{k_2}-\frac{1}{k_{2d}}\right)/\left(\frac{1}{k_{2d}}\right)\times 100\%;\hfill & {\Delta }_3=\left(\frac{1}{k_3}-\frac{1}{k_{3d}}\right)/\left(\frac{1}{k_{3d}}\right)\times 100\%;\hfill \\ {\Delta }_4=\left(\frac{1}{k_4}-\frac{1}{k_{4d}}\right)/\left(\frac{1}{k_{4d}}\right)\times 100\%;\hfill & {\Delta }_5=\left(\frac{1}{k_5}-\frac{1}{k_{5d}}\right)/\left(\frac{1}{k_{5d}}\right)\times 100\%;\hfill \\ {\Delta }_6=\left(\frac{1}{k_6}-\frac{1}{k_{6d}}\right)/\left(\frac{1}{k_{6d}}\right)\times 100\%;\hfill & {\Delta }_7=\left(\frac{1}{k_7}-\frac{1}{k_{7d}}\right)/\left(\frac{1}{k_{7d}}\right)\times 100\%;\hfill \\ {\Delta }_8=\left(\frac{1}{k_8}-\frac{1}{k_{8d}}\right)/\left(\frac{1}{k_{8d}}\right)\times 100\%\hfill & \hfill \end{array}\right)$

[0053] Then, the relative amount of damage of the flexural rigidity for the first segment is the maximum value of these variations, and the amount of damage of another segment is the difference between the variation of the flexural rigidity of the segment and the maximum value. Since merely the amount of damage is the factor of concern, absolute values are taken, and the final calculation Formula is shown in Formula (19):

[00029]$\left\{\begin{array}{l}{D}_1=\max \left\{{\Delta }_2,{\Delta }_3,{\Delta }_4,{\Delta }_5,{\Delta }_6,{\Delta }_7,{\Delta }_8\right\};\hfill \\ D_2=\left|{\Delta }_2-D_1\right|;D_3=\left|{\Delta }_3-D_1\right|;D_4=\left|{\Delta }_4-D_1\right|;D_5=\left|{\Delta }_5-D_1\right|;\hfill \\ D_6=\left|{\Delta }_6-D_1\right|;D_7=\left|{\Delta }_7-D_1\right|;D_8=\left|{\Delta }_8-D_1\right|\hfill \end{array}\right)$

[0054] The method provided in the present disclosure is described in detail below by taking the simply supported concrete beam structure with a uniform section and the simply supported concrete beam structure with a variable section as embodiments respectively, in combination with the results of finite element numerical analysis.

Embodiment 1: Simply Supported Concrete Beam With a Uniform Section

[0055] A concrete beam with a uniform section has a span of 20 m, a concrete strength grade of C50, a beam height of 1 m and a beam width of 0.8 m. The schematic diagram of the beam structure is shown in FIG. 2, and the finite element numerical model is shown in FIG. 3. Different damage conditions are set, as shown in Table 1.

TABLE-US-00001 Settings for damage conditions of a simply supported beam with a uniform section Damage conditio n Detailed content Concentrated force P applied at midspan Remarks 1 In case where the elastic modulus of C50 is taken, none of the segments are subject to damage. 80 kN Verify the accuracy of the method provided in the present disclosure 2 In case where the elastic modulus is 1.2 times that of C50, none of the segments are subject to damage. 100 kN In engineering practice, the elastic modulus of the new structure is generally greater than a design value 3 In case where the elastic modulus is 1.2 times that of C50, only the first segment is subject to a 10% damage of flexural rigidity 120 kN / 4 In case where the elastic modulus is 1.2 times that of C50, the amounts of damage for the flexural rigidity of the first segment, the third segment, the fifth segment, and the eighth segment are 10%, 5%, 15%, and 5%, respectively. 100 kN / 5 In case where the elastic modulus of C50 is taken, the amounts of damage for the flexural rigidity of the first segment, the second segment, the third segment, the sixth segment, and the seventh segment are 5%, 5%, 5%, 10% and 10%, respectively. 120 kN /

[0056] The calculation process is described in detail by using damage condition 1 as an example, and only the final results are given for other damage conditions. Damage condition 1 indicates no damage and a uniform section, so there is no need to establish a finite element numerical model, and it follows that: k.sub.2d =k.sub.3d =k.sub.4d =k.sub.5d =k.sub.6d =k.sub.7d =k.sub.8d =1. According to FIG. 2 and Table 1, each measured sectional tilt angle under condition 1 is calculated by finite element method, as shown in Table 2.

TABLE-US-00002 Calculation for the tilt angle of a simply supported beam with a uniform section condition 1) No. Tilt angle/ ° 1 θ.sub.0 0.0498 2 θ.sub.1 0.0467 3 θ.sub.2 0.0374 4 θ.sub.3 0.0218 5 θ.sub.4 0 6 θ.sub.5 -0.0218 7 θ.sub.6 -0.0374 8 θ.sub.7 -0.0467 9 θ.sub.8 -0.0498

[0057] Note: The tilt angle is positive in the clockwise direction, and negative in the counterclockwise direction.

[0058] The values of k.sub.2 , k.sub.3, k.sub.4, k.sub.5, k.sub.6, k.sub.7 and k.sub.8 are calculated according to the following formula, and the results are listed in Table 3.

[00030]$\left\{\begin{array}{l}{k}_2=\frac{1}{3}\left(\frac{{\theta }_1-{\theta }_2}{{\theta }_0-{\theta }_1}\right);k_3=\frac{1}{5}\left(\frac{{\theta }_2-{\theta }_3}{{\theta }_0-{\theta }_1}\right);k_4=\frac{1}{7}\left(\frac{{\theta }_3-{\theta }_4}{{\theta }_0-{\theta }_1}\right);k_5=\frac{1}{7}\left(\frac{{\theta }_4-{\theta }_5}{{\theta }_0-{\theta }_1}\right);\hfill \\ k_6=\frac{1}{5}\left(\frac{{\theta }_5-{\theta }_6}{{\theta }_0-{\theta }_1}\right);k_7=\frac{1}{3}\left(\frac{{\theta }_6-{\theta }_7}{{\theta }_0-{\theta }_1}\right);k_8=\left(\frac{{\theta }_7-{\theta }_8}{{\theta }_0-{\theta }_1}\right)\hfill \end{array}\right)$

[0059] The values of Δ.sub.2, Δ.sub.3, Δ.sub.4, Δ.sub.5, Δ.sub.6, Δ.sub.7 and Δ.sub.8 are calculated according to the following formula, and the results are listed in Table 3.

[00031]$\left\{\begin{array}{ll}{\Delta }_2=\left(\frac{1}{k_2}-\frac{1}{k_{2d}}\right)/\left(\frac{1}{k_{2d}}\right)\times 100\%;\hfill & {\Delta }_3=\left(\frac{1}{k_3}-\frac{1}{k_{3d}}\right)/\left(\frac{1}{k_{3d}}\right)\times 100\%;\hfill \\ {\Delta }_4=\left(\frac{1}{k_4}-\frac{1}{k_{4d}}\right)/\left(\frac{1}{k_{4d}}\right)\times 100\%;\hfill & {\Delta }_5=\left(\frac{1}{k_5}-\frac{1}{k_{5d}}\right)/\left(\frac{1}{k_{5d}}\right)\times 100\%;\hfill \\ {\Delta }_6=\left(\frac{1}{k_6}-\frac{1}{k_{6d}}\right)/\left(\frac{1}{k_{6d}}\right)\times 100\%;\hfill & {\Delta }_7=\left(\frac{1}{k_7}-\frac{1}{k_{7d}}\right)/\left(\frac{1}{k_{7d}}\right)\times 100\%;\hfill \\ {\Delta }_8=\left(\frac{1}{k_8}-\frac{1}{k_{8d}}\right)/\left(\frac{1}{k_{8d}}\right)\times 100\%\hfill & \hfill \end{array}\right)$

[0060] The amounts of damage D.sub.1, D.sub.2, D.sub.3, D.sub.4, D.sub.5, D.sub.6, D.sub.7 and D.sub.8 of the first segment, the second segment, the third segment, the fourth segment, the fifth segment, the sixth segment, the seventh segment and the eighth segment are calculated, respectively according to the following formula, and the results are listed in Table 3.

[00032]$\left\{\begin{array}{l}{D}_1=\max \left\{{\Delta }_2,{\Delta }_3,{\Delta }_4,{\Delta }_5,{\Delta }_6,{\Delta }_7,{\Delta }_8\right\};\hfill \\ D_2=\left|{\Delta }_2-D_1\right|;D_3=\left|{\Delta }_3-D_1\right|;D_4=\left|{\Delta }_4-D_1\right|;D_5=\left|{\Delta }_5-D_1\right|;\hfill \\ D_6=\left|{\Delta }_6-D_1\right|;D_7=\left|{\Delta }_7-D_1\right|;D_8=\left|{\Delta }_8-D_1\right|\hfill \end{array}\right)$

TABLE-US-00003 Damage identification for beam with a uniform section (damage condition 1) Reciprocal of flexural rigidity of each segment relative to the first segment Value Variation in flexural rigidity of each segment Value Amount of damage in flexural rigidity of each segment Value / / / / D.sub.1 0 k.sub.2 1 Δ.sub.2 0 D.sub.2 0 k.sub.3 1.006452 Δ.sub.3 -0.64% D.sub.3 0.64% k.sub.4 1.004608 Δ.sub.4 -0.46% D.sub.4 0.46% k.sub.5 1.004608 Δ.sub.5 -0.46% D.sub.5 0.46% k.sub.6 1.006452 Δ.sub.6 -0.64% D.sub.6 0.64% k.sub.7 1 Δ.sub.7 0 D.sub.7 0 k.sub.8 1 Δ.sub.8 0 D.sub.8 0

[0061] Note: Under damage condition 1, the elastic modulus of C50 is set, and none of the segments are subject to damage.

[0062] As shown in Table 3, the amount of damage in flexural rigidity of each segment is close to 0, and has a maximum value of 0.64%, which is consistent with the assumption that there is no damage in damage condition 1, indicating that the method provided in the present disclosure is accurate and feasible, and is high in damage identification accuracy. According to the above method, the calculation results of damage identification for each beam under damage condition 2 to damage condition 5 are listed in Table 4 to Table 7, respectively.

TABLE-US-00004 Damage identification for simply supported beam with a uniform section (damage condition 2) Reciprocal of flexural rigidity of each segment relative to the first segment Value Variation in flexural rigidity of each segment Value Amount of damage in flexural rigidity of each segment Value / / / / D.sub.1 2.06% k.sub.2 0.979798 Δ.sub.2 2.06% D.sub.2 0 k.sub.3 0.981818 Δ.sub.3 1.85% D.sub.3 0.21% k.sub.4 0.982684 Δ.sub.4 1.76% D.sub.4 0.30% k.sub.5 0.982684 Δ.sub.5 1.76% D.sub.5 0.30% k.sub.6 0.981818 Δ.sub.6 1.85% D.sub.6 0.21% k.sub.7 0.979798 Δ.sub.7 2.06% D.sub.7 0 k.sub.8 1 Δ.sub.8 0 D.sub.8 2.06%

[0063] Note: Under damage condition 2, the elastic modulus is 1.2 times that of C50, and none of the segments are subject to damage.

TABLE-US-00005 Damage identification for a beam with a uniform section (damage condition 3) Reciprocal of flexural rigidity of each segment relative to the first segment Value Variation in flexural rigidity of each segment Value Amount of damage in flexural rigidity of each segment Value / / / / D.sub.1 13.79% k.sub.2 0.878788 Δ.sub.2 13.79% D.sub.2 0 k.sub.3 0.886364 Δ.sub.3 12.82% D.sub.3 0.97% k.sub.4 0.886364 Δ.sub.4 12.82% D.sub.4 0.97% k.sub.5 0.883117 Δ.sub.5 13.24% D.sub.5 0.56% k.sub.6 0.886364 Δ.sub.6 12.82% D.sub.6 0.97% k.sub.7 0.878788 Δ.sub.7 13.79% D.sub.7 0 k.sub.8 0.886364 Δ.sub.8 12.82% D.sub.8 0.97%

[0064] Note: Under damage condition 3, the elastic modulus is 1.2 times that of C50, and only the first segment is subject to a 10% damage of flexural rigidity.

TABLE-US-00006 Damage identification for a beam with a uniform section (damage condition 4) Reciprocal of flexural rigidity of each segment relative to the first segment Value Variation in flexural rigidity of each segment Value Amount of damage in flexural rigidity of each segment Value / / / / D.sub.1 11.34% k.sub.2 0.898148 Δ.sub.2 11.34% D.sub.2 0.00% k.sub.3 0.95 Δ.sub.3 5.26% D.sub.3 6.08% k.sub.4 0.900794 Δ.sub.4 11.01% D.sub.4 0.33% k.sub.5 1.059524 Δ.sub.5 -5.62% D.sub.5 16.96% k.sub.6 0.9 Δ.sub.6 11.11% D.sub.6 0.23% k.sub.7 0.907407 Δ.sub.7 10.20% D.sub.7 1.14% k.sub.8 0.944444 Δ.sub.8 5.88% D.sub.8 5.46%

[0065] Note: Under damage condition 4, the elastic modulus is 1.2 times that of C50, and the amounts of damage for the flexural rigidity of the first segment, the third segment, the fifth segment, and the eighth segment are 10%, 5%, 15%, and 5%, respectively.

TABLE-US-00007 Damage identification for a beam with a uniform section (damage condition 5) Reciprocal of flexural rigidity of each segment relative to the first segment Value Variation in flexural rigidity of each segment Value Amount of damage in flexural rigidity of each segment Value / / / / D.sub.1 4.89% k.sub.2 1 Δ.sub.2 0.00% D.sub.2 4.89% k.sub.3 1.004082 Δ.sub.3 -0.41% D.sub.3 5.30% k.sub.4 0.953353 Δ.sub.4 4.89% D.sub.4 0 k.sub.5 0.953353 Δ.sub.5 4.89% D.sub.5 0 k.sub.6 1.061224 Δ.sub.6 -5.77% D.sub.6 10.66% k.sub.7 1.054422 Δ.sub.7 -5.16% D.sub.7 10.05% k.sub.8 0.959184 Δ.sub.8 4.26% D.sub.8 0.64%

[0066] Note: Under condition 5, the elastic modulus of C50 is set, and the amounts of damage for the flexural rigidity of the first segment, the second segment, the third segment, the sixth segment, and the seventh segment are 5%, 5%, 5%, 10% and 10%, respectively.

[0067] As can be seen from Table 4 to Table 7, the amounts of damage identified according to the method of the present disclosure are basically the same as those set in advance under various damage conditions. Thus, under the condition of guaranteeing the measurement accuracy of the tilt angle, damage location and evaluation on amounts of damage for damage to a simply supported beam can be conducted by adopting the method of the present disclosure.

Embodiment 2: Simply Supported Concrete Beam With a Variable Section

[0068] A concrete beam with a variable section has a span of 20 m and a concrete strength grade of C50, and a rectangular section is adopted. From the left-ended section, the beam has a height of 0.5 m and a width of 0.4 m; while from the right-ended section, the beam has a height of 1 m and a width of 0.8 m; and the left-ended section changes linearly to the right-ended section, and at this time, the structural diagram is shown in FIG. 4. Different damage conditions are manually set, as listed in Table 8.

TABLE-US-00008 Settings for damage conditions of a simply supported beam with a variable section Damage condition Detailed content Concentrated force P applied at midspan 1 In case where the elastic modulus is 1.2 times that of C50, only the first segment is subject to a 10% damage of flexural rigidity 80 kN 2 In case where the elastic modulus is 1.2 times that of C50, the amounts of damage for the flexural rigidity of the first segment, the third segment, the fifth segment, and the eighth segment are 10%, 5%, 15%, and 5%, respectively. 180 kN 3 In case where the elastic modulus of C50 is taken, the amounts of damage for the flexural rigidity of the first segment, the second segment, the third segment, the sixth segment, and the seventh segment are 5%, 5%, 5%, 10% and 10%, respectively. 80 kN

[0069] The calculation process is described in detail by using damage condition 1 as an example, and only the final results are given for other conditions. Under damage condition 1, in the simply supported beam with a variable section, only the first segment is subject to a 10% damage of flexural rigidity. For this reason, it is required to first establish a finite element numerical model of the structure in a damage-free state. The finite element numerical model diagram is shown in FIG. 5, and the tilt angle of the ⅛ section of the structure is extracted, and based on the extracted tilt angle, values of k.sub.2d, k.sub.3d, k.sub.4d, k.sub.5d, k.sub.6d, k.sub.7d and k.sub.8d are calculated according to the following formula in the invention. The calculated results and tilt angles are shown in Table 9:

[00033]$\left\{\begin{array}{l}{k}_{2d}=\frac{1}{3}\left(\frac{{\theta }_{1d}-{\theta }_{2d}}{{\theta }_{0d}-{\theta }_{1d}}\right);k_{3d}=\frac{1}{5}\left(\frac{{\theta }_{2d}-{\theta }_{3d}}{{\theta }_{0d}-{\theta }_{1d}}\right);k_{4d}=\frac{1}{7}\left(\frac{{\theta }_{3d}-{\theta }_{4d}}{{\theta }_{0d}-{\theta }_{1d}}\right);k_{5d}=\frac{1}{7}\left(\frac{{\theta }_{4d}-{\theta }_{5d}}{{\theta }_{0d}-{\theta }_{1d}}\right);\hfill \\ k_{6d}=\frac{1}{5}\left(\frac{{\theta }_{5d}-{\theta }_{6d}}{{\theta }_{0d}-{\theta }_{1d}}\right);k_7=\frac{1}{3}\left(\frac{{\theta }_{6d}-{\theta }_{7d}}{{\theta }_{0d}-{\theta }_{1d}}\right);k_8=\left(\frac{{\theta }_{7d}-{\theta }_{8d}}{{\theta }_{0d}-{\theta }_{1d}}\right)\hfill \end{array}\right)$

TABLE-US-00009 Calculation for the tilt angle of a simply supported beam structure with a variable section under a damage-free state No. tilt angle/ ° Reciprocal of flexural rigidity of each of the second segment, the third segment, the fourth segment, the fifth segment, the sixth segment, the seventh segment and the eighth segment with respect to the first segment 1 θ.sub.0d 0.2359 / / 2 θ.sub.1d 0.1995 k.sub.2d 0.677655677655678 3 θ.sub.2d 0.1255 k.sub.3d 0.458791208791209 4 θ.sub.3d 0.042 k.sub.4d 0.319858712715856 5 θ.sub.4d -0.0395 k.sub.5d 0.232731554160126 6 θ.sub.5d -0.0988 k.sub.6d 0.170879120879121 7 θ.sub.6d -0.1299 k.sub.7d 0.129120879120879 8 θ.sub.7d -0.144 k.sub.8d 0.104395604395604 9 θ.sub.8d -0.1478 / /

[0070] Note: The tilt angle is positive in the clockwise direction, and negative in the counterclockwise direction.

[0071] In order to obtain the tilt angle of ⅛ section of the beam with a variable section under damage condition 1, the finite element numerical model of the structure is established (the elastic modulus of concrete is 1.2 times that of C50, and only the first segment is subject to a 10% damage of flexural rigidity). The measured sectional tilt angle at this time is extracted, and the extraction results are given in Table 10.

TABLE-US-00010 Calculation for measured sectional tilt angles of a simply supported beam structure with a variable section (damage condition 1) No. Tilt angle/ ° 1 θ.sub.0 0.3995 2 θ.sub.1 0.332 3 θ.sub.2 0.2086 4 θ.sub.3 0.0694 5 θ.sub.4 -0.0664 6 θ.sub.5 -0.1652 7 θ.sub.6 -0.2171 8 θ.sub.7 -0.2406 9 θ.sub.8 -0.2468

[0072] Note: The tilt angle is positive in the clockwise direction, and negative in the counterclockwise direction.

[0073] From the measured sectional tilt angles described above, the values of k.sub.2, k.sub.3, k.sub.4, k.sub.5, k.sub.6, k.sub.7 and k.sub.8 are calculated according to the following formula in the present disclosure, and the calculation results are given in Table 11:

[00034]$\left\{\begin{array}{l}{k}_2=\frac{1}{3}\left(\frac{{\theta }_1-{\theta }_2}{{\theta }_0-{\theta }_1}\right);k_3=\frac{1}{5}\left(\frac{{\theta }_2-{\theta }_3}{{\theta }_0-{\theta }_1}\right);k_4=\frac{1}{7}\left(\frac{{\theta }_3-{\theta }_4}{{\theta }_0-{\theta }_1}\right);k_5=\frac{1}{7}\left(\frac{{\theta }_4-{\theta }_5}{{\theta }_0-{\theta }_1}\right);\hfill \\ k_6=\frac{1}{5}\left(\frac{{\theta }_5-{\theta }_6}{{\theta }_0-{\theta }_1}\right);k_7=\frac{1}{3}\left(\frac{{\theta }_6-{\theta }_7}{{\theta }_0-{\theta }_1}\right);k_8=\left(\frac{{\theta }_7-{\theta }_8}{{\theta }_0-{\theta }_1}\right)\hfill \end{array}\right)$

[0074] Based on the obtained values k.sub.2, k.sub.3, k.sub.4, k.sub.5, k.sub.6, k.sub.7 and k.sub.8, the values of Δ.sub.2, Δ.sub.3, Δ.sub.4, Δ.sub.5, Δ.sub.6, Δ.sub.7 and Δ.sub.8 are calculated according to the following formula in the present disclosure, and the calculation results are given in Table 11:

[00035]$\left\{\begin{array}{ll}{\Delta }_2=\left(\frac{1}{k_2}-\frac{1}{k_{2d}}\right)/\left(\frac{1}{k_{2d}}\right)\times 100\%;\hfill & {\Delta }_3=\left(\frac{1}{k_3}-\frac{1}{k_{3d}}\right)/\left(\frac{1}{k_{3d}}\right)\times 100\%;\hfill \\ {\Delta }_4=\left(\frac{1}{k_4}-\frac{1}{k_{4d}}\right)/\left(\frac{1}{k_{4d}}\right)\times 100\%;\hfill & {\Delta }_5=\left(\frac{1}{k_5}-\frac{1}{k_{5d}}\right)/\left(\frac{1}{k_{5d}}\right)\times 100\%;\hfill \\ {\Delta }_6=\left(\frac{1}{k_6}-\frac{1}{k_{6d}}\right)/\left(\frac{1}{k_{6d}}\right)\times 100\%;\hfill & {\Delta }_7=\left(\frac{1}{k_7}-\frac{1}{k_{7d}}\right)/\left(\frac{1}{k_{7d}}\right)\times 100\%;\hfill \\ {\Delta }_8=\left(\frac{1}{k_8}-\frac{1}{k_{8d}}\right)/\left(\frac{1}{k_{8d}}\right)\times 100\%\hfill & \hfill \end{array}\right)$

[0075] Based on the obtained values Δ.sub.2, Δ.sub.3, Δ.sub.4, Δ.sub.5, Δ.sub.6, Δ.sub.7 and Δ.sub.8, the amounts of damage D.sub.1, D.sub.2, D.sub.3, D.sub.4, D.sub.5, D.sub.6, D.sub.7 and D.sub.8 of the first segment, the second segment, the third segment, the fourth segment, the fifth segment, the sixth segment, the seventh segment and the eighth segment are calculated, respectively according to the following formula, and the calculation results are given in Table 3.

[00036]$\left\{\begin{array}{l}{D}_1=\max \left\{{\Delta }_2,{\Delta }_3,{\Delta }_4,{\Delta }_5,{\Delta }_6,{\Delta }_7,{\Delta }_8\right\};\hfill \\ D_2=\left|{\Delta }_2-D_1\right|;D_3=\left|{\Delta }_3-D_1\right|;D_4=\left|{\Delta }_4-D_1\right|;D_5=\left|{\Delta }_5-D_1\right|;\hfill \\ D_6=\left|{\Delta }_6-D_1\right|;D_7=\left|{\Delta }_7-D_1\right|;D_8=\left|{\Delta }_8-D_1\right|\hfill \end{array}\right)$

TABLE-US-00011 Damage identification for a beam with a variable section (damage condition 1) Reciprocal of flexural rigidity of each segment relative to the first segment Value Variation in flexural rigidity of each segment Value Amount of damage in flexural rigidity of each segment Value / / / / D.sub.1 13.66% k.sub.2 0.609382716049383 Δ.sub.2 11.20% D.sub.2 2.45% k.sub.3 0.412444444444444 Δ.sub.3 11.24% D.sub.3 2.42% k.sub.4 0.287407407407407 Δ.sub.4 11.29% D.sub.4 2.37% k.sub.5 0.209100529100529 Δ.sub.5 11.30% D.sub.5 2.36% k.sub.6 0.153777777777778 Δ.sub.6 11.12% D.sub.6 2.54% k.sub.7 0.116049382716049 Δ.sub.7 11.26% D.sub.7 2.39% k.sub.8 0.091851851851852 Δ.sub.8 13.66% D.sub.8 0

[0076] Note: Under damage condition 1, the elastic modulus is 1.2 times that of C50, and only the first segment is subject to a 10% damage of flexural rigidity.

[0077] As can be seen from Table 11, by adoption of the method, it is determined that the first segment is subject to a 13.66% damage of flexural rigidity, which is 3.66% greater than 10% damage set in advance for the present condition, and this error is within an acceptable scope. The error is mainly caused by the measurement accuracy of tilt angles. According to the above method, the calculation results of damage identification for each beam under damage condition 2 and damage condition 3 are given in Table 12 and Table 13, respectively.

TABLE-US-00012 Damage identification for a beam with a variable section (damage condition 2) Reciprocal of flexural rigidity of each segment relative to the first segment Value Variation in flexural rigidity of each segment Value Amount of damage in flexural rigidity of each segment Value / / / / D.sub.1 11.37% k.sub.2 0.609574000878349 Δ.sub.2 11.17% D.sub.2 0.20% k.sub.3 0.434255599472991 Δ.sub.3 5.65% D.sub.3 5.72% k.sub.4 0.287596461509505 Δ.sub.4 11.22% D.sub.4 0.15% k.sub.5 0.246188594014681 Δ.sub.5 -5.47% D.sub.5 16.83% \k.sub.6 0.153886693017128 Δ.sub.6 11.04% D.sub.6 0.32% k.sub.7 0.115942028985507 Δ.sub.7 11.37% D.sub.7 0 k.sub.8 0.097496706192358 Δ.sub.8 7.08% D.sub.8 4.29%

[0078] Note: Under damage condition 2, the elastic modulus is 1.2 times that of C50, the amounts of damage for the flexural rigidity of the first segment, the third segment, the fifth segment, and the eighth segment are 10%, 5%, 15%, and 5%, respectively.

TABLE-US-00013 Damage identification for a beam with a uniform section (damage condition 3) Reciprocal of flexural rigidity of each segment relative to the first segment Value Variation in flexural rigidity of each segment Value Amount of damage in flexural rigidity of each segment Value / / / / D.sub.1 8.06% k.sub.2 0.678851174934726 Δ.sub.2 -0.18% D.sub.2 8.24% k.sub.3 0.459007832898172 Δ.sub.3 -0.05% D.sub.3 8.11% k.sub.4 0.303618052965311 Δ.sub.4 5.35% D.sub.4 2.71% [k.sub.5 0.221186124580380 Δ.sub.5 5.22% D.sub.5 2.84% k.sub.6 0.180678851174935 Δ.sub.6 -5.42% D.sub.6 13.49% k.sub.7 0.136640557006092 Δ.sub.7 -5.50% D.sub.7 13.57% k.sub.8 0.096605744125326 Δ.sub.8 8.06% D.sub.8 0

[0079] Note: Under condition 3, the elastic modulus of C50 is set, and the amounts of damage for the flexural rigidity of the first segment, the second segment, the third segment, the sixth segment, and the seventh segment are 5%, 5%, 5%, 10% and 10%,

[0080] As can be seen from Table 12 and Table 13, the method provided in the present disclosure has high precision in identifying the damage to a damaged simply supported beam with a variable section, and the maximum error between the amount of damage identified and the preset amount of damage is 3.57%, which is within the acceptable range of engineering error. This proves the accuracy and feasibility of the method provided in the present disclosure.

[0081] It should be noted that in the method of the present disclosure, the relative relationship of flexural rigidities between the segments is made use of (thereby shielding the load effect), and the relative amount of damage of each segment is obtained. As results obtained are not the absolute values of the flexural rigidities, it is impossible to determine the bearing capacity of the whole structure directly according to the results in the present disclosure. However, it is feasible to conduct damage location and evaluation on the relative amount of damage of each segment according to the results in the present disclosure.

[0082] According to the idea of the present disclosure, the applied load can be changed randomly according to the actual situation (that is, it is possible to apply a load of any form, such as uniformly distributed force, trapezoidal load, bending moment, etc.), and the number of rotations for rotation angle measurement can also be added, that is, the number of segments of the beam structure can also be increased (the more segments are, the more accurate the damage location is). Hence, it is feasible to carry out static identification of damage to a simply supported beam under an uncertain load based on the method of the present disclosure. The present disclosure is only one of the common cases, and any change based on the method of the present disclosure shall fall within the protection scope of the present disclosure.