Shield tunnel aerodynamic effect stress field response characteristic calculation method and device

Abstract

The invention provides a shield tunnel aerodynamic effect stress field response characteristic calculation method and device, and relates to the technical field of shield tunnels, and the method comprises the steps: obtaining a plurality of stress value data of a plurality of longitudinal sections of a tunnel; respectively calculating to obtain an average value of each section; respectively calculating to obtain a first correction coefficient set and a second correction coefficient set of each section; respectively constructing a circumferential stress characteristic model of the aerodynamic effect of each section; fitting the circumferential stress characteristic models of the plurality of sections to obtain a full-tunnel stress characteristic model; and the angle and the longitudinal distance of the to-be-measured point location are substituted into the full tunnel stress characteristic model, and the stress value and the acceleration value of the aerodynamic effect of the to-be-measured point location are calculated respectively. According to the method, the stress value and the acceleration value, generated by the aerodynamic effect, of each point position of the whole tunnel can be obtained only by arranging a limited number of monitoring devices to the multiple sections of the tunnel, and the arrangement number of the monitoring devices of the tunnel is reduced.

Description

Technical Field

[0001] This invention relates to the field of shield tunnel technology, and more specifically, to a method and apparatus for calculating the aerodynamic stress field response characteristics of shield tunnels. Background Technology

[0002] During the construction and operation of shield tunnels, the stress state of the tunnel directly affects the stability and safety of the structure, while the acceleration value reflects the dynamic response of the tunnel under external loads (such as earthquakes, train vibrations, etc.). In existing technologies, obtaining the stress and acceleration values ​​at a specific point in the shield tunnel requires the installation of a corresponding monitoring device at that point. Obtaining stress and acceleration values ​​at multiple points requires a corresponding number of monitoring devices. This results in a large demand for monitoring devices and makes it impossible to obtain stress and acceleration values ​​at every point in the entire tunnel (as monitoring devices cannot be fully deployed). Summary of the Invention

[0003] The purpose of this invention is to provide a method and apparatus for calculating the aerodynamic stress field response characteristics of shield tunnels, thereby improving the aforementioned problems. To achieve the above objective, the technical solution adopted by this invention is as follows:

[0004] In a first aspect, this application provides a method for calculating the stress field response characteristics of aerodynamic effects in a shield tunnel, comprising: acquiring multiple stress value data of multiple longitudinal sections of the tunnel, wherein the multiple sections are distributed at intervals along the longitudinal direction of the tunnel, and the multiple stress value data of each section are data acquired by multiple monitoring devices arranged at circumferential intervals on that section; calculating the average value of each section based on the multiple stress value data of each section; calculating a first set of correction coefficients and a second set of correction coefficients for the multiple stress value data of each section in the horizontal and vertical directions, respectively, based on the multiple stress value data of each section; constructing a circumferential stress characteristic model of aerodynamic effects for each section based on the average value, the first set of correction coefficients and the second set of correction coefficients; fitting the circumferential stress characteristic model of aerodynamic effects of multiple sections to obtain a full tunnel stress characteristic model; and inputting the angle and longitudinal distance of the test point into the full tunnel stress characteristic model, and calculating the stress value and acceleration value of the aerodynamic effect at the test point.

[0005] Secondly, this application provides a device for calculating the aerodynamic stress field response characteristics of a shield tunnel, comprising: a data acquisition module for acquiring multiple stress value data of multiple longitudinal sections of the tunnel, wherein the multiple sections are distributed at intervals along the longitudinal direction of the tunnel, and the multiple stress value data of each section are data acquired by multiple monitoring devices arranged at circumferential intervals around the section; a first calculation module for calculating the average value of each section based on the multiple stress value data of each section; and a second calculation module for calculating the number of stress values ​​of each section based on the multiple stress value data of each section. The system is based on a first set of correction coefficients and a second set of correction coefficients in the horizontal and vertical directions, respectively. A first model building module is used to construct a circumferential stress characteristic model of the aerodynamic effect for each cross-section based on the average value of each cross-section, the first set of correction coefficients, and the second set of correction coefficients, respectively. A second model building module is used to fit the circumferential stress characteristic models of the aerodynamic effect of multiple cross-sections to obtain a full tunnel stress characteristic model. A data processing module is used to input the angle and longitudinal distance of the test point into the full tunnel stress characteristic model and calculate the stress value and acceleration value of the aerodynamic effect at the test point, respectively.

[0006] Thirdly, this application provides a device for calculating the aerodynamic stress field response characteristics of a shield tunnel, comprising: a memory for storing a computer program; and a processor for executing the computer program to implement the steps of the method for calculating the aerodynamic stress field response characteristics of a shield tunnel as described in the first aspect.

[0007] Fourthly, this application provides a readable storage medium storing a computer program, which, when executed by a processor, implements the steps of the method for calculating the aerodynamic stress field response characteristics of a shield tunnel as described in the first aspect.

[0008] The beneficial effects of this invention are as follows:

[0009] This invention only requires a limited number of monitoring devices to be deployed to multiple sections of the tunnel to obtain the stress and acceleration values ​​of the entire tunnel at each point due to aerodynamic effects. It also reduces the number of monitoring devices required for the tunnel, thereby reducing the cost of obtaining the aerodynamic stress field response characteristics of shield tunnels.

[0010] Other features and advantages of the invention will be set forth in the following description, and will be apparent in part from the description, or may be learned by practicing embodiments of the invention. The objects and other advantages of the invention may be realized and obtained by means of the structures particularly pointed out in the written description, claims, and drawings. Attached Figure Description

[0011] To more clearly illustrate the technical solutions of the embodiments of the present invention, the accompanying drawings used in the embodiments will be briefly introduced below. It should be understood that the following drawings only show some embodiments of the present invention and should not be regarded as a limitation on the scope. For those skilled in the art, other related drawings can be obtained based on these drawings without creative effort.

[0012] Figure 1 A schematic diagram illustrating the calculation method for the stress field response characteristics of shield tunnels under aerodynamic effects;

[0013] Figure 2 A schematic diagram showing the coordination of a shield tunnel model, a train launching device, and a train recovery device;

[0014] Figure 3 This is a schematic diagram of a shield tunnel model;

[0015] Figure 4 This is a schematic diagram of a cross-section of a shield tunnel model;

[0016] Figure 5 This is a side view of a shield tunnel model;

[0017] Figure 6 A schematic diagram of a device for calculating the stress field response characteristics of aerodynamic effects in shield tunnels.

[0018] The diagram is labeled as follows: 1. Train model; 11. Plaster section; 12. Glass section; 13. Base; 14. Track; 15. Cross-section; 21. Air compressor; 22. Air cannon; 23. Acceleration pipe; 31. Buffer roller; 32. Protective box; 33. Recycling net; 34. Anti-collision pad; 41. Strain gauge; 42. Wind speed sensor; 43. Pressure sensor; 44. Accelerometer; 800. Equipment for calculating the aerodynamic stress field response characteristics of shield tunnels; 801. Processor; 802. Memory; 803. Multimedia component; 804. I / O interface; 805. Communication component. Detailed Implementation

[0019] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of the present invention. The components of the embodiments of the present invention described and shown in the accompanying drawings can generally be arranged and designed in various different configurations. Therefore, the following detailed description of the embodiments of the present invention provided in the accompanying drawings is not intended to limit the scope of the claimed invention, but merely to illustrate selected embodiments of the invention. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without inventive effort are within the scope of protection of the present invention.

[0020] It should be noted that similar reference numerals and letters in the following figures indicate similar items; therefore, once an item is defined in one figure, it does not need to be further defined and explained in subsequent figures. Furthermore, in the description of this invention, terms such as "first," "second," etc., are used only to distinguish descriptions and should not be construed as indicating or implying relative importance.

[0021] Example 1:

[0022] like Figure 1 As shown in the figure, this embodiment provides a method for calculating the stress field response characteristics of aerodynamic effects in shield tunnels, including:

[0023] S100 acquires multiple stress value data from multiple longitudinal sections of the tunnel. These multiple sections are distributed at intervals along the longitudinal direction of the tunnel, and the multiple stress value data for each section are acquired by multiple monitoring devices that are set at circumferential intervals around that section.

[0024] In some embodiments, multiple cross-sections are selected in the tunnel, and these cross-sections are longitudinal sections of the tunnel. These cross-sections are spaced apart along the longitudinal direction of the tunnel. On each cross-section, multiple monitoring devices are spaced apart circumferentially, and these devices are used to acquire multiple stress value data points on that cross-section. For example, a cross-section is selected at regular intervals along the longitudinal direction of the tunnel, and several stress monitoring sensors are evenly arranged on the circumference of each cross-section to obtain multiple stress value data points for each cross-section.

[0025] In other embodiments, the monitoring device may include a stress plate 41, which is attached to and connected to the tunnel. The stress value of the tunnel at that point can be calculated using a formula, which is: It is worth mentioning that the air pressure generated when the train passes through acts on the inner wall of the tunnel concrete, thereby deforming the inner wall of the tunnel concrete, and the stress plate 41 is adapted to follow the deformation of the inner wall of the tunnel concrete.

[0026] in, This represents the stress value of the tunnel at that point. The elastic modulus of the tunnel concrete; The strain of strain gauge 41 can directly reflect the strain of tunnel concrete at that point.

[0027] S200 calculates the average value of each cross section based on multiple stress value data for each cross section.

[0028] In some embodiments, for the multiple stress values ​​obtained for each cross-section, the average stress value of each cross-section is calculated using a formula, which is as follows:

[0029] ;

[0030] in, This is the average value; This refers to the number of monitoring devices installed in this section of the tunnel. In order to be in The cross-section shows stress values ​​acquired by various monitoring devices. , To correspond to the angle of the monitoring device, for example , or .

[0031] S300 is calculated based on multiple stress values ​​for each cross section, with the multiple stress values ​​for each cross section having a first set of correction coefficients and a second set of correction coefficients in the horizontal and vertical directions, respectively.

[0032] In some embodiments, multiple stress value data for each cross-section are analyzed to calculate a first set of correction coefficients in the horizontal direction and a second set of correction coefficients in the vertical direction. The first and second sets of correction coefficients are used to account for the distribution differences and variation patterns of stress values ​​in the horizontal and vertical directions. That is, the first set of correction coefficients can correct the stress value of the measured point in the horizontal direction, and the second set of correction coefficients can correct the stress value of the measured point in the vertical direction.

[0033] S400 constructs a circumferential stress characteristic model of the aerodynamic effect of each cross section based on the average value of each cross section, the first set of correction coefficients, and the second set of correction coefficients.

[0034] Understandably, based on the average value of each cross section, the first set of correction coefficients, and the second set of correction coefficients, a circumferential stress characteristic model of the aerodynamic effect of each cross section is constructed. The circumferential stress characteristic model can describe the circumferential stress characteristics of the aerodynamic effect of that cross section.

[0035] It is worth mentioning that in the circumferential stress characteristic model of the aerodynamic effect of each cross section, the stress value and acceleration value of the aerodynamic effect at the test point can be calculated by inputting the angle of the test point.

[0036] S500 fits the circumferential stress characteristic models of aerodynamic effects at multiple cross-sections to obtain the full tunnel stress characteristic model. The full tunnel stress model is the full tunnel aerodynamic effect stress field response characteristic model.

[0037] In some embodiments, the circumferential stress characteristic models of multiple cross-sectional aerodynamic effects are fitted. Since the tunnel is a continuous structure, there are correlations and variation patterns among the stress characteristics of different cross-sectional aerodynamic effects. Therefore, by fitting the circumferential stress characteristic models of multiple cross-sectional aerodynamic effects, the stress characteristic models of local cross-sectional aerodynamic effects can be extended to the entire tunnel range to obtain the full tunnel stress characteristic model. The full tunnel stress characteristic model can describe the stress characteristics of the aerodynamic effects of the entire tunnel.

[0038] S600 inputs the angle and longitudinal distance of the test point into the full tunnel stress characteristic model and calculates the stress and acceleration values ​​of the aerodynamic effect at the test point.

[0039] In some embodiments, when it is necessary to obtain the stress and acceleration values ​​of the aerodynamic effect at a certain test point in the tunnel, the angle of the test point (the angle between the line connecting the test point and the center of the cross section and the horizontal direction) and the longitudinal distance (the distance between the test point and the tunnel entrance along the longitudinal direction of the tunnel) are substituted into the full tunnel stress characteristic model. Through the calculation of the full tunnel stress characteristic model, the stress and acceleration values ​​of the aerodynamic effect at the test point can be obtained respectively.

[0040] Understandably, each cross-section is first analyzed independently to obtain its average value, first set of correction coefficients, and second set of correction coefficients. Then, based on the average value, first set of correction coefficients, and second set of correction coefficients for each cross-section, a circumferential stress characteristic model of the aerodynamic effect is constructed for each cross-section. Next, based on the continuity and variation law of the tunnel aerodynamic effect stress characteristics in the longitudinal direction, the circumferential stress characteristic models of the aerodynamic effect of multiple cross-sections are fitted into a full tunnel stress characteristic model. Subsequently, only the angle and longitudinal distance of the point to be measured need to be input, and the stress value and acceleration value of the aerodynamic effect at the point to be measured can be calculated through the full tunnel stress characteristic model.

[0041] According to the method for calculating the stress field response characteristics of shield tunnel aerodynamic effects according to the present invention, only a limited number of monitoring devices need to be deployed to multiple sections of the tunnel to obtain the stress and acceleration values ​​of the entire tunnel at each point due to aerodynamic effects, and the number of monitoring devices to be deployed in the tunnel is reduced, thereby reducing the cost of obtaining the stress field response characteristics of shield tunnel aerodynamic effects.

[0042] According to some embodiments of the present invention, the calculation process of the first set of correction coefficients and the second set of correction coefficients includes:

[0043] Determine the number of stress value data for each cross section.

[0044] In some embodiments, for each longitudinal section, the number of monitoring devices arranged at circumferential intervals in that section must first be determined, with each monitoring device used to acquire a stress value data.

[0045] Based on the number of stress value data for each section, a corrected order set is calculated. The corrected order set includes multiple positive integers greater than zero, and the positive integers are less than or equal to half the number of stress value data for each section.

[0046] Understandably, the correction order set is calculated based on the number of stress value data points for each cross-section (the number of monitoring devices installed at circumferential intervals for each cross-section). This correction order set consists of multiple positive integers greater than zero, and all of these positive integers are less than or equal to half the number of stress value data points for each cross-section. For example, if the number of stress value data points for a certain cross-section is 9, then the positive integers in the correction order set are all less than or equal to 4.5. However, since the correction order set is a set of positive integers, the correction order set would be 1, 2, 3, or 4.

[0047] Based on the set of correction orders and multiple stress value data, the first set of correction coefficients and the second set of correction coefficients are calculated respectively.

[0048] In some embodiments, the formula for calculating the first set of correction coefficients is:

[0049] ;

[0050] in, This is the first set of correction coefficients; The number of stress value data, i.e. This refers to the number of monitoring devices installed in this section of the tunnel. In order to be in The cross-section shows stress values ​​acquired by various monitoring devices. To correspond to the angle of the monitoring device, for example , or , This refers to the longitudinal distance between the monitoring device and the tunnel entrance along the tunnel's longitudinal direction. The Fourier fit order ( ).

[0051] The formula for calculating the second set of correction coefficients is:

[0052] ;

[0053] in, For the second set of correction coefficients; The number of stress value data, i.e. This refers to the number of monitoring devices installed in this section of the tunnel. In order to be in The cross-section shows stress values ​​acquired by various monitoring devices. To correspond to the angle of the monitoring device, for example , or , This refers to the longitudinal distance between the monitoring device and the tunnel entrance along the tunnel's longitudinal direction. The Fourier fit order ( ).

[0054] According to some embodiments of the present invention, the process of fitting circumferential stress characteristic models of aerodynamic effects at multiple cross-sections to obtain a full tunnel stress characteristic model includes:

[0055] The first Fourier coefficients at any longitudinal position are obtained by fitting the average value to an exponential function along the longitudinal direction of the tunnel.

[0056] The first and second sets of correction coefficients are fitted with exponential functions along the longitudinal direction of the tunnel, and the second and third Fourier coefficients at any longitudinal position are obtained respectively. When fitting the average value, the first set of correction coefficients and the second set of correction coefficients with exponential functions, the residual value of the function is ignored and the data obtained by the monitoring device is used for calculation.

[0057] In some embodiments, the average values ​​at the same circumferential angle but different longitudinal distances exhibit a smooth attenuation along the tunnel longitudinal direction. Based on the attenuation law of energy propagation, an exponential function is used for fitting, ignoring the residual value of the function. The first Fourier coefficient at any longitudinal position is obtained from the stress response at the monitoring point (data acquired by the monitoring device), as shown in the formula:

[0058] ;

[0059] in, The first Fourier coefficient at any longitudinal position; and for The longitudinal fitting parameters; This is the longitudinal distance between the point to be measured and the tunnel entrance along the tunnel's longitudinal direction. is the base of the natural logarithm.

[0060] In other embodiments, the first and second sets of correction coefficients at the same circumferential angle but different longitudinal distances exhibit a smooth attenuation along the tunnel longitudinal direction. Based on the attenuation law of energy propagation, an exponential function is used for fitting, ignoring the residual value of the function. The second and third Fourier coefficients at any longitudinal position are obtained from the stress response at the monitoring point (data acquired by the monitoring device), as shown in the formula:

[0061] ;

[0062] ;

[0063] in, represents the second Fourier coefficient at any longitudinal position; represents the third Fourier coefficient at any longitudinal position; , and for and The longitudinal fitting parameters; This is the longitudinal distance between the point to be measured and the tunnel entrance along the tunnel's longitudinal direction. The Fourier fit order ( ); is the base of the natural logarithm.

[0064] It is understandable that the first Fourier coefficients at any longitudinal position are obtained by fitting an exponential function to the average value along the tunnel's longitudinal direction, including:

[0065] A logarithmic model is obtained by fitting the average value using the least squares method.

[0066] The longitudinal distance and fitting data of each cross section are obtained separately. The fitting data is one of multiple stress value data for each cross section. The line connecting the monitoring device used to obtain the fitting data for each cross section is parallel to the longitudinal direction of the tunnel.

[0067] By substituting the longitudinal distance of each cross section and the fitted data of each cross section into the logarithmic model, the longitudinal fitting parameters of the average value are calculated.

[0068] The first Fourier coefficients are obtained based on the longitudinal fitting parameters and the average value.

[0069] In some embodiments, the average value of each cross-section is calculated according to the formula for calculating the average value of each cross-section described above. , , …the average values ​​corresponding to each Subsequently, a logarithmic model was obtained by fitting the data using the least squares method. At this time, order , Calculate each cross section , , …corresponding to value.

[0070] Subsequently, based on the linear equation ,get:

[0071] ;

[0072] ;

[0073] The exponent is obtained by inverse calculation based on the results: , .

[0074] Then, , Substitute The first Fourier coefficients are obtained.

[0075] The stress characteristic model of the entire tunnel is obtained based on the first Fourier coefficient, the second Fourier coefficient, and the third Fourier coefficient.

[0076] It is understandable that the full tunnel stress characteristic model includes the full tunnel stress formula and the full tunnel acceleration formula. The full tunnel stress formula is as follows:

[0077] ;

[0078] ;

[0079] ;

[0080] ;

[0081] ;

[0082] ;

[0083] in, The stress value at the point to be measured; The angle of the point to be measured (the angle between the line connecting the point to be measured and the center of the cross section and the horizontal direction); is the base of the natural logarithm; This is the longitudinal distance between the point to be measured and the tunnel entrance along the tunnel's longitudinal direction. The Fourier fit order ( ).

[0084] The formula for acceleration throughout the tunnel is:

[0085] ;

[0086] ;

[0087] ;

[0088] ;

[0089] ;

[0090] in, The acceleration value at the point to be measured; The angle of the point to be measured (the angle between the line connecting the point to be measured and the center of the cross section and the horizontal direction); is the base of the natural logarithm; This is the longitudinal distance between the point to be measured and the tunnel entrance along the tunnel's longitudinal direction. The Fourier fit order ( ).

[0091] In some embodiments, the method for calculating the aerodynamic stress field response characteristics of shield tunnels in this application can be applied to shield tunnels that have already been constructed, or to shield tunnel models.

[0092] like Figures 2-5 As shown, when the aerodynamic stress field response characteristic calculation method for shield tunnels is applied to a shield tunnel model, the shield tunnel model includes five tunnel segments. Three of these segments are constructed from multiple plaster blocks, and two segments are made of glass panels. Their arrangement is: Plaster Segment 11 - Glass Segment 12 - Plaster Segment 11 - Glass Segment 12 - Plaster Segment 11. Plaster Segment 11 simulates different concrete mixes by adjusting the plaster ratio, thus allowing the shield tunnel model to simulate a real shield tunnel. By calculating the stress and acceleration values ​​experienced by Plaster Segment 11 when a train model 1 passes through the shield tunnel model at high speed, the strength of the plaster blocks with that mix ratio in coping with a high-speed train can be evaluated. Therefore, in actual production, concrete blocks of corresponding strength can be used to construct shield tunnels, thereby improving the safety of shield tunnels.

[0093] It should be noted that, due to the differences in aerodynamic effects of the train at the tunnel entrance, tunnel body, and tunnel exit, plaster sections 11 are used in these three sections to monitor the stress field changes in the tunnel in order to study the aerodynamic effects of the entire shield tunnel. Glass sections 12 are arranged between the plaster sections 11 to monitor the speed of the train model 1 and observe changes in the tunnel flow field.

[0094] It is worth mentioning that when using the shield tunnel model, it is also necessary to use a train launching device and a train recovery device. The train launching device and the train recovery device are located at opposite ends of the shield tunnel model, and there is a certain distance between the train launching device and the shield tunnel model.

[0095] The train launching device consists of an air compressor 21, an air cannon 22, and an acceleration pipe 23. The air compressor 21 delivers gas to the air cannon 22 for storage and compression. When the internal pressure of the air cannon 22 reaches the target value, the air cannon 22 releases the compressed gas, thereby propelling the train model 1 in the acceleration pipe 23 to achieve the acceleration process of the train model 1. Subsequently, the train model 1 runs by inertia.

[0096] The shield tunnel model also includes a base 13 and a track 14. The shield tunnel model, the train launching device, and the train recovery device are all connected to the base 13, and the base 13 is equipped with the track 14. One end of the track 14 extends into the acceleration pipe 23, and the other end of the track 14 extends into the train recovery device. The track 14 is used to cooperate with the train model 1. The track 14 can be made of I-beams. The width of the track 14 is determined according to the size of the train model 1 used in the test. The resistance when the track 14 cooperates with the train model 1 is small enough so that the train model 1 can pass through the shield tunnel model at a near-uniform speed.

[0097] The train recovery device consists of a buffer roller 31, a protective box 32, a recovery net 33, and a crash pad 34. The buffer roller 31, a cylindrical piece of elastic polymer foam material, is positioned at the tail end of the track 14. The buffer roller 31 is designed to contact both sides of the train model 1 in the width direction, reducing the speed of the train model 1 through friction. The protective box 32, made of steel, can resist impacts from the train model 1 and control its operating range, ensuring experimental safety. The protective box 32 has an opening facing the shield tunnel model. The recovery net 33 is arranged on the outermost layer of the protective box 32 and on the side closest to the shield tunnel model. That is, the recovery net 33 is set at the open opening. The recovery net 33 flexibly protects the train model 1, controls the derailment direction of the train model 1, and at the same time reduces the speed of the train model 1 again. The anti-collision pad 34 is made of flexible and highly elastic rubber. The anti-collision pad 34 is located between the recovery net 33 and the protective box 32. The anti-collision pad 34 is used to absorb the impact force of the train model 1 hitting the protective box 32 to avoid rigid collision between the train model 1 and the protective box 32.

[0098] It is understood that the monitoring device may include strain gauges 41, acceleration sensors 44, wind speed sensors 42, and pressure sensors 43. When the monitoring device is arranged in the gypsum section 11, the strain gauges 41 are evenly arranged at an angle in the upper half of the tunnel model's travel space; the wind speed sensors 42 are arranged at the arch crown; and the acceleration sensors 44 and pressure sensors 43 are arranged on the arch shoulder and arch crown near the side of the train model 1.

[0099] Of course, the monitoring device may also include an infrared speed monitor. When the monitoring device is arranged in the glass section 12, the wind speed sensor 42 is arranged at the top of the arch, and the acceleration sensor 44 and the pressure sensor 43 are also arranged on the shoulder and top of the arch near the train model 1. The infrared speed monitor is randomly arranged to monitor the speed of the train model 1 when it passes through the glass section 12.

[0100] It is worth mentioning that infrared velocity monitoring devices also need to be installed at the entrance of the shield tunnel model.

[0101] Therefore, the above setup allows for dynamic model tests to be conducted to study the aerodynamic effects of shield tunnels, and also enables monitoring of the changes in the flow field and stress field during the aerodynamic effects of shield tunnels, thus achieving full-process monitoring of the stress state of the shield tunnel structure.

[0102] Example 2:

[0103] This application provides a device for calculating the stress field response characteristics of aerodynamic effects in a shield tunnel, comprising: a data acquisition module for acquiring multiple stress value data of multiple longitudinal sections of the tunnel, wherein the multiple sections are distributed at intervals along the longitudinal direction of the tunnel, and the multiple stress value data of each section are data acquired by multiple monitoring devices arranged at circumferential intervals on that section; a first calculation module for calculating the average value of each section based on the multiple stress value data of each section; a second calculation module for calculating a first set of correction coefficients and a second set of correction coefficients for each section based on the multiple stress value data of each section in the horizontal and vertical directions; a first model construction module for constructing a circumferential stress characteristic model of aerodynamic effects for each section based on the average value, the first set of correction coefficients, and the second set of correction coefficients; a second model construction module for fitting the circumferential stress characteristic models of aerodynamic effects of multiple sections to obtain a full tunnel stress characteristic model; and a data processing module for inputting the angle and longitudinal distance of the test point into the full tunnel stress characteristic model and calculating the stress value and acceleration value of the aerodynamic effect at the test point.

[0104] According to some embodiments of the present invention, the second calculation module includes: a quantity confirmation unit, configured to determine the quantity of stress value data for each cross section; a first calculation unit, configured to calculate a correction order set based on the quantity of stress value data for each cross section, the correction order set including a plurality of positive integers greater than zero, the positive integers being less than or equal to half the quantity of stress value data for each cross section; and a second calculation unit, configured to calculate a first correction coefficient set and a second correction coefficient set based on the correction order set and the plurality of stress value data.

[0105] According to some embodiments of the present invention, the second model construction module includes: a first fitting unit, configured to perform exponential function fitting on the average value along the tunnel longitudinal direction to obtain the first Fourier coefficient at any longitudinal position; a second fitting unit, configured to perform exponential function fitting on the first set of correction coefficients and the second set of correction coefficients along the tunnel longitudinal direction respectively, and obtain the second Fourier coefficient and the third Fourier coefficient at any longitudinal position respectively; wherein when performing exponential function fitting on the average value, the first set of correction coefficients and the second set of correction coefficients respectively, the residual value of the function is ignored and the data obtained by the monitoring device is used for calculation; and a first model construction unit, configured to obtain the full tunnel stress characteristic model based on the first Fourier coefficient, the second Fourier coefficient and the third Fourier coefficient.

[0106] According to some embodiments of the present invention, the first fitting unit includes: a first fitting subunit, used to fit the average value based on the least squares method to obtain a logarithmic model; a data acquisition unit, used to acquire the longitudinal distance of each cross section and the fitting data of each cross section respectively, wherein the fitting data is one of the multiple stress value data of each cross section, and the line connecting the monitoring device used to acquire the fitting data of each cross section is parallel to the longitudinal direction of the tunnel; a third calculation unit, used to input the longitudinal distance of each cross section and the fitting data of each cross section into the logarithmic model to calculate the longitudinal fitting parameter of the average value; and to obtain the first Fourier coefficient based on the longitudinal fitting parameter and the average value.

[0107] Example 3:

[0108] Corresponding to the above method embodiments, this embodiment also provides a device for calculating the aerodynamic stress field response characteristics of a shield tunnel. The device for calculating the aerodynamic stress field response characteristics of a shield tunnel described below can be referred to in correspondence with the method for calculating the aerodynamic stress field response characteristics of a shield tunnel described above.

[0109] Figure 6 This is a block diagram illustrating a shield tunnel aerodynamic stress field response characteristic calculation device 800 according to an exemplary embodiment. Figure 6As shown, the shield tunnel aerodynamic stress field response characteristic calculation device 800 may include: a processor 801 and a memory 802. The shield tunnel aerodynamic stress field response characteristic calculation device 800 may also include one or more of the following: a multimedia component 803, an I / O interface 804, and a communication component 805.

[0110] The processor 801 controls the overall operation of the shield tunnel aerodynamic stress field response characteristic calculation device 800 to complete all or part of the steps in the aforementioned shield tunnel aerodynamic stress field response characteristic calculation method. The memory 802 stores various types of data to support the operation of the shield tunnel aerodynamic stress field response characteristic calculation device 800. This data may include, for example, instructions for any application or method operating on the shield tunnel aerodynamic stress field response characteristic calculation device 800, as well as application-related data, such as contact data, sent and received messages, images, audio, video, etc. The memory 802 can be implemented using any type of volatile or non-volatile storage device or a combination thereof, such as Static Random Access Memory (SRAM), Electrically Erasable Programmable Read-Only Memory (EEPROM), Erasable Programmable Read-Only Memory (EPROM), Programmable Read-Only Memory (PROM), Read-Only Memory (ROM), magnetic storage, flash memory, magnetic disk, or optical disk. The multimedia component 803 may include a screen and an audio component. The screen may be, for example, a touchscreen, and the audio component is used to output and / or input audio signals. For example, the audio component may include a microphone for receiving external audio signals. The received audio signals may be further stored in the memory 802 or transmitted via the communication component 805. The audio component also includes at least one speaker for outputting audio signals. I / O interface 804 provides an interface between processor 801 and other interface modules, such as keyboards, mice, and buttons. These buttons can be virtual or physical. Communication component 805 is used for wired or wireless communication between the shield tunnel aerodynamic stress field response characteristic calculation device 800 and other devices. Wireless communication includes Wi-Fi, Bluetooth, Near Field Communication (NFC), 2G, 3G, or 4G, or a combination thereof. Therefore, the corresponding communication component 805 may include a Wi-Fi module, a Bluetooth module, and an NFC module.

[0111] In an exemplary embodiment, the shield tunnel aerodynamic stress field response characteristic calculation device 800 may be implemented by one or more application-specific integrated circuits (ASICs), digital signal processors (DSPs), digital signal processing devices (DSPDs), programmable logic devices (PLDs), field programmable gate arrays (FPGAs), controllers, microcontrollers, microprocessors, or other electronic components to perform the above-described shield tunnel aerodynamic stress field response characteristic calculation method.

[0112] In another exemplary embodiment, a computer-readable storage medium including program instructions is also provided. When executed by a processor, these program instructions implement the steps of the above-described method for calculating the aerodynamic stress field response characteristics of a tunnel boring machine. For example, the computer-readable storage medium may be the memory 802 including the program instructions, which may be executed by the processor 801 of the tunnel boring machine aerodynamic stress field response characteristic calculation device 800 to complete the above-described method for calculating the aerodynamic stress field response characteristics of a tunnel boring machine.

[0113] Example 4:

[0114] Corresponding to the above method embodiments, this embodiment also provides a readable storage medium. The readable storage medium described below can be referred to in conjunction with the method for calculating the stress field response characteristics of the aerodynamic effect of a shield tunnel described above.

[0115] A readable storage medium storing a computer program, which, when executed by a processor, implements the steps of the method for calculating the stress field response characteristics of the aerodynamic effect of a shield tunnel as described in the above method embodiments.

[0116] The readable storage medium can specifically be a USB flash drive, external hard drive, read-only memory (ROM), random access memory (RAM), magnetic disk, or optical disk, or any other readable storage medium capable of storing program code.

[0117] The above description is merely a preferred embodiment of the present invention and is not intended to limit the invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

[0118] The above description is merely a specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in the present invention should be included within the scope of protection of the present invention. Therefore, the scope of protection of the present invention should be determined by the scope of the claims.

Claims

1. A method for calculating the aerodynamic stress field response characteristics of a shield tunnel, characterized in that, include: Multiple stress value data of multiple longitudinal sections of the tunnel are obtained. The multiple sections are distributed at intervals along the longitudinal direction of the tunnel. The multiple stress value data of each section are data obtained by multiple monitoring devices that are circumferentially spaced at intervals on that section. The average value of each cross section is calculated based on the multiple stress value data of each cross section. The stress values ​​of each section are calculated based on multiple stress value data, and the multiple stress value data of each section are respectively in the first correction coefficient set and the second correction coefficient set in the horizontal direction and the vertical direction. A circumferential stress characteristic model of the aerodynamic effect of each cross section is constructed based on the average value of each cross section, the first set of correction coefficients, and the second set of correction coefficients, respectively. By fitting the circumferential stress characteristic model of aerodynamic effects at multiple cross sections, a stress characteristic model of the entire tunnel is obtained. The angle and longitudinal distance of the test point are substituted into the full tunnel stress characteristic model, and the stress value and acceleration value of the aerodynamic effect of the test point are calculated respectively.

2. The method for calculating the stress field response characteristics of aerodynamic effects in shield tunnels according to claim 1, characterized in that, The calculation process of the first set of correction coefficients and the second set of correction coefficients includes: Determine the number of stress value data for each cross section; Based on the number of stress value data for each section, a set of corrected orders is calculated, which includes a plurality of positive integers greater than zero, wherein the positive integers are less than or equal to half the number of stress value data for each section. Based on the set of correction orders and multiple stress value data, the first set of correction coefficients and the second set of correction coefficients are calculated respectively.

3. The method for calculating the aerodynamic stress field response characteristics of a shield tunnel according to claim 1, characterized in that, The process of fitting the circumferential stress characteristic model of multiple cross-section aerodynamic effects to obtain the stress characteristic model of the entire tunnel includes: The first Fourier coefficients at any longitudinal position are obtained by fitting the average value to an exponential function along the longitudinal direction of the tunnel. The first set of correction coefficients and the second set of correction coefficients are fitted with exponential functions along the longitudinal direction of the tunnel, and the second Fourier coefficients and the third Fourier coefficients at any longitudinal position are obtained respectively; wherein when the average value, the first set of correction coefficients and the second set of correction coefficients are fitted with exponential functions, the residual value of the function is ignored and the data obtained by the monitoring device is used for calculation. The stress characteristic model of the entire tunnel is obtained based on the first Fourier coefficient, the second Fourier coefficient, and the third Fourier coefficient.

4. The method for calculating the aerodynamic stress field response characteristics of a shield tunnel according to claim 3, characterized in that, The process of obtaining the first Fourier coefficients at any longitudinal position by performing an exponential function fit on the average value along the tunnel longitudinal direction includes: A logarithmic model is obtained by fitting the average value using the least squares method. The longitudinal distance and fitting data of each section are obtained respectively. The fitting data is one of the multiple stress value data of each section. The line connecting the monitoring device used to obtain the fitting data of each section is parallel to the longitudinal direction of the tunnel. The longitudinal distance of each cross section and the fitted data of each cross section are substituted into the logarithmic model to calculate the longitudinal fitting parameters of the average value. The first Fourier coefficient is obtained based on the longitudinal fitting parameters and the average value.

5. A device for calculating the aerodynamic stress field response characteristics of a shield tunnel, characterized in that, include: The data acquisition module is used to acquire multiple stress value data of multiple longitudinal sections of the tunnel. The multiple sections are distributed at intervals along the longitudinal direction of the tunnel. The multiple stress value data of each section are acquired by multiple monitoring devices that are circumferentially spaced at intervals on that section. The first calculation module is used to calculate the average value of each cross section based on the multiple stress value data of each cross section; The second calculation module is used to calculate based on the multiple stress value data of each section, wherein the multiple stress value data of each section are respectively in the first correction coefficient set and the second correction coefficient set in the horizontal direction and the vertical direction. The first model construction module is used to construct the circumferential stress characteristic model of the aerodynamic effect of each cross section based on the average value of each cross section, the first set of correction coefficients, and the second set of correction coefficients, respectively. The second model building module is used to fit the circumferential stress characteristic model of multiple cross-section aerodynamic effects to obtain the stress characteristic model of the entire tunnel. The data processing module is used to input the angle and longitudinal distance of the test point into the full tunnel stress characteristic model, and calculate the stress value and acceleration value of the aerodynamic effect of the test point respectively.

6. The device for calculating the stress field response characteristics of aerodynamic effects in shield tunnels according to claim 5, characterized in that, The second calculation module includes: A quantity verification unit is used to determine the quantity of stress value data for each cross section; The first calculation unit calculates a set of corrected orders based on the number of stress value data for each section. The set of corrected orders includes a plurality of positive integers greater than zero, and the positive integers are less than or equal to half the number of stress value data for each section. The second calculation unit is used to calculate the first set of correction coefficients and the second set of correction coefficients based on the set of correction orders and multiple stress value data, respectively.

7. The device for calculating the aerodynamic stress field response characteristics of a shield tunnel according to claim 5, characterized in that, The second model building module includes: The first fitting unit is used to perform exponential function fitting on the average value along the longitudinal direction of the tunnel to obtain the first Fourier coefficient at any longitudinal position. The second fitting unit is used to perform exponential function fitting on the first set of correction coefficients and the second set of correction coefficients along the longitudinal direction of the tunnel, and to obtain the second Fourier coefficient and the third Fourier coefficient at any longitudinal position, respectively; wherein when performing exponential function fitting on the average value, the first set of correction coefficients and the second set of correction coefficients, respectively, the residual value of the function is ignored and the data obtained by the monitoring device is used for calculation. The first model construction unit is used to obtain the stress characteristic model of the entire tunnel based on the first Fourier coefficient, the second Fourier coefficient, and the third Fourier coefficient.

8. The device for calculating the aerodynamic stress field response characteristics of a shield tunnel according to claim 7, characterized in that, The first fitting unit includes: The first fitting subunit is used to fit the average value based on the least squares method to obtain a logarithmic model; The data acquisition unit is used to acquire the longitudinal distance of each cross section and the fitting data of each cross section respectively. The fitting data is one of the multiple stress value data of each cross section. The line connecting the monitoring device for acquiring the fitting data of each cross section is parallel to the longitudinal direction of the tunnel. The third calculation unit is used to input the longitudinal distance of each cross section and the fitted data of each cross section into the logarithmic model to calculate the longitudinal fitting parameters of the average value. The first Fourier coefficient is obtained based on the longitudinal fitting parameters and the average value.

9. A device for calculating the aerodynamic stress field response characteristics of a shield tunnel, characterized in that, include: Memory, used to store computer programs; A processor, configured to execute the computer program to implement the steps of the method for calculating the aerodynamic stress field response characteristics of a shield tunnel as described in any one of claims 1 to 4.

10. A readable storage medium, characterized in that, The readable storage medium stores a computer program that, when executed by a processor, implements the steps of the method for calculating the aerodynamic stress field response characteristics of a shield tunnel as described in any one of claims 1 to 4.

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