Sensor Optimization Arrangement Method Based on Assembly Effective Independence Method

Abstract

The present invention discloses a sensor optimization layout method based on the effective independence method of assembly, which belongs to the field of aerospace structure health monitoring. The present invention determines each stage of on-orbit assembly of aerospace structures and the corresponding assembly structure configuration; determines its target mode according to the force spectrum frequency band range corresponding to the assembly impact load; calculates the corresponding effective independence coefficient; performs weighted summation of the effective independence coefficients of all assembly structure configurations according to the number of target modes to obtain the assembly effective independence coefficient; finally, deletes the sensor candidate point with the smallest coefficient and the row of the point in the modal matrix, and calculates the assembly effective independence coefficient again; until the number of remaining sensor candidate points meets the arrangement requirements of the number of sensors. Based on the characteristics of the change of dynamic parameters of the on-orbit assembly structure in space, the present invention expands the classical effective independence method and gives the comprehensive contribution of each sensor candidate point to the linear independence of the target modal vibration mode of different assembly structure configurations.

Description

Technical Field

[0001] The present invention belongs to the technical field of aerospace structure health monitoring, and in particular relates to a sensor optimization arrangement method based on an assembly effective independence method, which is used for optimizing the arrangement of sensors of an on-orbit assembly structure in space. Background Art

[0002] With the development of aerospace technology and the needs of space missions, the size of spacecraft is constantly developing towards large-scale; the application demand for large-scale space structures with a size of hundreds of meters or even kilometers is becoming increasingly strong, and the application prospects are very broad. Restricted by the rocket's carrying capacity and envelope size, decomposing the entire structure into several modules on the ground, launching it into orbit multiple times, and assembling it on orbit has become the most promising way to build large space structures. Compared with the traditional manufacturing model, the new model of "modular design and manufacturing-on-orbit assembly" is more suitable for the construction of large and super-large aerospace structures. In modular design, sensors and actuators are usually designed in multiple assembly modules. During the on-orbit assembly stage, the aerospace structure continues to increase in size and change in configuration due to the assembly process, and the structure will be subject to impact loads during the assembly process. Therefore, it is necessary to monitor the structural health of the space structure at each assembly stage and obtain its dynamic parameter information to ensure the service safety of the structure.

[0003] Large structures have many degrees of freedom, and it is unrealistic to measure the information of each degree of freedom. Therefore, the optimal arrangement of a limited number of sensors is the first step in health monitoring of the structure, which directly determines the accuracy of monitoring. At present, many scholars have proposed various sensor optimization arrangements, such as the effective independence method, the modal kinetic energy method, the modal strain energy method, the sensor optimization arrangement method based on information entropy, the modal confidence criterion method, etc. These methods are all oriented to a complete structure, and do not take into account the large deformation of the structure in the subsequent service stage.

[0004] On-orbit space structures have the characteristics of on-orbit assembly. After each assembly, the structure size and configuration will change, and the dynamic fingerprint parameters will also change. The traditional sensor optimization layout method cannot guarantee that the structure has the best sensor layout at each stage of assembly. Therefore, it is necessary to develop sensor layout optimization methods for space assembly structures to meet the needs of accurate identification of dynamic fingerprint parameters in the on-orbit assembly process of space structures. Summary of the invention

[0005] In view of the above-mentioned deficiencies in the prior art, an object of the present invention is to provide a sensor optimization layout method based on the assembly effective independence method, so as to solve the problem that the existing sensor layout optimization method cannot perform effective sensor optimization layout for the on-orbit assembly structure.

[0006] To achieve the above object, the technical solution adopted by the present invention is as follows:

[0007] The present invention provides a sensor optimization arrangement method based on an assembly effective independent method, comprising the following steps:

[0008] 1) Determine the on-orbit assembly process of the space structure and the assembly structure configuration corresponding to each assembly stage, and establish a finite element model for all assembly structure configurations;

[0009] 2) Determine the assembly structure configuration N at the final assembly stage (s) The number of sensors deployed n m ; At the same time, the target modal frequency range of all assembly structure configurations is determined according to the force spectrum frequency band range corresponding to the impact load generated during the assembly process;

[0010] 3) Perform finite element modal analysis on each assembly structure configuration according to the frequency range in step 2), select the mode within the frequency range as the target mode, obtain its modal vibration vectors of each order, and form the modal vibration matrix Φ j ;

[0011] 4) The jth assembly structure configuration N is calculated by the effective independent method (j) The contribution of the candidate sensor points in to the linear independence of the modal vibration shape of the current assembly structure configuration;

[0012] 5) Establish the effective independent coefficient of the assembly in the effective independent method, and perform weighted summation on the effective independent coefficient corresponding to each assembly structure configuration according to the corresponding sensor candidate point to obtain the effective independent vector E in the effective independent method. D , the elements in the vector are the effective independent coefficients of assembly;

[0013] 6) Iterate the assembly effective independent method and delete the assembly effective independent vector E D The sensor candidate point with the smallest coefficient in the modal vibration matrix Φ is deleted at the same time. j Repeat steps 4) to 5) in the corresponding row until the number of remaining sensor candidate points is equal to the number of points required in the assembly structure configuration N. (s) The number of sensors arranged on m ;

[0014] 7) Arrange the sensors according to the sensor arrangement scheme obtained in step 6) and assemble the structure configuration N (s) The system is disassembled according to the assembly process to obtain sensor layout plans for different assembly structure configurations, thus completing the optimized sensor layout for the on-orbit assembly structure.

[0015] Further, the step 1) specifically includes: a complete space on-orbit structure is set to have s assembly stages, and the structure corresponding to the jth stage is called the jth assembly structure configuration, and is represented by the symbol N (j) Represents, and j = 1, 2, ..., s, assembling structure configuration N at the same time (j) There is the following relationship:

[0016]

[0017] The above formula indicates that the assembly structure configurations of the previous assembly stage are all subsets of the subsequent assembly structure configurations, and the corresponding finite element model is established according to the relationship between the assembly structure configurations.

[0018] Furthermore, the step 2) specifically includes: obtaining the collision load during the assembly of the on-track structure and obtaining its force spectrum curve; then determining its effective frequency range according to the force spectrum curve, and the mode within the effective frequency range can be effectively excited, and it is believed that the mode within the effective frequency range can be regarded as the target mode.

[0019] Furthermore, when the uniaxial sensor is arranged in the assembly structure configuration in step 4), the calculation formula of the effective independent coefficient of the single assembly structure configuration is as follows:

[0020]

[0021] Among them, Φ j represents the mode shape matrix corresponding to the j-th assembly structure configuration, E D (j) It represents the effective independent vector corresponding to the j-th assembly structure configuration. Each element in the vector is an effective independent coefficient, which represents the contribution of the corresponding alternative point to the independence of the modal vibration shape. The superscript T represents the transpose operation of the matrix, and diag(·) represents taking the main diagonal elements of the matrix.

[0022] Furthermore, when arranging the three-dimensional sensor in the assembly structure configuration in step 4), the effective independence coefficient is calculated using the three-dimensional effective independence method, and the calculation formula is:

[0023]

[0024] Among them, Q (j) is the Fisher information matrix of the j-th assembled structure configuration in the effective independent assembly method, Reason The matrix composed of Respectively represent the assembly structure configuration N (j) The lth node of corresponds to the row vector of the modal vibration matrix under three translational degrees of freedom under the target mode; I3 is a 3×3 unit matrix, det(·) represents the determinant of the matrix, EFI3l (j) Represents the assembly structure configuration N in the effective independent method of assembly (j) The effective independence coefficient of the lth node, which represents the contribution of the current candidate point to the independence of the modal vibration shape.

[0025] Furthermore, the weighted summation method in step 5) is used to maximize the Fisher information matrix of each assembly structure configuration, and the effective independent coefficient vector E of different assembly structure configurations is D (j) Performing weighted summation gives the assembled effective independent vector E D , the vector E D Measures the contribution of each sensor candidate point to the linear independence of the target mode of all assembled structural configurations.

[0026] Furthermore, the weighted summation method in step 5) is as follows:

[0027]

[0028] Where i represents the assembly structure configuration N (s) The i-th sensor candidate point in E D,i It represents the ith element in the assembly effective independent vector. When a single-axis sensor is arranged, it is called the assembly effective independent coefficient. When a three-axis sensor is arranged, it is called the three-dimensional assembly effective independent coefficient. E D,i (j) Represents the assembly structure configuration N (s) The i-th node in the assembly structure N (j) The effective independence coefficient in is, Represents the weight of the effective independence coefficient of node i at assembly stage j.

[0029] Furthermore, the weight in step 5) The calculation formula is as follows:

[0030]

[0031] Among them, m k represents the number of target modes of the assembled structural configuration in the kth assembly stage, m j Represents the jth assembly structure configuration N (j) The target number of modes.

[0032] Furthermore, in step 5), the effective independence coefficient is weighted according to the target modal order to measure the contribution of the sensor candidate points in different assembly structure configurations to the target modal linear independence of the current assembly structure configuration; for the assembly structure configuration N (s)If the i-th node in the assembly structure belongs to the assembly structure configuration of the assembly stage j, and the assembly structure configuration has a large number of target modes, then the node needs to undertake more modal parameter identification tasks for the j-th assembly structure configuration. The effective independent coefficient E of node i in the assembly stage j is D,i (j) In assembling the effective independence coefficient E D,i It should occupy a large proportion.

[0033] Furthermore, in step 7), the sensor arrangement scheme obtained in step 6) is represented by a finite element node set SP (s) Indicates that the sensor arrangement scheme represents the assembly structure configuration N (s) Corresponding sensor layout, sensor layout scheme SP (s) According to the assembly process, the sensor layout scheme of the remaining assembly structure configuration is expressed as SP (j) , j = 1, 2, ..., s-1, and have the following relationship:

[0034]

[0035] The above formula indicates that the sensor arrangement schemes of the previous assembly structure configuration are all subsets of the sensor arrangement schemes corresponding to the next assembly structure configuration.

[0036] Beneficial effects of the present invention:

[0037] The present invention measures the contribution of all sensor candidate points to the linear independence of target modal vibration modes of different assembled structural configurations during the structural assembly process through the assembly effective independence coefficient, takes into account the optimal arrangement of sensors at different assembly stages of the on-orbit assembled structure, and effectively ensures the accuracy of structural modal parameter identification in the intermediate stage of assembly. BRIEF DESCRIPTION OF THE DRAWINGS

[0038] Figure 1 Flow chart of the method of the present invention.

[0039] Figure 2 Schematic diagram of an I-shaped truss structure.

[0040] Figure 3 This is a schematic diagram of the I-shaped truss assembly structure configuration.

[0041] Figure 4 Schematic diagram of the T-shaped truss assembly structure configuration.

[0042] Figure 5 Schematic diagram of weighted summation for assembling valid independent vectors.

[0043] Figure 6Schematic diagram of the assembly three-dimensional effective independence coefficients of all sensor candidate points on the I-truss structure.

[0044] Figure 7 Schematic diagram of the assembly three-dimensional effective independence coefficient of the sensor placement points on the I-shaped truss structure after optimization.

[0045] Figure 8 Schematic diagram of the sensor layout scheme for the I-shaped truss assembly structure configuration.

[0046] Fig. 9 Schematic diagram of the sensor layout scheme for the T-shaped truss assembly structure configuration.

[0047] Fig.10 Schematic diagram of the sensor layout scheme for the I-shaped truss structure. DETAILED DESCRIPTION

[0048] In order to facilitate the understanding of those skilled in the art, the present invention is further described below in conjunction with embodiments and drawings. The contents mentioned in the implementation modes are not intended to limit the present invention.

[0049] Reference Figure 1 As shown, a sensor optimization arrangement method based on the assembly effective independence method of the present invention comprises the following steps:

[0050] 1) Determine the on-orbit assembly process of the space structure and the assembly structure configuration corresponding to each assembly stage, and establish a finite element model for all assembly structure configurations; specifically, a complete on-orbit space structure is set to have s assembly stages, and the structure corresponding to the jth stage is called the jth assembly structure configuration, which is symbolized by N (j) Represents, and j = 1, 2, ..., s, assembling structure configuration N at the same time (j) There is the following relationship:

[0051]

[0052] The above formula indicates that the assembly structure configurations of the previous assembly stage are all subsets of the subsequent assembly structure configurations, and the corresponding finite element model is established according to the relationship between the assembly structure configurations.

[0053] 2) Determine the assembly structure configuration N at the final assembly stage (s) The number of sensors deployed n m ; At the same time, the target modal frequency range of all assembled structural configurations is determined according to the force spectrum frequency band range corresponding to the impact load generated during the assembly process; specifically, it includes: obtaining the collision load during the on-orbit structure assembly process and obtaining its force spectrum curve; and then determining its effective frequency range according to the force spectrum curve. The modes within the effective frequency range can be effectively excited, and it is believed that the modes within the effective frequency range can be regarded as target modes.

[0054] 3) Perform finite element modal analysis on each assembly structure configuration according to the frequency range in step 2), select the mode within the frequency range as the target mode, obtain its modal vibration vectors of each order, and form the modal vibration matrix Φ j ;

[0055] 4) The jth assembly structure configuration N is calculated by the effective independent method (j) The contribution of the candidate sensor points in to the linear independence of the modal vibration shape of the current assembly structure configuration;

[0056] Among them, when a single-axis sensor is arranged in a single assembly structure configuration, the calculation formula of its effective independence coefficient is as follows:

[0057]

[0058] Among them, Φ j represents the mode shape matrix corresponding to the j-th assembly structure configuration, E D (j) It represents the effective independent vector corresponding to the j-th assembly structure configuration. Each element in the vector is an effective independent coefficient, which represents the contribution of the corresponding alternative point to the independence of the modal vibration shape. The superscript T represents the transpose operation of the matrix, and diag(·) represents taking the main diagonal elements of the matrix.

[0059] Among them, when arranging the three-dimensional sensor in the assembly structure configuration, the effective independence coefficient is calculated using the three-dimensional effective independence method, and the calculation formula is:

[0060]

[0061] Among them, Q (j) is the Fisher information matrix of the j-th assembled structure configuration in the effective independent assembly method, Reason The matrix composed of Respectively represent the assembly structure configuration N (j) The lth node of corresponds to the row vector of the modal vibration matrix under three translational degrees of freedom under the target mode; I3 is a 3×3 unit matrix, det(·) represents the determinant of the matrix, EFI 3l (j) Represents the assembly structure configuration N in the effective independent method of assembly (j) The effective independence coefficient of the lth node, which represents the contribution of the current candidate point to the independence of the modal vibration shape.

[0062] 5) Establish the effective independent coefficient of the assembly in the effective independent method, and perform weighted summation on the effective independent coefficient corresponding to each assembly structure configuration according to the corresponding sensor candidate point to obtain the effective independent vector E in the effective independent method.D ;

[0063] Among them, the weighted summation method is used to maximize the Fisher information matrix of each assembly structure configuration, and the effective independent coefficient vector E of different assembly structure configurations is D (j) The weighted sum gives the assembled effective independent vector E D , the vector E D Measures the contribution of each sensor candidate point to the linear independence of the target mode of all assembled structural configurations.

[0064] The weighted summation method is as follows:

[0065]

[0066] Where i represents the assembly structure configuration N (s) The i-th sensor candidate point in E D,i It represents the ith element in the assembly effective independent vector. When a single-axis sensor is arranged, it is called the assembly effective independent coefficient. When a three-axis sensor is arranged, it is called the three-dimensional assembly effective independent coefficient. E D,i (j) Represents the assembly structure configuration N (s) The i-th node in the assembly structure N (j) The effective independence coefficient in is, Represents the weight of the effective independence coefficient of node i at assembly stage j.

[0067] The weight The calculation formula is as follows:

[0068]

[0069] Among them, m k represents the number of target modes of the assembled structural configuration in the kth assembly stage, m j Represents the jth assembly structure configuration N (j) The target number of modes.

[0070] In the step 5), the effective independence coefficient is weighted according to the target modal order to measure the contribution of the sensor candidate points in different assembly structure configurations to the target modal linear independence of the current assembly structure configuration; for the assembly structure configuration N (s) If the i-th node in the assembly structure belongs to the assembly structure configuration of the assembly stage j, and the assembly structure configuration has a large number of target modes, then the node needs to undertake more modal parameter identification tasks for the j-th assembly structure configuration. The effective independent coefficient E of node i in the assembly stage j is D,i (j) In assembling the effective independence coefficient E D,iIt should occupy a large proportion.

[0071] 6) Iterate the assembly effective independent method and delete the assembly effective independent vector E D The sensor candidate point with the smallest coefficient in the modal vibration matrix Φ is deleted at the same time. j Repeat steps 4) to 5) in the corresponding row until the number of remaining sensor candidate points is equal to the number of points required in the assembly structure configuration N. (s) The number of sensors arranged on m ;

[0072] 7) The sensor layout solution obtained in step 6) is converted into a finite element node set SP (s) Indicates that the sensor arrangement scheme represents the assembly structure configuration N (s) Corresponding sensor layout, sensor layout scheme SP (s) According to the assembly process, the sensor layout scheme of the remaining assembly structure configuration is expressed as SP (j) , j = 1, 2, ..., s-1, and have the following relationship:

[0073]

[0074] The above formula indicates that the sensor arrangement schemes of the previous assembly structure configuration are all subsets of the sensor arrangement schemes corresponding to the next assembly structure configuration.

[0075] In the example:

[0076] (1) Consideration Figure 2 The "I"-shaped space truss structure shown in the figure is assumed to be assembled in three stages, namely, an "I"-shaped truss assembly structure configuration, a "T"-shaped truss assembly structure configuration and an "I"-shaped space truss structure. The schematic diagrams of the "I"-shaped truss assembly structure configuration and the "T"-shaped truss assembly structure configuration are shown in FIG. Figure 3 and Figure 4 As shown;

[0077] (2) Figure 2 Twenty triaxial sensors are arranged on the "I"-shaped space truss structure shown. It is considered that the collision load generated during the assembly process is a half-sine impact load with an action time of 0.01s and an amplitude of 2000N, and its effective frequency band range is 0-60Hz;

[0078] (3) Targeting Figure 2 to Figure 4The finite element model of the space truss structure is established, and its modes between 0 and 60 Hz are analyzed, and the modal vibration matrix of the above three structures is given. The assembly structure configuration at assembly stage 1 is a "I" truss, the assembly structure configuration at assembly stage 2 is a "T" truss, and the assembly structure configuration at assembly stage 3 is an "I" shaped space truss. At assembly stage 3, the entire on-track assembly stage is completed. After finite element modal analysis, the modal matrices corresponding to the above three structures are obtained, which are Φ1, Φ2 and Φ3 respectively;

[0079] (4) Applying the modal vibration matrix in step (3) to calculate the effective independence coefficients of the candidate sensor points on the three structures, and applying the three-dimensional effective independence method to calculate, obtain three three-dimensional effective independent vectors corresponding to the three structures;

[0080] (5) In the modal analysis in step (3), the target modal number of the “I” truss is 8, the target modal number of the “T” truss is 16, and the target modal number of the “I” truss is 24. According to the target modal number, the three three-dimensional effective independent vectors are weighted summed according to the sensor candidate points, as follows: Figure 5 As shown, the three-dimensional assembly effective independent coefficient of the “I”-shaped space truss is obtained;

[0081] (6) The effective independent coefficient of the three-dimensional assembly of the “I”-shaped structure obtained in step (5) is as follows: Figure 6 As shown in Figure 1, delete the candidate sensor point with the smallest coefficient, and then repeat steps (4) to (5) until the number of remaining candidate sensor points is equal to the number of arranged sensors, that is, the calculation is completed when the number of remaining candidate sensor points is equal to 20. At this time, the effective independent coefficient of the three-dimensional assembly of the "I"-shaped structure is as follows: Figure 7 As shown;

[0082] (7) The sensor candidate points given in step (6) are the optimal sensor layout scheme, which takes into account the optimal layout of sensors at all stages of the on-orbit assembly of the space structure, maximizes the Fisher information matrix of each assembly structure configuration, and has the effect of accurately identifying the modal parameters of each assembly structure configuration. The sensor layout scheme given in step (6) is used to arrange the assembly structure configuration, and the assembly structure configuration is split according to the assembly stage to obtain the optimal sensor layout scheme for the structure at different assembly stages, such as Figure 8 to Figure 10 shown.

[0083] The present invention has many specific application paths. The above is only a preferred embodiment of the present invention. It should be pointed out that for ordinary technicians in this technical field, several improvements can be made without departing from the principle of the present invention. These improvements should also be regarded as the protection scope of the present invention.

Claims

1. A sensor optimization layout method based on assembly effective independence method, It is characterized in that Here are the steps: 1) Determine the on-orbit assembly process of the space structure and the assembly structure configuration corresponding to each assembly stage, and establish a finite element model for all assembly structure configurations; 2) Determine the assembly structure configuration N at the final assembly stage (s) The number of sensors deployed n m ; At the same time, the target modal frequency range of all assembly structure configurations is determined according to the force spectrum frequency band range corresponding to the impact load generated during the assembly process; 3) Perform finite element modal analysis on each assembly structure configuration according to the frequency range in step 2), select the mode within the frequency range as the target mode, obtain its modal vibration vectors of each order, and form the modal vibration matrix Φ j ; 4) The jth assembly structure configuration N is calculated by the effective independent method (j) The contribution of the candidate sensor points in to the linear independence of the modal vibration shape of the current assembly structure configuration; 5) Establish the effective independent coefficient of the assembly in the effective independent method, and perform weighted summation on the effective independent coefficient corresponding to each assembly structure configuration according to the corresponding sensor candidate point to obtain the effective independent vector E in the effective independent method. D ; 6) Iterate the assembly effective independent method and delete the assembly effective independent vector E D The sensor candidate point with the smallest coefficient in the modal vibration matrix Φ is deleted at the same time. j Repeat steps 4) to 5) in the corresponding row until the number of remaining sensor candidate points is equal to the number of points required in the assembly structure configuration N. (s) The number of sensors arranged on m ; 7) Arrange the sensors according to the sensor arrangement scheme obtained in step 6) and assemble the structure configuration N (s) The sensor layout schemes for different assembly structure configurations are obtained by splitting according to the assembly process, and the sensor optimization layout for the on-orbit assembly structure is completed; The weighted summation method in step 5) is used to maximize the Fisher information matrix of each assembly structure configuration, and the effective independent coefficient vector E of different assembly structure configurations is D (j) The weighted sum gives the assembled effective independent vector E D , vector E D Measure the contribution of each candidate sensor point to the linear independence of the target mode of all assembled structural configurations; The weighted summation method in step 5) is as follows: Where i represents the assembly structure configuration N (s) The i-th sensor candidate point in E D,i It represents the ith element in the assembly effective independent vector. When a single-axis sensor is arranged, it is called the assembly effective independent coefficient. When a three-axis sensor is arranged, it is called the three-dimensional assembly effective independent coefficient. E D,i (j) Represents the assembly structure configuration N (s) The i-th node in the assembly structure N (j) The effective independence coefficient in is, represents the weight of the effective independence coefficient of node i at assembly stage j; The weight in step 5) The calculation formula is as follows: Among them, m k represents the target mode number of the assembled structural configuration in the kth assembly stage, m j Represents the jth assembly structure configuration N (j) The target number of modes.

2. The sensor optimization arrangement method based on the assembly effective independence method according to claim 1, It is characterized in that The step 1) specifically includes: a complete space on-orbit structure is set to have s assembly stages, and the structure corresponding to the jth stage is called the jth assembly structure configuration, and is represented by the symbol N (j) Represents, and j = 1, 2, ..., s, assembling structure configuration N at the same time (j) There is the following relationship: The above formula indicates that the assembly structure configurations of the previous assembly stage are all subsets of the subsequent assembly structure configurations, and the corresponding finite element model is established according to the relationship between the assembly structure configurations.

3. The sensor optimization arrangement method based on the assembly effective independence method according to claim 1, It is characterized in that The step 2) specifically includes: obtaining the collision load during the assembly of the on-track structure and obtaining its force spectrum curve; then determining its effective frequency range according to the force spectrum curve, and the mode within the effective frequency range can be effectively excited, and it is believed that the mode within the effective frequency range can be regarded as the target mode.

4. The sensor optimization arrangement method based on the assembly effective independence method according to claim 1, It is characterized in that When the uniaxial sensor is arranged in the assembly structure configuration in step 4), the calculation formula of the effective independent coefficient of the candidate point of the single assembly structure configuration sensor is as follows: Among them, Φ j represents the mode shape matrix corresponding to the j-th assembly structure configuration, E D (j) It represents the effective independent vector corresponding to the j-th assembly structure configuration. Each element in the vector is an effective independent coefficient, which represents the contribution of the corresponding alternative point to the independence of the modal vibration shape. The superscript T represents the transpose operation of the matrix, and diag(·) represents taking the main diagonal elements of the matrix.

5. The sensor optimization arrangement method based on the assembly effective independence method according to claim 1, It is characterized in that When the three-dimensional sensor is arranged in the assembly structure configuration in step 4), the effective independence coefficient of a single assembly structure configuration is calculated using the three-dimensional effective independence method, and the calculation formula is: Among them, Q (j) is the Fisher information matrix of the jth assembly structure configuration in the assembly effective independent method, Reason The matrix composed of Respectively represent the assembly structure configuration N (j) The lth node of corresponds to the row vector of the modal vibration matrix under three translational degrees of freedom in the target mode; 3 is a 3×3 unit matrix, det(·) means finding the determinant of the matrix, EFI 3l (j) Represents the assembly structure configuration N in the effective independent method of assembly (j) The effective independence coefficient of the lth node, which represents the contribution of the current candidate point to the independence of the modal vibration shape.

6. The sensor optimization arrangement method based on the assembly effective independence method according to claim 1, It is characterized in that In the step 5), the effective independence coefficient is weighted according to the target modal order to measure the contribution of the sensor candidate points in different assembly structure configurations to the target modal linear independence of the current assembly structure configuration; for the assembly structure configuration N (s) If the i-th node in the assembly structure belongs to the assembly structure configuration of the assembly stage j, and the assembly structure configuration has a large number of target modes, then the node needs to undertake more modal parameter identification tasks for the j-th assembly structure configuration. The effective independent coefficient E of node i in the assembly stage j is D,i (j) In assembling the effective independence coefficient E D,i It should occupy a large proportion.

7. The sensor optimization arrangement method based on the assembly effective independence method according to claim 1, It is characterized in that In step 7), the sensor arrangement scheme obtained in step 6) is transformed into a finite element node set SP (s) Indicates that the sensor arrangement scheme represents the assembly structure configuration N (s) The corresponding sensor layout, sensor layout scheme SP (s) According to the assembly process, the sensor layout scheme of the remaining assembly structure configuration is expressed as SP (j) , j = 1, 2, ..., s-1, and have the following relationship: The above formula indicates that the sensor arrangement schemes of the previous assembly structure configuration are all subsets of the sensor arrangement schemes corresponding to the next assembly structure configuration.

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