Discontinuous wing structure deformation reconstruction method and system based on inclination angle compensation

Abstract

The invention provides a discontinuous wing structure deformation reconstruction method and system based on inclination angle compensation, and belongs to the technical field of structure health state monitoring, and the method comprises the steps: obtaining calibration strain data and calibration displacement data of a discontinuous wing; according to a calibration method, calculating a neutral surface thickness and a dip angle coefficient; and completing structural deformation reconstruction of the wing according to the calibrated thickness of the neutral surface, the dip angle coefficient and the reconstruction method in combination with the real-time strain value. Aiming at the problem of the additional dip angle at the joint of the discontinuous wing, the dip angle coefficient reflecting the direct proportion relation between the additional dip angle and the wing surface strain is constructed, the problem that the deformation of the discontinuous wing cannot be reconstructed by a classical Ko displacement theory method is solved, and the deformation reconstruction of the discontinuous wing is realized.

Description

Technical Field

[0001] The present invention belongs to the technical field of structural health monitoring, and particularly relates to a discontinuous wing structure deformation reconstruction method and system based on inclination compensation. Background Art

[0002] The statements in this part merely provide background technical information related to the present invention and do not necessarily constitute prior art.

[0003] In recent years, with the development of aerospace technology, the large aspect ratio design has gradually become an important design trend for new aircraft such as large transport aircraft, bombers, and solar aircraft. The large aspect ratio design can improve the aerodynamic efficiency of the aircraft, reduce fuel consumption, and extend the flight range. However, the wing structures of such aircraft are usually discontinuous, with large flexibility and complex stress characteristics. During flight, the wing structure is prone to large elastic deformations under the action of various loads. Especially under the combined influence of aerodynamic loads, gravity, and inertial forces, the deformation of the wing will have an important impact on flight safety and performance. Therefore, how to monitor and reconstruct the deformation state of the wing structure in real time has become a key issue to ensure the safe operation of the aircraft.

[0004] The structural deformation reconstruction technology based on strain information is one of the forefront research directions in the field of structural health monitoring and deformation reconstruction. This technology can reconstruct the deformation morphology of the structure by obtaining the strain data of the structure in real time, providing key support for the safety monitoring and maintenance of the aircraft. Especially in the complex wing structures of large aspect ratio aircraft, the deformation reconstruction technology can effectively reflect the stress conditions and deformation states of the structure, thereby ensuring the safety and reliability of the aircraft under different load conditions.

[0005] At present, there are many reconstruction methods for wing structure deformation, and common ones include the Ko displacement method, curvature reconstruction algorithm, modal superposition method, etc. Among them, William L. Ko et al. proposed the Ko displacement theory. By means of piecewise linear or nonlinear processing, the deformation problem of high aspect ratio wing structures is transformed into a summation problem, realizing wing deformation reconstruction. An FBG strain sensing system was embedded in the wing main beam of the "Predator-B" prototype Ikhana, and longitudinal displacement was calculated using multi-point strain data, verifying the feasibility of this theory. Gao T et al. proposed a method for optimizing the layout of strain sensors based on finite element analysis. Combining FBG sensors and the Ko displacement theory, precise reconstruction of wing deformation was achieved, verifying the effectiveness and feasibility of the method. Chen Xinyi studied the real-time deformation monitoring of flexible high aspect ratio wings. Using the Ko displacement theory and ridge regression algorithm, high-precision structure reconstruction was realized, improving flight safety. Guo et al. proposed a graphene-based flexible electronic skin, and an optimized reconstruction method was proposed based on the Ko displacement method to realize the reconstruction of wing surface deformation. The results showed an error of less than 5%, solving the limitations of existing online monitoring and testing methods for flexible wing surface deformation. Zhang Junkang et al. used single-core fiber Bragg grating sensing, deduced based on the relationship between strain and curvature, and realized the three-dimensional shape reconstruction of the flexible skin through coordinate transformation and curve fitting. This method effectively solved the problem of shape reconstruction of aircraft under different loads. Subsequently, multi-core fiber Bragg grating sensing was adopted, a curve reconstruction was established through the relationship between wavelength drift and curvature, and temperature decoupling was used to reduce temperature errors. The reconstructed curve was converted into the deployment angle and flip angle of the aircraft, realizing the continuity of multi-dimensional large-scale deformation. Wang Wenjuan et al. proposed fiber optic strain-deformation algorithms and curvature reconstruction algorithms for the shape change of the trailing edge of variable camber wings, verified the algorithms theoretically and experimentally, and carried out application verification on the trailing edge of the wing, which can well realize the deformation test of the trailing edge of the wing. Si et al. proposed a method for monitoring and reconstructing the strain field of a scaled model of a high aspect ratio wing based on the combination of distributed fiber optic sensors and the modal superposition principle for the problem of reconstructing the strain field of an aircraft wing structure. The research results show that this method has the advantages of non-visual measurement, good real-time performance, and relatively high inversion accuracy. Li Wuqian carried out reconstruction on the research object based on the displacement reconstruction algorithm of the modal superposition method for the static and dynamic deformations of large flexible structures such as large aircraft wings. The results showed that the reconstructed displacement and the measured displacement were in good agreement, verifying the effectiveness of the structural displacement reconstruction technology based on the modal superposition method.

[0006] However, both the Ko displacement method and the curvature reconstruction method assume that the structure is continuous and has uniform stiffness. At the joints of the discontinuous wing, the stiffness and stress distribution change suddenly, and there is an angle, which destroys the continuity and smooth curvature assumptions of the structure, resulting in the inability of these two methods to accurately reconstruct the deformation of the discontinuous wing. The modal superposition method relies on the establishment of an accurate structural model, but for complex actual wing structures, it is very difficult to establish a model that is highly consistent with the actual situation. The complex geometry of the wing, uneven material distribution, discontinuous joints and other factors are difficult to express through modal expressions, resulting in the difficulty of the modal superposition method to accurately capture the response of the actual structure, thus affecting the accuracy of the analysis. Summary of the invention

[0007] In order to overcome the deficiencies of the above-mentioned prior art, the present invention proposes a method and system for reconstructing the deformation of a discontinuous wing structure based on inclination compensation, and uses a connection position inclination compensation method and an additional inclination and neutral plane thickness calibration method in combination. Aiming at the additional inclination problem at the connection of the discontinuous wing, an inclination coefficient reflecting the proportional relationship between the additional inclination and the wing surface strain is constructed, and a bridge between the strain and the additional inclination is established. In addition, the additional inclination and the neutral plane thickness are calibrated with measured data, and combined with the Ko displacement theory, a method for reconstructing the deformation of a discontinuous wing based on the connection position inclination compensation is proposed, which solves the problem that the classical Ko displacement theory method cannot reconstruct the deformation of the discontinuous wing, and realizes the deformation reconstruction of the discontinuous wing.

[0008] To achieve the above objectives, one or more embodiments of the present invention provide the following technical solutions: In a first aspect, a method for reconstructing a discontinuous wing structure deformation based on tilt angle compensation is disclosed, comprising: Obtaining calibrated strain data and calibrated displacement data of the discontinuous wing; According to the calibration method, the neutral plane thickness and inclination coefficient are calculated; According to the calibrated neutral plane thickness, inclination coefficient and reconstruction method, combined with the real-time strain value, the structural deformation reconstruction of the wing is completed.

[0009] Further, the calibration method includes inclination coefficient calibration; The inclination coefficient calibration specifically includes: Calculate the additional inclination angle of the discontinuous wing, expressed as:

[0010] In the formula, is the additional inclination angle; is the angle between the true displacement of the second wing section and the horizontal direction; is the angle between the displacement reconstructed by Ko displacement theory and the horizontal direction; The additional inclination angle is directly proportional to the strain at a specific position on the second - stage wing, and the inclination coefficient is obtained, which is expressed as:

[0011] In the formula, is the inclination coefficient; is the strain value.

[0012] Furthermore, the calibration method also includes the calibration of the neutral - plane thickness; The calibration of the neutral - plane thickness is specifically to divide the measured strain value by the second - order derivative of the true displacement curve at this point to obtain the calibrated thickness, which is expressed as:

[0013] In the formula, is the neutral - plane thickness; is the measured strain value; is the second - order derivative of the true displacement curve at this point.

[0014] Furthermore, before calculating the neutral - plane thickness and the inclination coefficient, it also includes the Ko - theory analysis. The specific derivation process is as follows: Assume that the length of the cantilever - beam structure is , and FBG sensors are arranged at equal intervals along its length direction. In the area between two adjacent sensors, the neutral - plane thickness function and the strain function of the structure are expressed as linear functions. According to the structural differential equation, the slope function of the structure is obtained through integration. Substitute the neutral - plane thickness function and the strain function into the slope function to obtain the slope value at any position. According to the structural differential equation, the displacement function of the structure is obtained through two - time integration. Substitute the neutral - plane thickness function and the strain function into the displacement function to obtain the displacement value at any position.

[0015] Furthermore, the reconstruction method includes compensating for the corresponding additional inclination angle according to the strain and the inclination coefficient under the action of an unknown load to obtain the compensated wing displacement curve. Merge the inclination - compensated wing displacement curve with the previous - stage displacement curve at the end point to obtain the final discontinuous wing displacement curve, realizing the reconstruction of the discontinuous wing - structure deformation.

[0016] Furthermore, according to the inclination coefficient and the strain value under the unknown load, the additional inclination angle under this load is calculated, which is expressed as:

[0017] In the formula, is the additional inclination angle; is the inclination coefficient; is the strain value.

[0018] Further, according to the obtained additional inclination angle and the coordinate transformation principle, the wing displacement curve after inclination compensation is obtained, which is expressed as:

[0019] In the formula, is the position coordinate of the second segment of the wing after inclination compensation, is the displacement curve of the second segment of the wing after inclination compensation, is the position coordinate of the second segment of the wing, is the displacement curve of the second segment of the wing reconstructed according to the Ko displacement.

[0020] In a second aspect, a discontinuous wing structure deformation reconstruction system based on inclination compensation is disclosed, including: An initialization module, which is configured to: obtain the calibrated strain data and calibrated displacement data of the discontinuous wing; A calibration module, which is configured to: calculate the neutral plane thickness and the inclination coefficient according to the calibration method; A reconstruction module, which is configured to: complete the structural deformation reconstruction of the wing according to the neutral plane thickness, inclination coefficient and reconstruction method obtained by calibration, in combination with the real-time strain value.

[0021] In a third aspect, an electronic device is disclosed, including a memory, a processor, and computer instructions stored on the memory and running on the processor. When the computer instructions are run by the processor, the steps of the above-mentioned discontinuous wing structure deformation reconstruction method based on inclination compensation are completed.

[0022] In a fourth aspect, a computer-readable storage medium is disclosed, which is used to store computer instructions. When the computer instructions are executed by the processor, the steps of the above-mentioned discontinuous wing structure deformation reconstruction method based on inclination compensation are completed.

[0023] Compared with the prior art, the beneficial effects of the present invention are as follows: The present invention can effectively handle the discontinuity problem of the wing. Aiming at the stiffness difference and initial inclination problem at the wing joint, an inclination compensation method is proposed, which effectively reduces the error in the reconstruction process and improves the accuracy of displacement reconstruction.

[0024] The calibration method proposed by the present invention has stability and strong adaptability: the calibration of the inclination coefficient adopts the method of calculating the average value of multiple loads to ensure the stability of deformation reconstruction; the calibration of the neutral plane thickness is obtained by calculating the real displacement and strain of the wing, which makes this method applicable to various types of wings and ensures the adaptability of the proposed method.

[0025] The present invention realizes high-precision strain measurement. The strain change of the wing structure is measured in real time and accurately through the fiber Bragg grating sensor, which can reflect tiny deformations.

[0026] Advantages of additional aspects of the present invention will be given in part in the following description, become apparent in part from the following description, or be learned through the practice of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] The accompanying drawings forming a part of this specification are used to provide a further understanding of the present invention. The schematic embodiments and descriptions thereof of the present invention are used to explain the present invention and do not constitute an improper limitation to the present invention.

[0028] Figure 1 It is a flowchart of a discontinuous wing structure deformation reconstruction method based on inclination compensation described in Embodiment 1 of the present invention.

[0029] Figure 2 It is a schematic diagram of a discontinuous wing described in Embodiment 1 of the present invention.

[0030] Figure 3 It is the analysis result of Ko displacement theory described in Embodiment 1 of the present invention.

[0031] Figure 4 It is the inclination coefficient under different load conditions described in Embodiment 1 of the present invention.

[0032] Figure 5 It is the analysis result of the discontinuous wing structure deformation reconstruction method based on inclination compensation described in Embodiment 1 of the present invention. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0033] It should be noted that the following detailed description is exemplary and is intended to provide further explanation of the present invention. Unless otherwise specified, all technical and scientific terms used herein have the same meaning as commonly understood by those of ordinary skill in the technical field to which the present invention belongs.

[0034] It should be noted that the terms used herein are only for describing specific embodiments and are not intended to limit the exemplary embodiments according to the present invention.

[0035] Without conflict, the embodiments in the present invention and the features in the embodiments can be combined with each other.

[0036] Embodiment 1 In one or more embodiments, a discontinuous wing structure deformation reconstruction method based on inclination compensation is disclosed. As Figure 1 shown, it includes the following steps: Step 1: Obtain multiple groups of calibrated strains of the discontinuous wing through strain measurement methods such as FBG sensors, and simultaneously obtain corresponding calibrated displacement data through displacement measurement methods such as visual measurement.

[0037] Step 2: Calculate the neutral plane thickness and inclination coefficient according to the calibration method.

[0038] Specifically, the calibration method includes inclination coefficient calibration and neutral plane thickness calibration.

[0039] First, conduct a theoretical analysis of the Ko displacement. The Ko displacement theory is based on classical mechanics of materials and the Euler-Bernoulli beam theory. By means of piecewise linear or nonlinear assumptions, the deformation problem of the beam structure is transformed into a summation problem. For a beam structure subjected to a bending load, the approximate differential equation of its displacement is: (1) In the formula, is the coordinate in the structural length direction, is the vertical deformation amount, i.e., the displacement, at the measuring point, is the bending load borne by the structure, is the Young's modulus of the material, is the moment of inertia of the beam cross-section. The relationship between the stress and the load at the position (upper surface or lower surface) can be expressed as: (2) In the formula, is the stress, is the load, represents 1 / 2 of the structural thickness. According to Hooke's law, the relationship between stress and strain can be expressed as: (3) In the formula, is the structural strain.

[0040] According to formula (2) and formula (3), the load borne by the structure can be expressed as a function of the structural strain: (4) Then the differential equation of the structure can be expressed as: (5) It can be obtained from formula (5) that the deformation information of the structure is only related to the geometric dimensions (thickness) of the structure and has nothing to do with the material properties (Young's modulus , moment of inertia of the cross-section , etc.). For a beam structure with a varying thickness, is no longer a constant, but should be . Therefore, the corrected differential equation of the structure is expressed as: (6) In the formula, c(x) is the neutral plane thickness function.

[0041] The deformation information of the structure can be obtained by integrating the modified structural differential equation, that is, the Ko displacement theory equation. The specific derivation process is as follows: , that is, the Ko displacement theory equation. The specific derivation process is as follows: Assume that the length of the cantilever beam structure is , and FBG sensors are arranged at equal intervals along its length. In the region between two adjacent sensors , the neutral plane thickness function and the strain function of the structure can be expressed as linear functions (7) (8) where and correspond to the neutral plane thickness and strain magnitude of the structure at the position respectively. In the region, the slope function of the structure at the position can be obtained by integrating Equation (6), that is (9) where is the slope value at the position. Substituting Equations (7) and (8) into (9), we get (10) In the region, the displacement function of the structure at the position can be obtained by integrating Equation (6) twice, that is (11) where is the displacement at the position. Substituting Equations (7) and (8) into the above equation, we get (12) One end of the cantilever beam structure is fixed and the other end is free. The displacement and slope at the fixed end are both 0, that is , , which are the boundary conditions of the Ko displacement theory for a single-sided fixed cantilever beam structure.

[0042] According to the Ko displacement theory, that is, Equation (12), the deformation displacement of the aircraft wing can be calculated to realize the structural deformation reconstruction. However, for a discontinuous wing, such as Figure 2As shown, due to the different stiffness of the wing connection part from the rest and the existence of an initial inclination angle, when the wing bears a load, not only conventional bending deformation occurs at the connection part, but also an additional inclination change occurs.

[0043] As Figure 3 shown, the displacement curves obtained by Abaqus analysis and the displacement curves reconstructed using the Ko displacement theory. From Figure 3 it can be seen that starting from the second section of the wing, the reconstruction accuracy of the Ko displacement theory decreases, resulting in a large error, and the end error reaches 30.8%. Assuming that the true displacement of the second section of the wing forms an angle with the horizontal direction, while the displacement reconstructed by the Ko displacement theory forms an angle with the horizontal direction. From Figure 3 it can be known that , that is, an additional inclination angle is generated: (13) In the formula, is the additional inclination angle.

[0044] This is mainly because the premise of the Ko displacement theory is a continuous beam, without considering the discontinuity caused by the connection. In addition, the reconstruction algorithm of the Ko displacement theory has the characteristic of error accumulation. Therefore, when analyzing a discontinuous wing, a large error will occur at the connection and run through the displacement reconstruction of the second section of the wing.

[0045] In order to eliminate the reconstruction error caused by the additional inclination angle, in this embodiment, it is analyzed that there is a proportional relationship between the additional inclination angle and the strain at a specific position of the second section of the wing. It should be noted that the magnitude of this additional inclination angle is mainly affected by the load borne by the second section of the wing and has nothing to do with the load of the first section of the wing. This relationship is expressed by introducing an inclination coefficient (14) In the formula, is the inclination coefficient, reflecting the proportional relationship between the strain and the additional inclination angle.

[0046] To further analyze the value of this inclination coefficient, in this embodiment, a finite element analysis of the inclination coefficient under different load combinations is carried out. As Figure 4 shown, the inclination coefficients under different load conditions (the load of the first section of the wing is 0.5 MPa, 0.8 MPa, and 1 MPa, and the loads of the second section of the wing are 0.5, 0.8, and 1 MPa respectively)The variation. The results show that, despite different load conditions, the calculated dip angle coefficient basically remains around 23.5, indicating that the dip angle coefficient can be taken as a fixed value. Therefore, it is deduced that under all load combinations, there is a direct proportional relationship with a fixed dip angle coefficient between the additional dip angle and the strain.

[0047] This result not only proves the proportional relationship between the additional dip angle and the strain, but also provides a theoretical basis for further displacement compensation and result optimization.

[0048] To ensure the stability of the finally calibrated dip angle coefficient, obtain the additional dip angles and strain values under different loads, and calculate the dip angle coefficient according to formula (14) .

[0049] Secondly, it is the calibration of the neutral plane thickness: As can be seen from formula (12), the neutral plane thickness needs to be input for calculating the reconstructed displacement. However, due to the discontinuity and asymmetry of the discontinuous wing structure, it cannot be directly obtained theoretically. Therefore, the present invention adopts a calibration method. From formula (6), it can be obtained (15) wherein, is the second derivative of the displacement function. Divide the measured strain value by the second derivative of the true displacement curve at this point, and the calibrated thickness can be obtained. This calibration method only needs to obtain the true displacement and true strain of the wing to obtain the neutral plane thickness, so it has strong adaptability.

[0050] Step 3: According to the calibrated neutral plane thickness, dip angle coefficient and reconstruction method, combined with the real-time strain value, complete the structural deformation reconstruction of the wing.

[0051] First of all, under the action of unknown loads, multiply the strain by the dip angle coefficient to obtain the corresponding additional dip angle, so as to carry out compensation to ensure the accurate reconstruction of the wing deformation. The dip angle compensation steps are as follows: According to the dip angle coefficient and the strain value under unknown loads, calculate the additional dip angle under this load, which is expressed as: (16) According to the coordinate transformation principle and the additional dip angle obtained from formula (16), construct the coordinate rotation matrix and displacement matrix , which are expressed as: (17) (18) wherein, is the position coordinate of the second segment of the wing, is the displacement curve of the second segment of the wing reconstructed according to the Ko displacement. Multiply the coordinate rotation matrix and the displacement matrix to obtain the displacement curve after coordinate transformation, which is expressed as: (19) The displacement curve of the second segment of the wing after inclination compensation is re-merged with the displacement curve of the first segment at the endpoints to obtain the final discontinuous wing displacement curve, that is, to realize the structural deformation reconstruction of the wing. As Figure 5 shown in the analysis result after inclination compensation, it can be seen that the inclination compensation effectively eliminates the error caused by the additional inclination, and the end error reaches 1.54%, verifying the effectiveness of the inclination compensation method proposed in the present invention.

[0052] If the discontinuous wing is composed of more than two segments of the wing, then after inclination compensation is performed on each segment in turn and merged with the previous segment at the endpoints until all segments are merged, the final discontinuous wing displacement curve is formed to realize the structural deformation reconstruction of the discontinuous wing.

[0053] Embodiment 2 In one or more embodiments, a discontinuous wing structural deformation reconstruction system based on inclination compensation is disclosed, specifically including: An initialization module, which is configured to: obtain the calibrated strain data and calibrated displacement data of the discontinuous wing; A calibration module, which is configured to: calculate the neutral plane thickness and inclination coefficient according to the calibration method; A reconstruction module, which is configured to: complete the structural deformation reconstruction of the wing according to the neutral plane thickness, inclination coefficient and reconstruction method obtained by calibration, in combination with the real-time strain value.

[0054] Embodiment 3 This embodiment provides an electronic device, including a memory and a processor, and computer instructions stored on the memory and running on the processor. When the computer instructions are run by the processor, the steps of the above-mentioned discontinuous wing structural deformation reconstruction method based on inclination compensation are completed.

[0055] Embodiment 4 This embodiment provides a computer-readable storage medium for storing computer instructions. When the computer instructions are executed by a processor, the steps of the above-mentioned discontinuous wing structural deformation reconstruction method based on inclination compensation are completed.

[0056] The present invention is described with reference to the flowcharts and / or block diagrams of methods, apparatuses (systems), and computer program products according to embodiments of the present invention. It should be understood that each flow and / or block in the flowchart and / or block diagram, as well as the combination of flows and / or blocks in the flowchart and / or block diagram, can be implemented by computer program instructions. These computer program instructions can be provided to the processor of a general-purpose computer, a special-purpose computer, an embedded processor, or other programmable data processing devices to generate a machine, such that the instructions executed by the processor of the computer or other programmable data processing devices produce means for implementing the functions specified in one flow Figure 1 one flow or multiple flows and / or blocks Figure 1 or multiple blocks.

[0057] These computer program instructions can also be stored in a computer-readable memory that can direct a computer or other programmable data processing device to work in a specific manner, such that the instructions stored in the computer-readable memory produce a manufactured article including instruction means that implement the functions specified in one flow Figure 1 one flow or multiple flows and / or blocks Figure 1 or multiple blocks.

[0058] These computer program instructions can also be loaded onto a computer or other programmable data processing device to perform a series of operational steps on the computer or other programmable device to generate a computer-implemented process, such that the instructions executed on the computer or other programmable device provide steps for implementing the functions specified in one flow Figure 1 one flow or multiple flows and / or blocks Figure 1 or multiple blocks.

[0059] In the above embodiments, the descriptions of the various embodiments have their own focuses. For parts not detailed in a certain embodiment, reference can be made to the relevant descriptions of other embodiments.

[0060] The above are only the preferred embodiments of the present invention and are not intended to limit the present invention. For those skilled in the art, the present invention can have various modifications and changes. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included within the protection scope of the present invention.

Claims

1. A method for reconstructing discontinuous wing structure deformation based on tilt angle compensation, characterized in that: include: Obtaining calibrated strain data and calibrated displacement data of the discontinuous wing; According to the calibration method, the neutral plane thickness and inclination coefficient are calculated; According to the calibrated neutral plane thickness, inclination coefficient and reconstruction method, combined with the real-time strain value, the structural deformation reconstruction of the wing is completed.

2. A method for discontinuous wing structure deformation reconstruction based on tilt angle compensation as claimed in claim 1, characterized in that: The calibration method includes inclination coefficient calibration; The specific steps of the inclination coefficient calibration are: Calculate the additional inclination angle of the discontinuous wing, expressed as: In the formula, is the additional inclination angle; is the angle between the true displacement of the second wing and the horizontal direction; is the angle between the displacement reconstructed by Ko displacement theory and the horizontal direction; The additional inclination angle is proportional to the strain at a specific position of the second wing section, and the inclination coefficient is obtained, which is expressed as: In the formula, is the inclination coefficient; is the strain value.

3. The method for discontinuous wing structure deformation reconstruction based on tilt angle compensation according to claim 1, characterized in that: The calibration method also includes neutral plane thickness calibration; The neutral plane thickness calibration is specifically to divide the measured strain value by the second-order derivative of the true displacement curve at this point to obtain the calibrated thickness, which is expressed as: In the formula, is the neutral plane thickness; is the measured strain value; is the second-order derivative of the true displacement curve at this point.

4. The method for discontinuous wing structure deformation reconstruction based on tilt angle compensation according to claim 1, characterized in that: Before calculating the neutral plane thickness and the inclination coefficient, Ko theory analysis is also included. The specific derivation process is as follows: Assume that the length of the cantilever beam is , arranged at equal intervals along its length An FBG sensor is installed. In the area between two adjacent sensors, the neutral plane thickness function and strain function of the structure are expressed as linear functions. The slope function of the structure is obtained by integral calculation according to the structural differential equation. The neutral plane thickness function and strain function are substituted into the slope function to obtain the slope value at any position. The displacement function of the structure is obtained by two integral calculations according to the structural differential equation. The neutral plane thickness function and strain function are substituted into the displacement function to obtain the displacement value at any position.

5. The method for discontinuous wing structure deformation reconstruction based on tilt angle compensation according to claim 1, characterized in that: The reconstruction method includes calculating the corresponding additional inclination angle for compensation according to the strain and the inclination coefficient under the action of unknown load to obtain a compensated wing displacement curve, merging the wing displacement curve after the inclination angle compensation with the previous displacement curve at the endpoint to obtain the final discontinuous wing displacement curve, thereby realizing the deformation reconstruction of the discontinuous wing structure.

6. A method for discontinuous wing structure deformation reconstruction based on tilt angle compensation as claimed in claim 5, characterized in that: According to the inclination coefficient and the strain value under the unknown load, the additional inclination under this load is calculated and expressed as: In the formula, is the additional inclination angle; is the inclination coefficient; is the strain value.

7. A method for discontinuous wing structure deformation reconstruction based on tilt angle compensation as claimed in claim 6, characterized in that: According to the obtained additional inclination angle and the coordinate transformation principle, the wing displacement curve after inclination angle compensation is obtained, which is expressed as: In the formula, is the position coordinate of the second section of the wing after tilt compensation, is the displacement curve of the second section of the wing after tilt angle compensation, is the position coordinate of the second section of the wing, is the second wing displacement curve reconstructed based on Ko displacement.

8. A discontinuous wing structure deformation reconstruction system based on tilt angle compensation, characterized in that: include: An initialization module is configured to: obtain calibration strain data and calibration displacement data of a non-continuous wing; A calibration module is configured to: calculate the neutral plane thickness and the inclination coefficient according to a calibration method; The reconstruction module is configured to complete the structural deformation reconstruction of the wing according to the calibrated neutral plane thickness, inclination coefficient and reconstruction method combined with the real-time strain value.

9. An electronic device, characterized in that: The invention comprises a memory and a processor and computer instructions stored in the memory and executed on the processor. When the computer instructions are executed by the processor, the discontinuous wing structure deformation reconstruction method based on tilt angle compensation as described in any one of claims 1 to 7 is completed.

10. A computer-readable storage medium, characterized in that: Used to store computer instructions, which, when executed by a processor, complete the discontinuous wing structure deformation reconstruction method based on tilt angle compensation as described in any one of claims 1 to 7.

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