Deformation measuring device and method capable of deforming along with trailing edge of variable-camber wing

Abstract

The invention relates to a deformation measuring device and method capable of deforming along with the rear edge of a variable-camber wing, and belongs to the field of wing deformation measurement. The key component of the deformation measuring device is a deformation beam provided with a fiber grating sensor, the deformation beam is connected with the wing through a sliding support, a positioning pin and other structures, according to the deformation characteristics of the rear edge of the variable camber wing, a sliding connection mode is adopted in a large deformation area, and a fixed connection mode is adopted in the rest area. The deformation beam can deform along with a wing after being connected with the wing structure, and the length change of a sliding connection area can be measured through a stay wire displacement sensor. The problems that in an existing wing deformation measurement technology, large deformation generated by a flexible structure is difficult to directly measure, large deformation measurement and small deformation measurement are difficult to consider, errors exist in the sensor manufacturing and installing process and the like can be solved, and efficient and accurate wing trailing edge profile measurement is achieved.

Description

Technical Field

[0001] The present invention relates to a deformation measurement device and method capable of following the deformation of a trailing edge of a wing with variable curvature. Based on a beam-type optical fiber sensor, the present invention proposes technical means such as a sensor installation method, a shape reconstruction algorithm and a calibration method to achieve reconstruction of the shape of the trailing edge of the wing, and belongs to the field of wing deformation measurement. Background Art

[0002] Flexible large deformation wings for civil aircraft, especially variable camber wing design technology, can continuously and smoothly adjust the wing camber in real time according to the flight status, so as to obtain the optimal aerodynamic efficiency, and then achieve the goals of reducing aircraft drag, weight, and fuel consumption. High-precision perception of the shape of the wing outer surface is the key to accurately control the deformation of the flexible large deformation wing and obtain the required aerodynamic characteristics. The flexible large deformation wing itself has the characteristics of self-adaptation, but it will produce serious deformation under the conditions of aerodynamic and inertial force disturbances, or heading gusts, attitude changes, etc., which will pose a major threat to the stability and safety of the aircraft. Therefore, real-time monitoring of the deformation state of the flexible large deformation wing has become an important issue in the field of aviation technology.

[0003] Commonly used wing measurement methods are mainly divided into two categories: one is the non-contact measurement method using external devices such as stereo cameras and 3D scanners. Generally, the measurement accuracy is high, but special instruments and equipment need to be deployed around the wing, which is limited in the operability range and portability, and it is difficult to meet the real-time monitoring requirements of the actual flight status; the other is the method of attaching or embedding the sensor to the object to be measured for contact measurement, such as directly sticking resistance strain gauges on the surface of the structure, etc., and reconstructing the deformation of the structure based on the measured structural strain data. For the resistance strain gauge deformation monitoring method, it is impossible to establish a distributed networking structure, which is difficult to apply to large-area measurements. When the number of strain gauges increases, more leads are required, and the leads need to add an electromagnetic shielding layer to avoid noise interference, which will lead to a significant increase in the weight of the structure, making it difficult to apply it to the wing structure for a long time.

[0004] Fiber Bragg Grating (FBG) sensors are small in size, resistant to electromagnetic interference, and highly designable. Using wavelength division multiplexing technology, one optical fiber can measure multiple strain points, greatly reducing the use of leads. The demodulation equipment of the FBG sensor has a fast demodulation rate, is lightweight and compact, and has been flight-tested and has strong adaptability to airborne environments. The above advantages make FBG sensors a feasible solution for online measurement of wing deformation.

[0005] The present invention is directed to a Figure 1 The variable camber wing trailing edge structure shown in the figure is deformed. The variable camber wing trailing edge is mainly composed of three "fingers" connected in series, each of which is driven by a motor and a connecting rod system. During the deformation process, Figure 1The skin at the joint area of ​​adjacent knuckles will produce a large deformation. The skin in this area is made of silicone rubber flexible material, and the skin in the rest of the area is made of metal material. Since the skin is made of different materials, the strain difference between the metal skin and the flexible skin during deformation is huge. The strain range of the flexible skin far exceeds the strain measurement range of the FBG sensor, and the connection structure between the two causes the inner surface to be uneven. Therefore, it is difficult to implement deformation measurement by common means, such as directly sticking FBG sensors on the skin surface. Summary of the invention

[0006] The purpose of the present invention is to provide a measurement method for real-time monitoring of the shape of a flexible large deformation wing trailing edge using a fiber grating sensor. Taking a "knuckle-type" variable-camber wing trailing edge structure as the measurement object, in order to overcome the problems that the strain range measured by the fiber grating sensor is difficult to meet the large deformation measurement requirements and the commonly used measurement methods have many points and complex algorithms, the present invention provides an indirect deformation measurement method based on a deformation beam, which can realize rapid and accurate measurement of large-scale deformation of the wing trailing edge structure.

[0007] To achieve the above-mentioned invention purpose, the present invention adopts the following technical scheme: a deformation measuring device capable of following the deformation of the trailing edge of a wing with variable curvature, comprising a deformation beam 1, a plurality of sliding supports 2, and a pull-wire displacement sensor 3; the deformation beam 1 is composed of a slender beam 11 and two fiber optic grating sensors 12, which are connected to the wing structure through a plurality of sliding supports 2 in the sliding connection area and are connected through densely arranged positioning pins in the fixed connection area; the upper and lower surfaces of the beam 11 are provided with guide grooves for cooperating with the sliding supports 2, the middle part of the guide groove is provided with a groove for installing the fiber optic grating sensor 12, and a circular hole for passing the positioning pin is provided on the side of the beam 11; the fiber optic grating sensor 12 is fixedly connected to the beam 11, and the two ends of the pull rope of the pull-wire displacement sensor 3 are respectively fixedly connected to the sliding supports 2 at the two ends of the sliding connection area.

[0008] The beam 11 is made of elastic material.

[0009] The fiber grating sensor 12 and the beam 11 are fixed by glue.

[0010] The glue is a two-component epoxy glue.

[0011] The sliding support 2 is composed of a base 21, two bearings 22 and a rubber sleeve 23. The base 21 is fixedly connected to the wing structure. The two bearings 22 are installed on two shafts perpendicular to the surface of the base 21. The rubber sleeve 23 is installed on the outer circumferential surface of the bearing 22. The deformable beam 1 passes through the middle of the two bearings and produces rolling contact with the rubber sleeve 23.

[0012] The minimum distance between the two rubber sleeves 23 is smaller than the thickness of the deformable beam 1 .

[0013] The rubber sleeve 23 is embedded in the guide groove on the deformation beam 1 .

[0014] A groove with a semicircular cross-section is designed in the middle of the outer circumferential surface of the rubber sleeve 23, and the pull rope of the pull-wire displacement sensor 3 passes through the groove.

[0015] A measuring method of a deformation measuring device capable of following the deformation of a trailing edge of a wing with variable camber comprises the following steps:

[0016] S1: After installing the above deformation measurement device for the trailing edge of the variable-camber wing, control the deformation of the trailing edge of the wing to five typical states: initial position, upward deflection to half of the maximum angle, upward deflection to the maximum angle, downward deflection to half of the maximum angle and downward deflection to the maximum angle, and use a laser tracker or other measuring equipment with similar functions to obtain the actual shape data of the upper and lower surfaces of the deformation beam and the trailing edge of the variable-camber wing under different states; at the same time, collect and record the data of the fiber grating sensor 12 and the wire displacement sensor 3 in the deformation measurement device;

[0017] S2: The curvature of each point is calculated from the strain data of each FBG measuring point on the deformed beam 1, and a continuous curvature distribution curve is obtained by a piecewise fitting method;

[0018] S3: The displacement curve of the deformed beam is reconstructed by using the coordinate recursion method based on the homogeneous transformation formula, and the length data obtained by the wire displacement sensor is used to correct the length of the sliding connection area;

[0019] S4: Calculate the reconstruction error under different states from the actual shape data of the deformed beam 1, perform piecewise fitting on the error data of each FBG measuring point under different states, and obtain an error compensation curve;

[0020] S5: Select the position of each FBG measuring point on the displacement curve of the deformed beam after error compensation, and calculate the normal distance between each point and the upper and lower surfaces of the trailing edge of the variable-camber wing;

[0021] S6: for any deformation state of the trailing edge of the variable camber wing, after obtaining the deformation beam displacement curve, the positions of the corresponding points on the upper and lower surfaces of the trailing edge of the variable camber wing are inversely calculated according to the normal distance calculated in S5, and the upper and lower surface curves are obtained by fitting;

[0022] S7: The above steps obtain the upper and lower surface curves of a certain section in the trailing edge of the variable-camber wing. For the surface curves of multiple sections, the position data of the entire trailing edge surface of the variable-camber wing is reconstructed by a surface fitting method.

[0023] Beneficial effects of the present invention:

[0024] The deformation measuring device proposed in the present invention can adapt to the deformation characteristics of different areas of the trailing edge of the variable-camber wing. In the area where the mechanism deformation occurs, due to the large deformation amplitude, a sliding connection with the wing structure is adopted;

[0025] In areas where structural deformation occurs, a fixed connection method is used to achieve "close following" of the deformation of the trailing edge, solving the problem that traditional measurement methods are difficult to measure for flexible and large deformation wing shapes.

[0026] The wing shape algorithm matched with the deformation measurement device proposed in the present invention takes into account the errors that may occur in the actual manufacturing and installation process, and uses a higher-precision laser tracker to calibrate the deformation measurement device to compensate for the shape reconstruction error and improve the reconstruction accuracy;

[0027] In the process of reconstructing the displacement curve of the deformed beam, the coordinate transformation is realized by using the homogeneous transformation formula, which simplifies the process of calculating the homogeneous transformation matrix and improves the calculation efficiency.

[0028] The accuracy of the curvature distribution curve is related to the reconstruction accuracy of the displacement curve. The piecewise fitting method is used to realize the continuity of discrete curvature data, which improves the adaptability and fitting accuracy to complex curvature distribution conditions.

[0029] Based on the normal distance, the surface shape curve of the variable-camber wing can be calculated from the deformed beam curve and fitted into the shape surface. The aerodynamic shape data can be obtained in real time without installing a shape sensor on the wing skin, thus avoiding the influence of sensor installation on the aerodynamic shape of the wing. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] In order to more clearly illustrate the technical solution of the present invention, the following is a description of the drawings used in the description of the embodiments:

[0031] Figure 1 It is the basic structure of the trailing edge of the variable camber wing;

[0032] Figure 2 is a schematic diagram of a deformation sensor;

[0033] Figure 3 Design of the sliding support and the deformable beam; wherein: a is a schematic diagram of the matching relationship between the two, and b is a schematic diagram of the contact position of the rubber sleeve 23 and the deformable beam 1

[0034] Figure 4 It is a schematic diagram of fixed connection mode;

[0035] Figure 5 The curvature measurement principle of fiber Bragg grating sensor;

[0036] Figure 6 This is a schematic diagram of coordinate recursion;

[0037] Figure 7 Refactor the flow chart for shapes.

[0038] Among them: 1-deformation beam, 2-multiple sliding supports, 3-wire displacement sensor, 11-beam, 12-two fiber grating sensors, 21-base, 22-bearing, 23-rubber sleeve. DETAILED DESCRIPTION

[0039] The present invention is further described below in conjunction with the accompanying drawings:

[0040] Aiming at the deformation characteristics of the trailing edge of a variable-camber wing with a multi-joint structure, the present invention proposes a deformation measurement device, in which a deformation beam for sensing shape is connected to the trailing edge of the wing by sliding connection and fixed connection respectively, so as to achieve synchronous tracking of the deformation. The device comprises: a deformation beam 1, a plurality of sliding supports 2, and a wire displacement sensor 3; Figure 1 As shown, in the root area of ​​the first, second and third knuckles, the relative movement between the knuckles is large, the skin strain range at the joint connection far exceeds the strain measurement range of the fiber grating sensor, and the deformation of the knuckle structure itself is relatively small, so the deformation beam 1 is connected to the dispersed sliding support 2 in a sliding manner to indirectly transfer the wing deformation to the deformation beam; in the end area of ​​the third knuckle, the wing only undergoes structural deformation, so the deformation beam 1 is fixedly connected to the wing structure, and the deformation of the wing here is directly transferred to the deformation beam 1. Figure 3 As shown, the deformable beam 1 is composed of a slender beam 11 and two fiber grating sensors 12, which are connected to the wing structure through multiple sliding supports 2 in the sliding connection area and connected through densely arranged positioning pins in the fixed connection area; the cross-section of the beam 11 is in a transverse "I" shape, and the upper and lower surfaces are provided with guide grooves for cooperating with the sliding supports 2, the middle of the guide groove is provided with a groove for installing the fiber grating sensor 12, and a circular hole for passing the positioning pin is provided on the side of the beam 11; the fiber grating sensor 12 is fixedly connected to the beam 11, and the two ends of the pull rope of the wire displacement sensor 3 are respectively fixedly connected to the sliding supports 2 at the two ends of the sliding connection area.

[0041] The beam 11 is made of elastic material.

[0042] The fiber grating sensor 12 and the beam 11 are fixed by glue, and the glue is a two-component epoxy glue.

[0043] The sliding support 2 is composed of a base 21, two bearings 22 and a rubber sleeve 23. The base 21 is fixedly connected to the wing structure by bolts. The two bearings 22 are installed on two shafts perpendicular to the surface of the base 21. The rubber sleeve 23 is installed on the outer circumferential surface of the bearing 22. The deformation beam 1 passes through the middle of the two bearings and produces rolling contact with the rubber sleeve 23.

[0044] The minimum distance between the two rubber sleeves 23 is slightly smaller than the thickness of the deformable beam 1 , so that the position where the rubber sleeves 23 contact the deformable beam 1 is elastically deformed to avoid the generation of gaps.

[0045] The rubber sleeve 23 is embedded in the guide groove on the deformable beam 1 to avoid lateral relative movement;

[0046] A groove with a semicircular cross-section is designed in the middle of the outer circumferential surface of the rubber sleeve 23, and the pull rope of the pull-wire displacement sensor 3 passes through the groove.

[0047] The two ends of the pull rope of the pull-wire displacement sensor 3 are respectively fixedly connected to the sliding supports 2 at both ends of the sliding connection area. The routing path of the pull rope is the same as the optical fiber on the upper surface of the deformable beam. The length of the deformable beam 1 in the sliding connection area can be measured, which is used to align with the curve reconstructed by the deformable beam, thereby calculating the precise position of the end of the sliding connection area.

[0048] In the fixed connection area, such as Figure 4 As shown, the deformation beam and the third finger joint of the wing trailing edge are fixed by a plurality of positioning pins, so that the deformation beam and the third finger joint can be deformed synchronously.

[0049] The deformations measured in the sliding connection area and the fixed connection area can be combined to obtain the overall deformation of the wing. Through this segmented measurement method, it is possible to adapt to the different deformation modes and deformation amounts of the trailing edge of the variable camber wing and obtain accurate and comprehensive deformation information.

[0050] Another aspect of the present invention further provides a measurement method of the deformation measuring device, the method comprising the following steps:

[0051] S1: After installing the above deformation measurement device for the trailing edge of the variable-camber wing, the deformation measurement device needs to be calibrated. First, control the deformation of the trailing edge of the wing to five typical states, namely, the initial position, the upper deflection to half of the maximum angle, the upper deflection to the maximum angle, the lower deflection to half of the maximum angle, and the lower deflection to the maximum angle. Use a laser tracker or other measuring equipment with similar functions to obtain the actual shape data of the upper and lower surfaces of the deformation beam and the trailing edge of the variable-camber wing under different states; at the same time, collect and record the data of the fiber grating sensor and the wire displacement sensor in the deformation measurement device;

[0052] S2: Based on the strain data of each measuring point of the fiber grating sensor 12 under different states, the corresponding discrete curvature is calculated. The measurement method is as follows: Figure 5 As shown. Two fiber Bragg grating strings are pasted along the axial position on the upper and lower surfaces of the deformable beam. When the structure bends, there is a strain difference between the two fiber Bragg grating sensors on the upper and lower surfaces. The axis spacing d of the fiber Bragg grating can be used to calculate the curvature radius R of the point. Based on the known fiber Bragg grating measurement point position and the curvature radius data corresponding to each measurement point, the curvature distribution curve of the deformable beam can be obtained by curve fitting.

[0053] In order to obtain a high-precision curvature distribution curve, the present invention designs a segmented fitting method. On the premise that the real shape data of the deformed beam has been obtained, the deformed beam is divided into several segments according to the distribution of discrete curvatures to ensure that the curvature change of each segment is relatively gentle. The quadratic polynomial y=ax 2 +bx+c fits the discrete curvature data corresponding to each segment, connects the fitted curves, and obtains the final fitting curve, that is, the desired curvature distribution curve.

[0054] S3: The displacement curve of the deformed beam is reconstructed by using the coordinate recursion method based on the homogeneous transformation formula, and the length data obtained by the wire displacement sensor is used to correct the length of the sliding connection area;

[0055] The displacement curve coordinate recursion process is as follows Figure 6 The displacement curve can be regarded as composed of countless continuous micro-arcs. The length of each micro-arc is set to Δs. According to the curvature curve, the curvature k of each micro-element starting point can be known. The reciprocal of the curvature radius r is the radius of the micro-arc. The position and posture of each point on the deformation curve are defined by the coordinate system. Figure 6 Take the coordinate system {1} in the figure as an example. Its position relative to the fixed coordinate system {0} is known. The origin O1 coincides with the starting point of the deformation curve. The direction of the coordinate axis O1x1 is the tangent direction of the deformation curve at O1, and O1y1 is the normal direction of the deformation curve. When the coordinates of point O1 are known, the coordinates of point O2 can be obtained by coordinate transformation. The specific process is as follows.

[0056] The process of transforming the coordinate system {1} to {2} can be regarded as the process of {1} rotating around the distance point P1 by an angle θ1. Since the curvature radius r1 and the micro-arc length Δs of the point O1 on the deformation curve are known, the rotation angle θ1 can be calculated by the following formula.

[0057]

[0058] Let the homogeneous coordinates of point O1 be [a1,b1,c1,1] T , the homogeneous coordinates of point O2 are [a2,b2,c2,1] T , let vector K1 = k x i+k y j+k z k passes through point P1 = [px1, py1, pz1] T , and is the axis of rotation of the coordinate system {1} to {2}, through the homogeneous transformation matrix The conversion between the two can be realized, and the matrix form is as follows:

[0059]

[0060] The transformation matrix in the above formula is is the general formula of the homogeneous transformation matrix, where P1 is its coordinate [0,r1,0] relative to the coordinate system {1} T , R(K,θ) is the general formula of the rotation matrix, and its specific form is as follows:

[0061]

[0062] In the above formula, sθ=sinθ, cθ=cosθ, versθ=(1-cosθ).

[0063] By repeating the above process, we can recursively calculate the coordinates of points O2, O3, etc. starting from O1. i , its coordinates can be calculated by the following formula.

[0064]

[0065] The above process can be summarized as a coordinate recursion process. After the endpoint coordinates of all micro-arcs are obtained, the displacement curve of the entire deformed beam can be reconstructed by interpolation.

[0066] Since the deformation range of the sliding connection area is large and the relative distance between the sliding supports changes significantly, the length measured by the wire displacement sensor can accurately obtain the length of the deformed beam in the sliding connection area, which is convenient for comparison with the actual shape curve.

[0067] S4: The reconstruction error is obtained by subtracting the data of the corresponding position of the FBG measuring point in the real deformation curve from the reconstructed deformation curve of the deformed beam 1. The actual deformation angle is used as the independent variable and the reconstruction error is used as the dependent variable. The error distribution curve is obtained by the same piecewise fitting method. In subsequent measurements, the error distribution curve is subtracted from the reconstructed deformation curve to compensate for the nonlinear error in the measurement process.

[0068] S5: This step is the last step of calibration, and its purpose is to obtain the corresponding relationship between the upper and lower surface shape curves of the trailing edge of the variable camber wing and the displacement curve of the deformation beam. At the initial position of the trailing edge, the deformation beam in the sliding connection area is straight. At this time, the normal distance between each FBG measuring point and the upper and lower surfaces of the trailing edge of the variable camber wing is calculated. The method for solving the normal distance is to obtain the upper and lower surface curves with the same cross-section as the deformation beam based on the actual shape data of the upper and lower surfaces of the trailing edge of the variable camber wing, and draw a perpendicular line of the deformation beam displacement curve through the selected measuring point, which intersects with the upper and lower surface curves respectively to generate two intersection points. The length of the line connecting the point and the two intersection points is the normal distance required.

[0069] S6: for any deformation state of the trailing edge of the variable camber wing, after obtaining the deformation beam displacement curve, the positions of the corresponding points on the upper and lower surfaces of the trailing edge of the variable camber wing are inversely calculated according to the normal distance calculated in S5, and the upper and lower surface curves are obtained by fitting;

[0070] S7: The above steps obtain the upper and lower surface curves of a certain section in the trailing edge of the variable-camber wing. For the surface curves of multiple sections, the position data of the entire trailing edge surface of the variable-camber wing is reconstructed by a surface fitting method.

[0071] The S6 and S7 processes are available Figure 7 The flowchart in is shown.

[0072] The above is only a part of the embodiments of the present invention. Equivalent changes made according to the method described in the present invention are all included in the protection scope of the present invention. Those skilled in the art of the present invention can replace the specific examples described in a similar manner, as long as they do not deviate from the structure of the present invention or exceed the scope defined by the claims, they all belong to the protection scope of the present invention.

Claims

1. A deformation measuring device capable of following the deformation of the trailing edge of a wing with variable camber, characterized in that: The invention comprises a deformable beam (1), a plurality of sliding supports (2), and a wire displacement sensor (3); the deformable beam (1) is composed of a slender beam (11) and two fiber optic grating sensors (12); the deformable beam (1) is connected to the wing structure in the sliding connection area through the plurality of sliding supports (2), and is connected in the fixed connection area through densely arranged positioning pins; the upper and lower surfaces of the beam (11) are provided with guide grooves for cooperating with the sliding supports (2); the middle of the guide groove is provided with a groove for installing the fiber optic grating sensor (12); and the side of the beam (11) is provided with a circular hole for passing the positioning pin; the fiber optic grating sensor (12) is fixedly connected to the beam (11), and the two ends of the wire displacement sensor (3) are respectively fixedly connected to the sliding supports (2) at the two ends of the sliding connection area.

2. The deformation measuring device capable of following the deformation of the trailing edge of a wing with variable camber according to claim 1, characterized in that: The beam (11) is made of elastic material.

3. The deformation measuring device capable of following the deformation of the trailing edge of a wing with variable camber according to claim 1, characterized in that: The fiber grating sensor (12) and the beam (11) are fixed by glue.

4. The deformation measuring device capable of following the deformation of the trailing edge of a wing with variable camber according to claim 3, characterized in that: The glue is a two-component epoxy glue.

5. The deformation measuring device capable of following the deformation of the trailing edge of a wing with variable camber according to claim 3, characterized in that: The sliding support (2) is composed of a base (21), two bearings (22) and a rubber sleeve (23); the base (21) is fixedly connected to the wing structure; the two bearings (22) are mounted on two shafts perpendicular to the surface of the base (21); the rubber sleeve (23) is mounted on the outer circumferential surface of the bearing (22); the deformation beam (1) passes through the middle of the two bearings and generates rolling contact with the rubber sleeve (23).

6. The deformation measuring device capable of following the deformation of the trailing edge of a wing with variable camber according to claim 3, characterized in that: The minimum distance between the two rubber sleeves (23) is smaller than the thickness of the deformable beam (1).

7. The deformation measuring device capable of following the deformation of the trailing edge of a wing with variable camber according to claim 3, characterized in that: The rubber sleeve (23) is embedded in the guide groove on the deformation beam (1).

8. The deformation measuring device capable of following the deformation of the trailing edge of a wing with variable camber according to claim 3, characterized in that: A groove with a semicircular cross-section is designed in the middle of the outer circumferential surface of the rubber sleeve (23), and the drawstring of the drawstring displacement sensor (3) passes through the groove.

9. The measuring method of the deformation measuring device capable of following the deformation of the trailing edge of a wing with variable camber according to any one of claims 1 to 8, characterized in that: The following steps are involved: S1: After installing the above deformation measurement device for the trailing edge of the variable-camber wing, the trailing edge of the wing is controlled to deform to five typical states: initial position, upward deflection to half of the maximum angle, upward deflection to the maximum angle, downward deflection to half of the maximum angle, and downward deflection to the maximum angle. A laser tracker or other measuring equipment with similar functions is used to obtain actual shape data of the upper and lower surfaces of the deformation beam and the trailing edge of the variable-camber wing under different states; at the same time, data of the fiber grating sensor 12 and the wire displacement sensor (3) in the deformation measurement device are collected and recorded; S2: The curvature of each point is calculated from the strain data of each FBG measuring point on the deformed beam 1, and a continuous curvature distribution curve is obtained by a piecewise fitting method; S3: The displacement curve of the deformed beam is reconstructed by using the coordinate recursion method based on the homogeneous transformation formula, and the length data obtained by the wire displacement sensor is used to correct the length of the sliding connection area; S4: Calculate the reconstruction error under different states from the actual shape data of the deformed beam 1, perform piecewise fitting on the error data of each FBG measuring point under different states, and obtain an error compensation curve; S5: Select the position of each FBG measuring point on the displacement curve of the deformed beam after error compensation, and calculate the normal distance between each point and the upper and lower surfaces of the trailing edge of the variable-camber wing; S6: for any deformation state of the trailing edge of the variable camber wing, after obtaining the deformation beam displacement curve, the positions of the corresponding points on the upper and lower surfaces of the trailing edge of the variable camber wing are inversely calculated according to the normal distance calculated in S5, and the upper and lower surface curves are obtained by fitting; S7: The above steps obtain the upper and lower surface curves of a certain section in the trailing edge of the variable-camber wing. For the surface curves of multiple sections, the position data of the entire trailing edge surface of the variable-camber wing is reconstructed by a surface fitting method.

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