Deformation measuring device and method capable of following deformation of variable camber wing trailing edge

Abstract

The present application relates to a deformation measuring device and method capable of following the deformation of the trailing 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 installed with fiber grating sensors. The deformation beam is connected with the wing through sliding supports, positioning pins and other structures. According to the deformation characteristics of the trailing edge of the variable camber wing, a sliding connection mode is adopted in the large deformation area, and a fixed connection mode is adopted in the remaining area. After the deformation beam is connected with the wing structure, it can follow the deformation of the wing. The length change of the sliding connection area can be measured by the cable displacement sensor. The present application can solve the problems in the existing wing deformation measurement technology, such as the difficulty in directly measuring the large deformation of flexible structures, the difficulty in considering both large deformation and small deformation measurement, the error in the sensor manufacturing and installation process, and the like, and realize efficient and accurate wing trailing edge shape measurement.

Description

TECHNICAL FIELD

[0001] The present application relates to a deformation measurement device and method capable of following the deformation of the trailing edge of a variable camber wing, based on a beam-type optical fiber sensor, and proposes a sensor mounting method, a shape reconstruction algorithm, and a calibration method, and other technical means, to achieve the reconstruction of the shape of the trailing edge of the wing, and belongs to the field of wing deformation measurement. BACKGROUND

[0002] The design technology of flexible large deformation wing, especially variable camber wing, of a civil aircraft can continuously and smoothly adjust the camber of the wing according to the flight state in real time, so as to obtain optimal aerodynamic efficiency, and further achieve the purposes of drag reduction, weight reduction, and fuel consumption reduction of the aircraft. High-precision perception of the shape of the outer surface of the wing 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 has the characteristics of self-adaptation, but under the disturbance of aerodynamic force and inertial force, or under the condition of sudden wind in the flight direction or attitude change, it will produce serious deformation, which will pose a serious 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 problem in the field of aviation technology.

[0003] The commonly used wing measurement methods mainly include two types: one type is a non-contact measurement method using external devices such as stereo cameras and three-dimensional scanners, which generally has high measurement accuracy, but needs to arrange special instruments and equipment around the wing, which is limited in terms of operability and portability, and is difficult to meet the real-time monitoring requirements in actual flight state; the other type is a contact measurement method by pasting or embedding sensors on the measured object, such as directly pasting resistance strain gauges on the surface of the structure, and reconstructing the deformation of the structure according to the measured strain data of the structure. For the resistance strain gauge type deformation monitoring method, it is difficult to establish a distributed networking structure, and it is difficult to apply to large area measurement. When the number of strain gauges increases, more leads are needed, and the leads need to increase electromagnetic shielding layers to avoid noise interference, which will cause a significant increase in the weight of the structure, and it is difficult to apply to the wing structure for a long time.

[0004] The fiber Bragg grating (FBG) sensor is small in size, resistant to electromagnetic interference, and has strong designability. Using wavelength division multiplexing technology, multiple points of strain can be measured using one optical fiber, which greatly reduces the use of leads. The demodulation rate of the FBG sensor demodulation device is fast, light and small, and has been verified by flight test, and has strong adaptability to airborne environment. The above advantages make the FBG sensor a feasible solution for online measurement of wing deformation.

[0005] The present application is aimed at measuring the deformation of a variable camber wing trailing edge structure as shown in Figure 1 The variable camber wing trailing edge is mainly composed of three "knuckles" connected in series, each knuckle is driven by a motor and a connecting rod system, and in the deformation process, Figure 1The skin of the adjacent knuckle joint area in the wing will be deformed greatly, the skin of the area is made of flexible material of silicone rubber, and the skin of the remaining area is made of metal material. Because the skin is made of different materials spliced, the strain difference between the metal skin and the flexible skin is huge during the deformation process, the strain range of the flexible skin is far beyond the strain measurement range of the FBG sensor, and the connection structure between the two causes the inner surface to be uneven, so it is difficult to implement deformation measurement by commonly used means, such as directly pasting the FBG sensor on the surface of the skin. SUMMARY

[0006] The purpose of the present application 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. A "knuckle" variable-camber wing trailing edge structure is taken as the measurement object. In order to overcome the problems of the strain range of the fiber grating sensor being difficult to meet the large-deformation measurement requirements and the commonly used measurement method having many points and complex algorithm, the present application provides an indirect deformation measurement method based on a deformation beam, which can realize rapid and accurate measurement of large-deformation of the wing trailing edge structure.

[0007] In order to achieve the above-mentioned purpose of the application, the following technical solutions are adopted: a deformation measurement device capable of following the deformation of a variable-camber wing trailing edge, comprising a deformation beam 1, a plurality of sliding supports 2, and a wire displacement sensor 3; the deformation beam 1 is composed of an elongated beam 11 and two fiber grating sensors 12, is connected to the wing structure through a plurality of sliding supports 2 at a sliding connection area, and is connected through densely arranged positioning pins at a 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 grooves is provided with a recess for installing the fiber grating sensor 12, and the side surface of the beam 11 is provided with a circular hole for passing through the positioning pin; the fiber grating sensor 12 is fixedly connected with the beam 11, and the two ends of the wire of the wire displacement sensor 3 are fixedly connected with the sliding supports 2 at both ends of the sliding connection area.

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

[0009] The fiber grating sensor 12 is fixed with the beam 11 by glue.

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

[0011] The sliding support 2 is composed of a base 21, two bearings 22, and rubber sleeves 23, the base 21 is fixedly connected with the wing structure, the two bearings 22 are installed on two shafts perpendicular to the surface of the base 21, the rubber sleeves 23 are installed on the outer circular surface of the bearings 22, and the deformation beam 1 passes through the middle of the two bearings and rolls with the rubber sleeves 23.

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

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

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

[0015] The measurement method of the deformation measurement device capable of following the deformation of the trailing edge of the variable camber wing comprises the following steps:

[0016] S1: After the deformation measurement device is installed on the trailing edge of the variable camber wing, the trailing edge of the wing is controlled to deform to five typical states of an initial position, half of a maximum angle, a maximum angle, half of a maximum angle and a maximum angle, and actual shape data of the upper and lower surfaces of the deformation beam and the trailing edge of the variable camber wing in different states are obtained by using a laser tracker or other measuring equipment with similar functions; at the same time, data of the fiber bragg grating sensor 12 and the pull wire displacement sensor 3 in the deformation measurement device are collected and recorded;

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

[0018] S3: The displacement curve of the deformation beam is reconstructed by using a coordinate recursion method based on a homogeneous transformation general formula, and the length of the sliding connection region is corrected by using the length data obtained by the pull wire displacement sensor;

[0019] S4: The reconstruction error in different states is obtained from the actual shape data of the deformation beam 1, the error data of each FBG measuring point in different states is fitted in sections, and an error compensation curve is obtained;

[0020] S5: The positions of each FBG measuring point on the deformation beam displacement curve after the compensation error are selected, and the normal distance of each point on the upper and lower surfaces of the trailing edge of the variable camber wing is calculated;

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

[0022] S7: The upper and lower surface curves of a section of the trailing edge of the variable camber wing are obtained by the above steps, and the position data of the surface of the entire trailing edge of the variable camber wing is reconstructed by using a surface fitting method for the surface curves of multiple sections.

[0023] The beneficial effects of the present application are as follows:

[0024] The deformation measuring device can adapt to the deformation characteristics of different areas of the variable camber wing trailing edge. In the area where the mechanism deforms, the sliding connection mode is adopted due to the large deformation range, and the sliding connection mode is adopted in the area where the structure deforms, so that the trailing edge deformation is closely followed, and the problem that the traditional measuring mode is difficult to measure the shape of the flexible large deformation wing is solved.

[0025] In the area where the structure deforms, the fixed connection mode is adopted, the trailing edge deformation is closely followed, and the problem that the traditional measuring mode is difficult to measure the shape of the flexible large deformation wing is solved.

[0026] The wing shape algorithm matched with the deformation measuring device considers the errors that may occur in the actual manufacturing and installation process, calibrates the deformation measuring device by using a higher precision laser tracker, compensates the shape reconstruction error, and improves the reconstruction precision.

[0027] In the process of reconstructing the displacement curve of the deformation beam, the homogeneous transformation formula is used to realize the coordinate transformation, the process of calculating the homogeneous transformation matrix is simplified, and the calculation efficiency is improved.

[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 the discrete curvature data, and the adaptability and fitting accuracy of the complex curvature distribution are improved.

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

[0030] In order to more clearly illustrate the technical scheme of the present application, the drawings used in the embodiment description are described as follows:

[0031] Figure 1 The variable camber wing trailing edge basic structure is shown in the figure.

[0032] Figure 2 The figure is a schematic view of the deformation sensor.

[0033] Figure 3 The figure is a design of the sliding support and the deformation beam. Wherein: a is a schematic view of the cooperation relationship between the two, and b is a schematic view of the contact position of the rubber sleeve 23 and the deformation beam 1

[0034] Figure 4 The figure is a schematic view of the fixed connection mode.

[0035] Figure 5 The figure is a curvature measurement principle of the fiber grating sensor.

[0036] Figure 6 The figure is a schematic view of coordinate recursion.

[0037] Figure 7 This is a flowchart for shape reconstruction.

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

[0039] The present invention will be further described below with reference to the accompanying drawings:

[0040] To address the deformation characteristics of the trailing edge of a multi-joint variable-camber wing, this invention proposes a deformation measurement device. A deformation beam for sensing the shape is connected to the wing's trailing edge via both sliding and fixed connections, enabling synchronous tracking of the deformation. The device includes: a deformation beam 1, multiple sliding supports 2, and a wire displacement sensor 3; as shown... Figure 1 As shown, in the root regions of the first, second, and third phalanges, the relative motion between the phalanges is relatively large, and the skin strain range at the joint connection far exceeds the strain measurement range of the fiber optic grating sensor. Furthermore, the deformation of the phalange structure itself is relatively small. Therefore, a sliding method is used to connect the deformation beam 1 to the dispersed sliding supports 2, indirectly transferring the wing deformation to the deformation beam. In the distal region of the third phalange, the wing only undergoes structural deformation; therefore, the deformation beam 1 is fixedly connected to the wing structure, and here the wing deformation is directly transferred to the deformation beam 1. Figure 3 As shown, the deformable beam 1 consists of a slender beam 11 and two fiber Bragg grating sensors 12. In the sliding connection area, it is connected to the wing structure through multiple sliding supports 2, and in the fixed connection area, it is connected through densely arranged positioning pins. The cross-section of the beam 11 is transversely "I"-shaped, 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 Bragg grating sensor 12, and the side of the beam 11 is provided with a circular hole for the positioning pin to pass through. The fiber Bragg 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 both ends of the sliding connection area.

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

[0042] The fiber optic grating sensor 12 is fixed to the beam 11 with adhesive, which is a two-component epoxy adhesive.

[0043] The sliding support 2 consists of a base 21, two bearings 22 and a rubber sleeve 23. The base 21 is fixed to the wing structure by bolts. The two bearings 22 are mounted on two shafts perpendicular to the surface of the base 21. The rubber sleeve 23 is installed on the outer surface of the bearings 22. The deformable beam 1 passes through the middle of the two bearings and makes 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 deformation beam 1, so that the position where the rubber sleeve 23 contacts the deformation beam 1 is elastically deformed, avoiding the generation of a gap.

[0045] The rubber sleeve 23 is embedded into the guide groove on the deformation beam 1, avoiding lateral relative movement;

[0046] A circle of semicircular section grooves is designed in the middle of the outer circular surface of the rubber sleeve 23, and the pull rope of the pull wire displacement sensor 3 passes through the grooves.

[0047] The two ends of the pull rope of the pull wire displacement sensor 3 are fixedly connected with the sliding supports 2 at the two ends of the sliding connection area, and the routing path of the pull rope is the same as the optical fiber on the upper surface of the deformation beam, so that the length of the deformation beam 1 in the sliding connection area can be measured, which is used for registration with the reconstructed curve of the deformation beam, so as to calculate the accurate position of the end of the sliding connection area.

[0048] In the fixed connection area, as shown in Figure 4 , a plurality of positioning pins are used to fix the deformation beam and the third knuckle of the wing trailing edge, so that the deformation beam and the third knuckle can be deformed synchronously.

[0049] The deformations measured by 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, different deformation modes and deformation amounts of the variable camber wing trailing edge can be adapted, and accurate and comprehensive deformation information can be obtained.

[0050] Another aspect of the present application also provides a measurement method of the deformation measurement device, which has the following steps:

[0051] S1: After the variable camber wing trailing edge is installed with the above deformation measurement device, the deformation measurement device needs to be calibrated. First, control the wing trailing edge to deform to an initial position, to half of a maximum angle, to the maximum angle, to half of the maximum angle and to the maximum angle, etc. five typical states, and use a laser tracker or other measurement equipment with similar functions to obtain the actual shape data of the upper and lower surfaces of the deformation beam and the variable camber wing trailing edge in different states; at the same time, collect and record the data of the fiber grating sensor and the pull 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 in different states, the corresponding discrete curvature is calculated, and the measurement method is as shown in Figure 5 . Two fiber grating strings are pasted on the upper and lower surfaces of the deformation beam along the axial position. When the structure is bent, there is a strain difference between the two fiber grating sensors on the upper and lower surfaces, and the axial distance d of the fiber grating can calculate the curvature radius R of the point. Based on the known position of the fiber grating measuring point and the curvature radius data corresponding to each measuring point, the curvature distribution curve of the deformation beam can be obtained by curve fitting method.

[0053] In order to obtain a high-precision curvature distribution curve, the application designs a segmented fitting method, under the premise of obtaining the real shape data of the deformed beam, the deformed beam is divided into several segments according to the distribution of discrete curvature, the curvature change of each segment is ensured to be relatively gentle, and a quadratic polynomial y=ax 2 +bx+c is used for fitting the discrete curvature data corresponding to each segment, the fitted curves of each segment are connected, and the final fitting curve, i.e. the curvature distribution curve, is obtained.

[0054] S3: reconstruct the displacement curve of the deformed beam by adopting a coordinate recursion method based on a homogeneous transformation general formula, and correct the length of the sliding connection region by using the length data obtained by the tensioning displacement sensor;

[0055] The displacement curve coordinate recursion process is shown in Figure 6 . The displacement curve can be regarded as being composed of an infinite number of continuous micro-arc segments, the length of each micro-arc segment is set as Δs, the curvature k of the starting point of each micro-arc segment is known according to the curvature curve, and the reciprocal of the curvature k is the curvature radius r, i.e. the radius of the micro-arc segment. The pose of each point on the deformed curve is defined by using a coordinate system, and the coordinate system {1} in Figure 6 is taken as an example, the position thereof relative to the fixed coordinate system {0} is known, the origin O1 coincides with the starting point of the deformed curve, the direction of the coordinate axis O1x1 is the tangent direction of the deformed curve at O1, and O1y1 is the normal direction of the deformed curve. In the case where the coordinates of the O1 point are known, the coordinates of the O2 point can be obtained through coordinate transformation, and the specific process is as follows.

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

[0057]

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

[0059]

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

[0061]

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

[0063] The coordinates of the points O2, O3, etc. can be recursively calculated from O1 by repeating the above process. The coordinates of the i-th point O i The coordinates of the i-th point O

[0064]

[0065] The above process can be summarized as a coordinate recursive process. After the coordinates of the end points of all the micro-arc segments are obtained, the whole deformation beam displacement curve can be reconstructed by interpolation.

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

[0067] S4: The reconstructed deformation curve of the deformation beam 1 is subtracted from the data at the corresponding positions of the FBG measuring points in the real deformation curve, that is, the reconstruction error. Taking the actual deformation angle as the independent variable and the reconstruction error as the dependent variable, the error distribution curve is obtained by using the piecewise fitting method. In subsequent measurement, the error distribution curve is subtracted from the reconstructed deformation curve to compensate for the nonlinear error in the measurement link.

[0068] S5: This step is the last step of the calibration, and the purpose is to obtain the corresponding relationship between the profile curves of the upper and lower surfaces of the variable camber wing trailing edge and the deformation beam displacement curve. At the initial position of the trailing edge, the deformation beam in the sliding connection region is flat. At this time, the normal distance between each FBG measuring point and the upper and lower surfaces of the variable camber wing trailing edge is calculated. The method for solving the normal distance is as follows: based on the actual profile data of the upper and lower surfaces of the variable camber wing trailing edge, the upper and lower surface curves of the same section as the deformation beam are obtained. A perpendicular line of the deformation beam displacement curve is drawn through the selected measuring point, and the perpendicular line intersects the upper and lower surface curves, respectively, to generate two intersection points. The length of the line connecting the point position and the two intersection points is the normal distance to be solved.

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

[0070] S7: the upper and lower surface curves of a section of the variable camber wing trailing edge are obtained through the above steps, and for the surface curves of multiple sections, the position data of the entire variable camber wing trailing edge surface is reconstructed through the surface fitting method.

[0071] The processes of S6 and S7 can be represented by the flow chart in Figure 7 .

[0072] The above description is only part of the embodiments of the present application, and equivalent changes made according to the described method of the present application are included in the protection scope of the present application. The skilled in the art can make similar substitutions to the described specific examples, as long as they do not deviate from the structure of the present application or exceed the scope defined by the present claims, and they belong to the protection scope of the present application.

Claims

1. A deformation measuring device capable of following the deformation of a variable camber trailing edge, characterised in that, The device comprises a deformation beam (1), a plurality of sliding supports (2) and a cable displacement sensor (3). The deformation beam (1) is composed of an elongated beam (11) and two fiber bragg grating sensors (12). The deformation beam (1) is connected to the wing structure through the sliding supports (2) at the sliding connection area and through densely arranged positioning pins at the fixed connection area. The beam (11) is provided with guide grooves on the upper and lower surfaces for cooperation with the sliding supports (2). The middle part of the guide grooves is provided with a recess for mounting the fiber bragg grating sensor (12). The side surface of the beam (11) is provided with a circular hole for passing through the positioning pin. The fiber bragg grating sensor (12) is fixedly connected to the beam (11). The two ends of the cable of the cable displacement sensor (3) are fixedly connected to the sliding supports (2) at the two ends of the sliding connection area. The sliding support (2) is composed of a base (21), two bearings (22) and rubber sleeves (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 sleeves (23) are installed on the outer circular surface of the bearings (22). The deformation beam (1) passes through the middle of the two bearings and rolls with the rubber sleeves (23).

2. The morphing measurement device of claim 1, wherein, The beam (11) is made of elastic material.

3. The morphing measurement device of claim 1, wherein, The fiber bragg grating sensor (12) is fixedly connected to the beam (11) by glue.

4. The morphing measurement device of claim 3, wherein, The glue is two-component epoxy glue.

5. The morphing measurement device of claim 3, wherein, The minimum distance between the two rubber sleeves (23) is less than the thickness of the deformation beam (1).

6. The morphing measurement device of claim 3, wherein, The rubber sleeves (23) are embedded in the guide grooves on the deformation beam (1).

7. The morphing measurement device of claim 3, wherein, The outer circular surface of the rubber sleeve (23) is designed with a circular groove with a semicircular cross section. The cable of the cable displacement sensor (3) passes through the groove.

8. The method of measuring the deformation of a trailing edge of a variable camber wing according to any one of claims 1 to 7, wherein The device comprises the following steps: S1: After the deformation measuring device is installed on the trailing edge of the variable camber wing, the trailing edge is controlled to deform to five typical states, i.e. the initial position, half of the maximum angle, the maximum angle, half of the maximum angle and the maximum angle. The actual shape data of the deformation beam and the upper and lower surfaces of the trailing edge of the variable camber wing in different states are obtained by using a laser tracker or other measuring equipment with similar functions. At the same time, the data of the fiber bragg grating sensor (12) and the cable displacement sensor (3) in the deformation measuring device are collected and recorded. S2: The curvature of each point is calculated from the strain data of each FBG measuring point on the deformation beam (1), and the continuous curvature distribution curve is obtained by piecewise fitting. S3: The displacement curve of the deformation beam is reconstructed by using the coordinate recursion method based on the homogeneous transformation formula. The length of the sliding connection area is corrected by using the length data obtained by the cable displacement sensor. S4: The reconstruction error of the deformation beam (1) in different states is calculated from the actual shape data. The error compensation curve is obtained by piecewise fitting the error data of each FBG measuring point in different states. S5: The normal distance of each FBG measuring point on the trailing edge of the variable camber wing is calculated. S6: for any deformation state of the variable camber wing trailing edge, after obtaining the deformation beam displacement curve, the positions of the corresponding points on the upper and lower surfaces of the variable camber wing trailing edge are reversely solved according to the normal distance obtained in S5, and the upper and lower surface curves are obtained through fitting; S7: the upper and lower surface curves of a certain section of the variable camber wing trailing edge are obtained through the above steps, and for the surface curves of multiple sections, the position data of the entire variable camber wing trailing edge surface are reconstructed through the surface fitting method.

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