Adaptive bidirectional flexible morphing wing structure and optimization method thereof

Abstract

The application discloses a kind of self-adapting bidirectional flexible deformation wing structure and its optimization method, including rib belt structure, driving rod and two telescopic rods;Two telescopic rods are vertically fixedly connected at the both ends of rib belt structure;Rib belt structure includes multiple groups of reinforcing ribs and ordinary ribs;Multiple groups of reinforcing ribs are evenly and parallelly arranged, and multiple groups of ordinary ribs are evenly and parallelly arranged between adjacent two groups of reinforcing ribs;Reinforcing rib includes rib plate outer contour, and its sequentially connected leading edge deformation zone, middle rigid fixed support zone and trailing edge deformation zone, and the end of leading edge deformation zone and trailing edge deformation zone away from middle rigid fixed support zone is evenly fixedly connected on telescopic rod respectively, and rib plate outer contour is fixedly connected with multiple groups of U-shaped connecting pieces.The structure does not need complex mechanical deflection structure, and the structure design is simple, with small additional weight and easy to process.The optimization method based on the structure can adaptively optimize deformation parameters according to flight speed.

Description

Technical Field

[0001] This invention relates to the field of aircraft, specifically to an adaptive bidirectional flexible deformable wing structure and its optimization method. Background Technology

[0002] Modern aircraft need to achieve flight performance across variable speed ranges, including low-speed, subsonic, transonic, and supersonic, to significantly improve combat effectiveness, depending on the specific combat mission, battlefield environment, and target. However, the aerodynamic characteristics of the flow around each speed range differ greatly. A fixed aerodynamic shape will experience a decrease in aerodynamic performance under non-designed flight conditions. This necessitates the design of deformable aerodynamic configurations that actively change the aerodynamic shape according to changes in the flight mission and environment to obtain better lift-drag, handling stability, and control characteristics, thereby increasing the aircraft's flight envelope. As a primary aerodynamic component, the development of variability technology for wings has become a crucial pathway for future performance breakthroughs in variable speed range aircraft.

[0003] Traditional deformable wings, such as leading-edge slats and trailing-edge flaps, employ rigid mechanical structures, as shown in Figures 1(a), 1(b), and 1(c). The disadvantages of this type of deformable wing are as follows:

[0004] First, the structure is complex and the added weight is large;

[0005] Second, the gap between the variable surface and the main wing surface leads to excessive fuselage noise and vibration;

[0006] Third, the deformation range is limited, and it can often only achieve small local deformation. Summary of the Invention

[0007] To address the problems existing in the aforementioned fields, this invention designs an adaptive bidirectional flexible deformable wing structure. This structure can adaptively change the chordal camber and span of the wing according to changes in flight speed to obtain better lift-drag characteristics. The structure can achieve significant deformation in both the chordal and spanwise directions, maintaining the overall structural integrity of the wing throughout the deformation process, resulting in a smooth, gapless deformed shape. This structure eliminates the need for complex mechanical deflection structures, features a simple deformable structure, minimal added weight, and is easy to manufacture. Based on this structure, an optimization method for the adaptive bidirectional flexible deformable wing structure is proposed, which can adaptively optimize deformation parameters according to flight speed.

[0008] To address the aforementioned technical problems, this invention provides an adaptive bidirectional flexible deformable wing structure and its optimization method, the structure comprising a ribbed structure, a drive rod, and two telescopic rods;

[0009] The two telescopic rods are vertically fixedly connected to both ends of the rib structure;

[0010] The rib structure includes multiple sets of reinforcing ribs and multiple sets of ordinary ribs; the multiple sets of reinforcing ribs are evenly and parallelly arranged, and the multiple sets of ordinary ribs are evenly and parallelly arranged between adjacent sets of reinforcing ribs;

[0011] The reinforcing rib includes an outer contour of a rib plate, and a leading edge deformation zone, a middle rigid support zone, and a trailing edge deformation zone connected sequentially within the outer contour of the rib plate. The ends of the multiple leading edge deformation zones and the trailing edge deformation zones away from the middle rigid support zone are uniformly fixedly connected to the two telescopic rods. The outer contours of the multiple sets of ordinary ribs and the multiple sets of reinforcing ribs are fixedly connected to multiple sets of U-shaped connectors, and the outer surfaces of the multiple sets of U-shaped connectors are provided with elastic skins. The leading edge deformation zone and the trailing edge deformation zone each include a comb-shaped structure, elastic filling material between the teeth, and shape memory alloy wire. A shape memory alloy wire is provided below each elastic filling material, passing through the end of each comb-shaped structure near the elastic material, and is fixedly connected to each comb-shaped structure. The tips of the comb-shaped structures are tangent to the outer contour of the rib plate.

[0012] Preferably, the telescopic rod is a sleeve structure.

[0013] Preferably, the elastic skin covers the entire outer surface of the wing and is fixedly connected to the outer contour of the mid-section rigid support area, and is slidably connected to the outer contours of the leading edge deformation area and the trailing edge deformation area.

[0014] Preferably, the elastic skin is made of 7075A rubber.

[0015] Preferably, the U-shaped connector is made of nylon alloy or nylon carbon fiber material.

[0016] Preferably, the middle rigid support area is fixedly sleeved around the drive rod; multiple sets of ordinary ribs are slidably sleeved around the drive rod.

[0017] Preferably, the method further includes an optimization method for an adaptive bidirectional flexible deformable wing structure, the optimization method comprising the following steps:

[0018] The deflection angle generated by the leading-edge deformation zone and the mid-section rigid support zone is defined as the leading-edge deflection angle. Similarly, the deflection angle generated by the aforementioned trailing edge deformation zone and the mid-section rigid support zone is defined as the trailing edge deflection angle. The deformable shape of the wing structure is described by the leading edge deflection angle. Trailing edge deflection angle and spanwise elongation The three characteristic geometric parameters describe the process, wherein the spanwise scaling factor is defined as follows:

[0019] (1)

[0020] in,L 0 Original wing span, Elongation;

[0021] The finite element method is used to perform calculations and analyses to obtain the geometric parameters of deformation characteristics. , , The corresponding deformed shape;

[0022] Computational fluid dynamics methods are used to obtain the airfoil surface pressure distribution in the airflow field, thereby obtaining the aerodynamic performance index lift-to-drag ratio. Boost-to-drag ratio and characteristic geometric parameters , , The following functional relationship exists between them:

[0023] (2)

[0024] Transform the structural deformation strategy optimization problem into a parameter optimization problem:

[0025] seek , so that:

[0026] (3)

[0027] In the formula, the function This is the cost function, i.e., the performance metric;

[0028] The optimal solution is obtained using the steepest descent method. The aerodynamic model is obtained by using the feature-complete orthogonal decomposition method. Then, the performance indicators of the target shape are obtained by solving the aerodynamic model using the surrogate model method. ;

[0029] According to performance indicators To determine the deformable shape of the wing structure.

[0030] Preferably, the surrogate model method is used to obtain the performance indicators of the target shape through an aerodynamic model. This includes the following steps:

[0031] The sample space is obtained by sampling in the design space using orthogonal design methods;

[0032] The deformable shape coordinate matrix of each sample was obtained using structural and aerodynamic numerical simulation methods. and the flow field pressure distribution matrix in the shape ;Will and Combining the results, we obtain the augmented snapshot matrix. :

[0033] (4)

[0034] S1: Pressure distribution on the target shape Initialize :

[0035] (5)

[0036] In the formula, for Average flow field pressure distribution on the shape of each sample: ;

[0037] S2: For augmented snapshot matrix Perform orthogonal decomposition of features and obtain the frontier features. Orthogonal decomposition method for missing features:

[0038] (6)

[0039] but The singular value decomposition is ;

[0040] in, And there is:

[0041] (7)

[0042] in, .also The singular value decomposition satisfies:

[0043] (8)

[0044] orthogonal decomposition method for missing features The maximum value problem is satisfied.

[0045] (9)

[0046] in, express Inner product operation of space, y j Indicates the first j An augmented snapshot vector of a deformed shape. u i , u j Indicates the first i , j The modal vector of order;

[0047] By constructing a matrix Perform missing feature orthogonal decomposition mode Solve the following eigenvalue problem:

[0048] (10)

[0049] Then we have:

[0050] (11)

[0051] In the formula, eigenvalues Characterizing the modes of the orthogonal decomposition method with missing features Contribution to the total energy of the flow field, before The proportion of the missing characteristic orthogonal decomposition mode in the total energy of the flow field is determined by the following formula:

[0052] (12)

[0053] S3: Before using Pressure distribution of target shape in modal update using orthogonal decomposition method for missing features :

[0054] (13)

[0055] in, a i These are the unsteady modal coefficients, obtained by least squares estimation. k Let be the number of iterations. At this point, if the error... Meets accuracy value EPS Require:

[0056] (14)

[0057] The algorithm then stops. For the target shape pressure distribution, otherwise return the augmented snapshot matrix. Perform orthogonal decomposition of features to enter the next iteration until formula (14) is satisfied.

[0058] Compared with the prior art, the present invention has the following beneficial effects:

[0059] This invention discloses an adaptive two-way flexible deformable wing structure and its optimization method, comprising a rib structure, a drive rod, and two telescopic rods; the two telescopic rods are vertically fixedly connected to both ends of the rib structure; the rib structure includes multiple sets of reinforcing ribs and ordinary ribs; the multiple sets of reinforcing ribs are uniformly and parallelly arranged, and the multiple sets of ordinary ribs are uniformly and parallelly arranged between adjacent sets of reinforcing ribs; the reinforcing ribs include the outer contour of the rib plate, and a leading-edge deformation zone, a mid-section rigid support zone, and a trailing-edge deformation zone connected thereto in sequence; the ends of the leading-edge and trailing-edge deformation zones away from the mid-section rigid support zone are uniformly and fixedly connected to the telescopic rods, and the outer contour of the rib plate is fixedly connected to multiple sets of U-shaped connectors. Compared with single-dimensional deformation, this two-way deformable structure has stronger deformation capability, achieving deformation in both chord and spanwise directions. The deformable shape of the wing structure is continuous, smooth, and seamless, which is beneficial to improving the aerodynamic performance of the wing. This structure does not require a complex mechanical deflection structure, is simple in structure, has low added weight, and is easy to manufacture. Furthermore, a deformation parameter optimization design method is proposed based on this structure, which can adaptively optimize the deformation parameters according to the flight speed. Attached Figure Description

[0060] Figure 1(a) is an example diagram of the gap between the leading edge slat and the main wing;

[0061] Figure 1(b) is an example diagram of gap aerodynamic noise;

[0062] Figure 1(c) is an example diagram of the leading edge deflection mechanical structure;

[0063] Figure 2 This is an overall structural diagram of the wing of the present invention;

[0064] Figure 3 This is a partially enlarged view of the rib structure of the present invention;

[0065] Figure 4 This is a diagram of the comb-shaped variable curvature reinforcing rib structure of the present invention;

[0066] Figure 5(a) is a schematic diagram of the leading edge deformation profile;

[0067] Figure 5(b) is a schematic diagram of the leading edge deformed comb tooth structure;

[0068] Figure 6 This is a schematic diagram showing the location of the leading edge deformation zone component of the present invention;

[0069] Figure 7 This is a structural diagram of a common rib variant;

[0070] Figure 8 This is a diagram of the zero Poisson's ratio ribbed belt structure of the present invention;

[0071] Figure 9 This is a diagram of the U-shaped connector of the present invention;

[0072] Figure 10 This is a diagram showing the leading / trailing edge deflection angles of the present invention;

[0073] Figure 11 This is a schematic diagram of the spanwise elongation of the present invention;

[0074] Figure 12 This is a flowchart of the agent modeling process of the present invention.

[0075] In the diagram: 1. Drive rod; 2. Reinforcing rib; 3. Ordinary rib; 4. Telescopic rod; 5. Elastic skin; 6. U-shaped connector; 7. Elastic filler material; 8. Leading edge deformation zone; 9. Mid-section rigid support zone; 10. Trailing edge deformation zone; 11. Shape memory alloy; 12. Aluminum alloy rib; 13. Original outline; 14. Deformed outline; 15. Rib outer outline; 16. Comb-shaped structure; 17. Tooth spacing; 18. Tooth width; 19. Upper wing surface connection structure; 20. Overall shape before deformation; 21. Overall shape after deformation. Detailed Implementation

[0076] The following will refer to the appendices in the embodiments of the present invention. Figure 1(a)-12 The technical solutions in the embodiments of the present invention will be clearly and completely described.

[0077] Example

[0078] like Figure 1(a)-12 As shown, this invention discloses an adaptive bidirectional flexible deformable wing structure and its optimization method. The deformable structure is a bidirectional flexible deformable wing with variable chord curvature and spanwise elongation.

[0079] like Figure 2-4 As shown, the deformable structure includes a ribbed structure, a drive rod 1, and two telescopic rods 4; the two telescopic rods 4 are vertically fixed to both ends of the ribbed structure, and the telescopic rods 4 are sleeve structures. The ribbed structure includes multiple sets of reinforcing ribs 2 and multiple sets of ordinary ribs 3; the multiple sets of reinforcing ribs 2 are evenly and parallelly arranged, and the multiple sets of ordinary ribs 3 are evenly and parallelly arranged between adjacent sets of reinforcing ribs 2, such as... Figure 4 and Figure 7 As shown; the reinforcing rib 2 includes the outer contour 15 of the rib plate, and the front edge deformation zone 8, the middle rigid support zone 9 and the rear edge deformation zone 10 connected in sequence within the outer contour 15 of the rib plate; the middle rigid support zone 9 is fixedly sleeved on the periphery of the drive rod 1, and multiple sets of ordinary ribs 3 are slidably sleeved on the periphery of the drive rod 1.

[0080] Both the leading-edge deformation zone 8 and the trailing-edge deformation zone 10 include a comb-shaped structure 16, elastic filling material 7 between the teeth, and a shape memory alloy wire 11. The tips of the comb-shaped structure 16 are designed to be tangent to the outer contour 15 of the rib. In addition, a shape memory alloy wire 11 is provided below each elastic filling material 7, passing through one end of each comb-shaped structure near the elastic material 7, and is fixedly connected to each comb-shaped structure 16. Figure 4 As shown.

[0081] The comb-shaped structure 16 fully utilizes the characteristics of the elastic skin material, which has good tensile properties but is prone to wrinkling under pressure. This avoids wrinkling of the elastic skin material under pressure, ensuring a smooth deformed shape, as shown in Figures 5(a), 5(b), and 5(c). Figure 6 As shown; compared with the reinforced rib structure, the ordinary rib structure with reinforcing ribs has a smaller rib plate thickness, a larger tooth spacing, and a smaller tooth width, as shown. Figure 7 As shown. Ordinary ribs have low structural stiffness, can deform along with the deformation of the reinforcing ribs on both sides, and provide auxiliary support for the skin.

[0082] The deformation principle and characteristics of chordally variable curvature are specifically reflected in:

[0083] The shape memory alloy wire 11 is in a pre-compressed state in the martensitic phase. After being heated by electricity, the material transforms into the austenitic phase, undergoing elongation and recovery. The resulting restoring force drives the leading-edge deformation zone 8 and trailing-edge deformation zone 10 of the reinforcing rib to undergo deflection deformation, which helps the wing structure deform in the chord direction. The elastic skin 5 is made of 7075A rubber material. Due to the good tensile properties of elastic skin 5, it is prone to wrinkling under compression. The deformation characteristics of the wing structure are that the upper wing surface is stretched and the lower wing surface is purely bent during deformation.

[0084] The structural composition, deformation principle, and deformation characteristics of spanwise elongable structures are specifically reflected in:

[0085] The spanwise elongated structure comprises multiple sets of ribbed structures, telescopic rods, and U-shaped connectors. The deformation principle involves a hydraulic rod driving the reinforcing ribs 2, causing the driving rod and two telescopic rods to elongate in the spanwise direction, thereby elongating the wing structure in the spanwise direction. The U-shaped connectors 6 are made of nylon alloy or nylon carbon fiber material, and the outer surfaces of the multiple U-shaped connectors are covered with elastic skin, such as... Figure 8 and Figure 9 As shown, under the action of the drive rod 1, multiple sets of rib structures fixedly connected to the two telescopic rods 4 will elongate in the spanwise direction. At the same time, multiple sets of U-shaped connectors fixedly connected to the outer contour of the rib structure will also elongate in the spanwise direction. Under the action of the driving load, the U-shaped connectors have a supporting function for the skin.

[0086] Based on this structure, the present invention also proposes an optimization method for a flexible deformable wing structure. This method refers to optimizing the aerodynamic performance indicators of the aforementioned deformable wing structure under a given flight environment with incoming flow conditions. The method for determining the deformable shape is based on the objective function. Specifically, it includes the following steps:

[0087] Based on the aforementioned adaptive bidirectional flexible deformable wing structure, comparing the overall shape 20 before deformation and the overall shape 21 after deformation of the leading edge deformation region, the deflection angle generated by the leading edge deformation region 8 and the mid-section rigid support region 9 is defined as the leading edge deflection angle. Similarly, the deflection angle generated by the trailing edge deformation region 10 and the mid-section rigid support region 9 is defined as the trailing edge deflection angle. The deformable shape of the wing structure is described by three characteristic geometric parameters: the leading edge deflection angle, the trailing edge deflection angle, and the spanwise scaling factor, as shown in Figures 5(a), 5(b), and 5(c). Figure 10 As shown, the definition of spanwise scaling factor is:

[0088] (1)

[0089] in, For the original wing span, Elongation, such as Figure 11 As shown;

[0090] S2: The structural finite element method is used to calculate and analyze the aforementioned wing variant structure to obtain the deformation characteristic geometric parameters. , , The corresponding wing deformation shape is determined; based on this, computational fluid dynamics methods are used to obtain the wing surface pressure distribution in the airflow field, thereby obtaining the aerodynamic performance index lift-to-drag ratio. Boost-to-drag ratio and characteristic geometric parameters , , The following functional relationship exists between them:

[0091] (2)

[0092] The structural deformation strategy optimization problem is transformed into the following parameter optimization problem:

[0093] seek , so that:

[0094] (3)

[0095] In the formula, the function This is called the cost function, or performance index. The classic gradient optimization method, steepest descent, is used to solve this parameter optimization problem, and the optimal solution is obtained using the steepest descent method. Gradient of the cost function f The aerodynamic performance indicators can be obtained using a finite difference scheme. However, if high-precision numerical simulation methods are directly used to obtain the aerodynamic performance indicators during the optimization process... f The computational workload would be enormous, even unacceptable.

[0096] This invention uses a surrogate model method to obtain the performance indicators of the target shape. This can greatly improve calculation speed. For example Figure 12 As shown, firstly, the orthogonal design method is used to sample in the design space to obtain the sample space; then, structural and aerodynamic numerical simulation methods are used to obtain the coordinate matrix of the deformed shape of each sample. and the flow field pressure distribution matrix in the shape ;Will and Combining the results, we obtain the augmented snapshot matrix. :

[0097] (4)

[0098] The aerodynamic model is obtained by using the orthogonal decomposition method with missing features. Then, the performance indicators of the target shape are obtained through the aerodynamic model using the surrogate model method. ;

[0099] According to performance indicators Determine the deformable shape of the wing structure.

[0100] The aerodynamic model is obtained using the missing feature orthogonal decomposition method. The specific iterative steps of this algorithm are as follows:

[0101] S1: Pressure distribution on the target shape Initialize :

[0102] (5)

[0103] for Average flow field pressure distribution on the shape of each sample:

[0104] S2: For augmented snapshot matrix Perform orthogonal decomposition of features and obtain the frontier features. Orthogonal decomposition method for missing features:

[0105] (6)

[0106] but The singular value decomposition is ;

[0107] in, And there is:

[0108] (7)

[0109] in .also The singular value decomposition satisfies:

[0110] (8)

[0111] orthogonal decomposition method for missing features The following maximum value problem is solved:

[0112] (9)

[0113] express Inner product operation of space, y j Indicates the first j An augmented snapshot vector of a deformed shape. u i , u j Indicates the first i , j The modal vector of order.

[0114] orthogonal decomposition method for missing features The solution can be obtained by constructing a matrix. And solve the following eigenvalue problem:

[0115] (10)

[0116] Then we have:

[0117] (11)

[0118] Eigenvalues Characterizing the modes of the orthogonal decomposition method with missing features Contribution to the total energy of the flow field. (Previous) The proportion of the missing characteristic orthogonal decomposition mode in the total energy of the flow field can be determined by the following formula:

[0119] (12)

[0120] In the analysis of the missing feature orthogonal decomposition method, the mean flow field is usually subtracted from the snapshot flow field first. Therefore, the modes of the missing feature orthogonal decomposition method characterize the flow field disturbance.

[0121] S3: Before using Pressure distribution of target shape in modal update using orthogonal decomposition method for missing features :

[0122] (13)

[0123] in, a i These are unsteady modal coefficients, which can be obtained by least squares estimation. k Let p be the number of iterations. At this point, if the error p meets the accuracy requirement EPS:

[0124] (14)

[0125] The algorithm then stops. If the target shape pressure distribution is not specified, then return the augmented snapshot matrix. Perform orthogonal decomposition of features to proceed to the next iteration until equation (14) is satisfied.

[0126] Specific data calculations show that the bidirectional flexible deformable wing structure with chordal variable camber and spanwise elongation designed in this invention achieves significant leading and trailing edge deflection in the chord direction (deflection angle >= 10°) and spanwise elongation of up to 20% of the original length. Based on this structure, a wing deformation parameter optimization method is proposed. This method can adaptively optimize the leading and trailing edge deflection angles according to flight speed, improving the lift-to-drag ratio by >50% under typical operating conditions. Therefore, this optimization method has high efficiency and reliable accuracy. Under driving action, this deformable wing achieves flexible deformation of the entire structure, with a continuous, smooth, and seamless deformed shape, eliminating aerodynamic noise generated by gap flow and reducing aerodynamic drag. It requires no mechanical deflection structure, has low added weight, a simple structure, and is easy to manufacture.

[0127] The above description is only a preferred embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any equivalent substitutions or modifications made by those skilled in the art within the scope of the technology disclosed in the present invention, based on the technical solution and inventive concept of the present invention, should be covered within the scope of protection of the present invention.

Claims

1. An adaptive bidirectional flexible deformable wing structure, characterized in that, It includes a ribbed structure, a drive rod (1), and two telescopic rods (4); The two telescopic rods (4) are vertically fixedly connected to both ends of the rib structure; The rib structure includes multiple sets of reinforcing ribs (2) and multiple sets of ordinary ribs (3); the multiple sets of reinforcing ribs (2) are evenly and parallelly arranged, and the multiple sets of ordinary ribs (3) are evenly and parallelly arranged between two adjacent sets of reinforcing ribs (2); The reinforcing rib (2) includes a rib plate outer contour (15), and a leading edge deformation zone (8), a middle rigid support zone (9), and a trailing edge deformation zone (10) connected sequentially within the rib plate outer contour (15). The ends of the multiple leading edge deformation zones (8) and the multiple trailing edge deformation zones (10) away from the middle rigid support zone (9) are uniformly fixedly connected to the two telescopic rods (4). Multiple sets of U-shaped connectors (6) are fixedly connected to the rib plate outer contours (15) of multiple sets of ordinary ribs (3) and multiple sets of reinforcing ribs (2). The outer surface of the U-shaped connector (6) is provided with an elastic skin (5); the leading edge deformation area (8) and the trailing edge deformation area (10) both include a comb-shaped structure (16), an elastic filling material (7) between the teeth and a shape memory alloy wire (11). A shape memory alloy wire (11) is provided below each elastic filling material (7) and passes through one end of each comb-shaped structure near the elastic filling material (7) and is fixedly connected to each comb-shaped structure (16). The tooth tip of the comb-shaped structure (16) is tangent to the outer contour (15) of the rib plate. The elastic skin (5) covers the entire outer surface of the wing and is fixedly connected to the outer contour of the mid-section rigid support area (9), and is slidably connected to the outer contour of the leading edge deformation area (8) and the trailing edge deformation area (10). The middle rigid support area (9) is fixedly sleeved around the drive rod (1); multiple sets of ordinary ribs (3) are slidably sleeved around the drive rod (1).

2. The adaptive bidirectional flexible deformable wing structure according to claim 1, characterized in that, The telescopic rod (4) is a sleeve structure.

3. The adaptive bidirectional flexible deformable wing structure according to claim 1, characterized in that, The elastic skin (5) is made of 7075A rubber.

4. The adaptive bidirectional flexible deformable wing structure according to claim 1, characterized in that, The U-shaped connector (6) is made of nylon alloy or nylon carbon fiber material.

5. An optimization method for an adaptive bidirectional flexible deformable wing structure according to any one of claims 1 to 4, characterized in that, Includes the following steps: The deflection angle generated by the leading edge deformation zone (8) and the middle rigid support zone (9) is defined as the leading edge deflection angle. Similarly, the deflection angle generated by the trailing edge deformation zone (10) and the middle rigid support zone (9) is defined as the trailing edge deflection angle. The deformable shape of the wing structure is described by the leading edge deflection angle. Trailing edge deflection angle and spanwise elongation The three characteristic geometric parameters describe the process, wherein the spanwise scaling factor is defined as follows: (1) in, For the original wing span, Elongation; The finite element method is used to perform calculations and analyses to obtain the geometric parameters of deformation characteristics. , , The corresponding deformed shape; Computational fluid dynamics methods are used to obtain the airfoil surface pressure distribution in the airflow field, thereby obtaining the aerodynamic performance index lift-to-drag ratio. Boost-to-drag ratio and characteristic geometric parameters , , The following functional relationship exists between them: (2) Transform the structural deformation strategy optimization problem into a parameter optimization problem: seek , so that: (3) In the formula, the function This is the cost function, i.e., the performance metric; The optimal solution is obtained using the steepest descent method. The aerodynamic model is obtained by using the feature-complete orthogonal decomposition method. Then, the performance indicators of the target shape are obtained by solving the aerodynamic model using the surrogate model method. ; According to performance indicators To determine the deformable shape of the wing structure.

6. The optimization method for an adaptive bidirectional flexible deformable wing structure according to claim 5, characterized in that, The method employs a surrogate model to obtain the performance indicators of the target shape through aerodynamic model solving. This includes the following steps: The sample space is obtained by sampling in the design space using orthogonal design methods; The deformable shape coordinate matrix of each sample was obtained using structural and aerodynamic numerical simulation methods. and the flow field pressure distribution matrix in the shape ;Will and Combining the results, we obtain the augmented snapshot matrix. : (4) S1: Pressure distribution on the target shape Initialize : (5) In the formula, for Average flow field pressure distribution on the shape of each sample: ; S2: For augmented snapshot matrix Perform orthogonal decomposition of features and obtain the frontier features. Orthogonal decomposition method for missing features: (6) but The singular value decomposition is ; in, And there is: (7) in, ,also The singular value decomposition satisfies: (8) orthogonal decomposition method for missing features To satisfy the maximum value problem: (9) in, express Inner product operation of space, y j Let u represent the augmented snapshot vector of the j-th deformed shape. i u j Let represent the mode vectors of order i and j; By constructing a matrix Perform missing feature orthogonal decomposition mode Solve the following eigenvalue problem: (10) Then we have: (11) In the formula, eigenvalues Characterizing the modes of the orthogonal decomposition method with missing features Contribution to the total energy of the flow field, before The proportion of the missing characteristic orthogonal decomposition mode in the total energy of the flow field is determined by the following formula: (12) S3: Before using Pressure distribution of target shape in modal update using orthogonal decomposition method for missing features : (13) Among them, a i These are the unsteady modal coefficients, obtained by least squares estimation, where k is the number of iterations. At this point, if the error Meets EPS accuracy requirements: (14) The algorithm then stops. For the target shape pressure distribution, otherwise return the augmented snapshot matrix. Perform orthogonal decomposition of features to proceed to the next iteration until formula (14) is satisfied.

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