Variable-sweep wing based on flexible corrugated skin and its design method

Abstract

The present invention discloses a variable-sweep wing based on a flexible corrugated skin and a design method, which relates to the field of aircraft structural design, including a wing mounting seat matched with a fuselage, and also including: a rigid edge strip adapted to the outer edge of the variable-sweep wing; a vertical layout in space, and the wing mounting seat and the rigid edge strip are connected as an integrated structure to construct a flexible corrugated skin I and a flexible corrugated skin II of the swept wing; multiple groups of support components arranged between the flexible corrugated skin I and the flexible corrugated skin II; a driving mechanism arranged on the wing mounting seat to tow the deformation of the flexible corrugated skin; and a linear displacement sensor for measuring the change in the wing sweep angle. The present invention provides a variable-sweep wing based on a flexible corrugated skin and a design method, which can help an aircraft realize the adjustment of aerodynamic shape with the flight trajectory, effectively solve the contradiction of aerodynamic shape across the speed domain, provide an aircraft with a higher available lift-to-drag ratio, and further improve the comprehensive aerodynamic performance of the aircraft.

Description

Technical Field

[0001] The present invention relates to the field of aircraft structure design, and more specifically, to a variable-sweep wing based on a flexible corrugated skin and a design method thereof. Background Art

[0002] During the flight of a cross-speed aircraft from high speed to low speed, the lift coefficient and flight pressure of the aircraft vary greatly; at the same time, with the consumption of fuel, the weight of the aircraft changes significantly, and the flight angle of attack after meeting the lift-to-weight balance deviates significantly from the designed maximum lift-to-drag ratio angle of attack, and the lift-to-drag ratio is seriously lost under the actual flight angle of attack; therefore, it is difficult to obtain the optimal lift-to-drag ratio in the entire flight profile by relying solely on single-point aerodynamic layout optimization, and the variant wing technology can realize the continuous adjustment of the aerodynamic shape with the flight trajectory, effectively solving the contradiction of the aerodynamic shape across the speed domain, thereby obtaining a higher available lift-to-drag ratio and improving the comprehensive aerodynamic performance of the aircraft.

[0003] Traditional aviation variant structures such as leading edge slats and trailing edge flaps are widely used in civil aircraft. This type of lift-enhancing device increases the lift of the wing by increasing the curvature of the wing airfoil and the area of ​​the entire wing. Although it can achieve the purpose of lift enhancement in the low-speed range, its large number of connection gaps, complex actuation mechanisms and small deformation are not suitable for low, supersonic and supersonic cross-speed flight. For variant wings in high-speed environments, current research is mainly focused on aerodynamic layout design and scheme exploration, and engineering applications are still rare. Variable-sweep wings can simultaneously change the wing area, sweep angle and wing span, and have good lift-to-drag ratio control capabilities. It is a very promising deformation method. However, in order to meet the requirements of high-speed cruising, high-performance metals or composite materials are usually used on the wing surface. Such skin materials are all rigid or inelastic materials. Therefore, most variable-sweep wings are currently rigid rotation deformations, with complex retraction and extension mechanisms, and occupy a large amount of fuselage space after retraction, which greatly reduces engineering practicality. That is, traditional variable geometry aircraft have problems such as complex structure / mechanism, heavy system weight, and large fuselage space occupation. Summary of the invention

[0004] An object of the present invention is to solve at least the above problems and / or disadvantages and to provide at least the advantages which will be described hereinafter.

[0005] In order to achieve these objects and other advantages of the present invention, there is provided a variable-sweep wing based on a flexible corrugated skin, comprising a wing mounting seat matched with a fuselage, and further comprising:

[0006] Rigid strakes that match the leading edge of the variable-sweep wing;

[0007] The structure is arranged up and down in space, and the wing mounting seat and the rigid side strip are connected into an integrated structure to construct the flexible corrugated skin I and the flexible corrugated skin II of the variable sweep wing;

[0008] A plurality of support components arranged between the flexible corrugated skin I and the flexible corrugated skin II;

[0009] A driving mechanism arranged on the wing mounting seat to pull the flexible corrugated skin to deform;

[0010] A sealing mechanism I is provided at the smaller end of the flexible corrugated skin I and the flexible corrugated skin II to seal and rectify the front end of the wing;

[0011] A sealing mechanism II is provided at the larger end of the flexible corrugated skin I and the flexible corrugated skin II to seal the rear end of the wing;

[0012] Wherein, the smaller end of the rigid edge strip is hinged to the wing mounting seat via a rotating shaft, and the power output end of the driving mechanism is hinged to the rigid edge strip via a fisheye joint ball;

[0013] The sealing mechanism I and the sealing mechanism II are both sliding structures.

[0014] Preferably, the support assembly is configured to include:

[0015] Two metal mounting strips respectively matched with the flexible corrugated skin I and the flexible corrugated skin II;

[0016] A fixed shaft disposed on a corresponding metal mounting strip;

[0017] A plurality of connecting rods are arranged at predetermined intervals to connect the fixed shaft into an integral structure.

[0018] Preferably, a telescopic main rail and a secondary rail are provided between the rigid edge strip and the wing mounting seat, and sliding grooves matching in space are provided on opposite side surfaces of the main rail and the secondary rail respectively;

[0019] Wherein, a central rod is arranged on the connecting rod, and pulleys or sliders which can be embedded and slid in the sliding grooves of the telescopic main guide rail and the telescopic auxiliary guide rail are arranged at both ends of the central rod;

[0020] The main guide rail and the auxiliary guide rail are both inner and outer nested sliding structures.

[0021] Preferably, the invention further comprises a linear displacement sensor arranged between the wing mounting seat and the rigid edge strip.

[0022] A flexible corrugated skin design method, which is applied to a variable-sweep wing based on the flexible corrugated skin, comprises:

[0023] S1. Determine the layout area of ​​the flexible corrugated skin in the variable sweep wing;

[0024] S2, based on the layout area in S1, select the location of the corrugated design section, located at the arc radius R 2 The length of the corrugation curve on the design section is obtained by the following formula L bw :

[0025]

[0026] In the above formula, It represents the arc length of the design section of the wing when it is fully extended. k represents the flattening coefficient of the flexible corrugated material, Φ 1 Indicates the angle occupied by the corrugated skin in the fully expanded state, β is the angle between the upper and lower surfaces of the wing on the design section;

[0027] S3, the length of the ripple curve obtained based on S2 L bw , the length of the combined gradual corrugation of straight line segment + arc segment is obtained by the following design;

[0028]

[0029] The combined gradual corrugation is obtained by adjusting the tolerance to j of n Arc radius r i Connected by straight line segments, i The values ​​are 1, 2, 3... n , is the total arc length in the ripple curve, L xd is the total straight line length in the corrugated curve;

[0030] S4, judging whether the combined gradual ripple obtained in S3 is in the layout area in S1, if so, outputting the ripple design result; otherwise, returning to S3.

[0031] Preferably, in S3, the It is characterized by the following formula:

[0032]

[0033] In the above formula, θ is the inclination of the straight line segment;

[0034] Said L xd It is characterized by the following formula:

[0035]

[0036] In the above formula, L xdty is the projection length of the total straight line segment, is the arc length of the wing in the fully retracted state, L yhxc Total arc chord length.

[0037] Preferably, in S3, in the design process of the combined gradual corrugation, for a given arc radius r 1 ,tolerance j , Number of arcs n After the initial design parameters are obtained, the inclination angle of the straight line segment is calculated. θ To determine the size of the corrugation, and then use the tangency constraint to determine whether the corrugation is within the upper and lower boundaries of the layout area. If so, output the corrugation design result; otherwise, adjust the initial value and recalculate θ .

[0038] Preferably, in S1, when determining the flexible corrugated skin arrangement area, the thickness of the corrugated skin design area should be less than 1 / 3 of the wing thickness;

[0039] For a given wing sweep angle, the required change Δ Φ The angle occupied by the corrugated skin in the fully retracted state of the wing is determined by the following formula: Φ 0 ,and Φ 0 ≥2×Δ Φ :

[0040] Φ 1 -Δ Φ = Φ 0

[0041] In the above formula, Φ 1 is the occupancy angle of the flexible corrugated skin when it is fully expanded.

[0042] The present invention includes at least the following beneficial effects: The present invention proposes a flexible corrugated skin variable-sweep wing structure and a design method thereof, which can help an aircraft to adjust its aerodynamic shape along with its flight trajectory, effectively resolve the contradiction of aerodynamic shape across speed ranges, provide the aircraft with a higher available lift-to-drag ratio, and further improve the aircraft's comprehensive aerodynamic performance.

[0043] Other advantages, objectives and features of the present invention will be embodied in part through the following description, and in part will be understood by those skilled in the art through study and practice of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0044] Figure 1It is a schematic diagram of the variable-sweep wing of the present invention in a large sweep angle state when in use;

[0045] Figure 2 It is a schematic diagram of the variable-sweep wing of the present invention in a small sweep angle state when in use;

[0046] Figure 3 This is a schematic diagram of the internal structure of the variable-sweep wing of the present invention after the flexible corrugated skin is removed;

[0047] Figure 4 It is a schematic diagram of the structure of the support assembly in the variable-sweep wing of the present invention;

[0048] Figure 5 It is a schematic diagram of the structure of the support assembly and the flexible corrugated skin in the variable-sweep wing of the present invention;

[0049] Figure 6 It is a schematic diagram of the structure of the support assembly of the variable-sweep wing of the present invention cooperating with the main guide rail slide groove and the auxiliary guide rail slide groove;

[0050] Figure 7 It is a schematic diagram of the arrangement area of ​​the flexible corrugated skin in the variable-sweep wing of the present invention;

[0051] Figure 8 A schematic diagram of determining the wing rotation axis in the variable-sweep wing of the present invention;

[0052] Fig. 9 A schematic diagram of the thickness of the corrugated skin design area in the variable-sweep wing design of the present invention;

[0053] Fig.10 A schematic diagram of the corrugation length on the designed cross section of the variable-sweep wing corrugated material of the present invention;

[0054] Fig.11 It is a schematic diagram of the variable-sweep wing of the present invention when the wing is fully extended;

[0055] Fig.12 It is a schematic diagram of the variable-sweep wing of the present invention when the wing is fully retracted;

[0056] Fig.13 This is a schematic diagram of the standard corrugated shape structure of the variable-sweep wing of the present invention;

[0057] Among them, rigid edge strip-1, flexible corrugated skin-2, supporting assembly-3, sealing mechanism I-4, wing mounting seat-5, sealing mechanism II-6, main rail-7, auxiliary rail-8, main rail slide groove-9, auxiliary guide rail slide groove-10, rotating shaft-11, servo electric cylinder-12, linear displacement sensor-13, metal mounting strip-14, fixed shaft-15, connecting rod-16, center rod-17, pulley-18, cover plate-19, sealing plate-20, slide plate-21, slide groove-22, arc segment-23, straight line segment-24, fixing part-25, flexible corrugated skin layout area-26, corrugated design section-27, initial configuration of corrugated material-28, maximum unfolding state of corrugated material with partial flattening ability-29, maximum unfolding state of corrugated material with full flattening ability-30, unfolding plane-31, center line-32. DETAILED DESCRIPTION

[0058] The present invention is further described in detail below in conjunction with the accompanying drawings so that those skilled in the art can implement the invention with reference to the description.

[0059] The flexible corrugated skin variable sweep wing proposed in the present invention mainly realizes the function that the wing sweep angle can be actively adjusted according to the flight state, which can meet the requirements of high-speed cruising of aircraft with large sweep angle ( Figure 1 ), low speed and horizontal recovery use small sweep angle ( Figure 2 ) needs, and has the characteristics of simple structure, light weight, and small fuselage space, and can provide technical support for the engineering application of cross-speed range aircraft.

[0060] Specifically, a flexible corrugated skin variable sweep wing mainly includes: a rigid edge strip 1, a flexible corrugated skin 2, a support assembly 3 of the flexible corrugated skin, a sealing mechanism I 4, a wing mounting seat 5 matched with the fuselage, a sealing mechanism II 6, a main rail 7, a secondary guide rail 8, a main rail slide groove 9, a secondary guide rail slide groove 10, etc.

[0061] 1. If Figure 3 , Figure 6 The rigid edge strip 1 shown can rotate around the rotating shaft 11 and transfer the load from the driving mechanism to the flexible corrugated skin 2, pulling the flexible corrugated skin 2 to deform. In actual applications, the flexible corrugated skin is arranged symmetrically in the upper and lower parts, and each flexible corrugated skin 2 includes a plurality of circular arc segments 23 and a plurality of straight line segments 24 connecting adjacent circular arc segments, and each flexible corrugated skin has a fixing portion 25 on both sides that cooperates with the wing mounting seat 5 and the rigid edge strip 1.

[0062] 2. If Figure 4-Figure 6As shown, the support assembly 3 of the flexible corrugated skin is used to connect the flexible corrugated skin with the main rail 7 and the auxiliary rail 8. It can be set as one or more groups as needed to maintain the shape of the flexible corrugated skin and transfer the aerodynamic load on the skin to the main rail 7 and the auxiliary rail 8. The flexible corrugated skin support assembly connects the upper and lower skins through the upper and lower metal mounting strips 14, and transfers the load from the skin to the center rod 17 through the fixed shaft 15 and the connecting rod 16. The pulleys 18 are designed at both ends of the center rod, which can be nested in the main rail slide groove 9 and the auxiliary rail slide groove 10 of the main rail 9 and the auxiliary rail 10 to slide. The number and placement of the flexible corrugated skin support assembly can be selected based on the size of the aerodynamic load and the wing area. The specific number of support assemblies required is based on the specific usage scenario and is determined after analysis by engineering means. For example, the finite element analysis results may be at least 3 groups or at least 5 groups.

[0063] 3. If Figure 3 As shown, the sealing mechanism I (also called rigid fairing skin) 4 has the function of fairing and drag reduction, one side of which is fixed on the rigid side strip and can rotate with the rigid side strip, and the other side is covered inside the structure and can slide (that is, a cover plate 19 is provided on the wing mounting seat 5, and the sealing mechanism I 4 is slidably provided on the inner side of the cover plate 19 to ensure the effectiveness of sealing and telescopicity).

[0064] 4. If Figure 3 As shown, the sealing mechanism II (also called sealing plate) 6 is a two-section nested sliding structure, and its specific structure includes two sealing plates 20, which are respectively arranged on the wing mounting seat 5 and the rigid side strip 1, and the two sealing plates 20 are overlapped in space, one of which has a smaller slide plate 21, and the other has a slide groove 22 matched with the slide plate, which can provide sealing operation for the rear end of the wing.

[0065] 5. If Figure 3 As shown, the drive mechanism and measuring mechanism of the variable sweep are: the drive mechanism adopts a servo electric cylinder 12, and the measuring mechanism adopts a linear displacement sensor 13. The servo electric cylinder 12 is installed at a position far away from the rotating shaft 11, has a large driving torque, and has a self-locking function, which can realize the continuous change of the sweep angle within the adjustable range and lock it at any position, and can ensure the adjustment accuracy of the sweep angle. The linear displacement sensor 13 can transmit the monitored displacement change to the control system, thereby converting it into the change of the wing sweep angle to realize the control closed loop.

[0066] 6. If Figure 6 As shown, the main guide rail 7 and the auxiliary guide rail 8 are both internally and externally nested sliding structures, and are the main load-bearing components. They have the advantages of simple structure and light weight, and can both ensure the rigidity of the wing and constrain the rotational deformation direction of the wing. Example

[0067] In the design of the flexible corrugated skin, it is necessary to ensure that the deformation of the flexible corrugated skin and the wing frame is coordinated. When the wing is fully unfolded, all parts of the skin reach the maximum unfolded position at the same time. Therefore, the specific design method of the flexible corrugated skin is as follows:

[0068] 1. Determine the flexible corrugated skin layout area 26

[0069] ① Such as Figure 8 As shown, the position of the wing rotation axis 11 is determined.

[0070] ②According to the configuration output by the aerodynamic design, extract the required change in the wing sweep angle Δ Φ , and determine the angle occupied by the corrugated skin when the wing is fully retracted Φ 0 And the angle occupied by the corrugated skin in the fully expanded state Φ 1 , must meet Φ 1 - Φ 0 =Δ Φ At the same time, considering the limited flattening ability of the corrugated skin material, Φ 0 ≥2×Δ Φ Considering that the front end of the corrugated skin needs to be arranged with a rectifier skin, the radius of the arc at the front end of the corrugated skin is selected. R 1 , R 1 Take it as 25%-30% of the wing root chord length, that is R 1 The rear edge of the rigid fairing skin.

[0071] ③ Such as Fig. 9 As shown in Figure 1, considering the aerodynamic shape, load-bearing structure size and internal space requirements, the thickness of the corrugated skin design area should be less than 1 / 3 of the wing thickness, that is, t 1 ≤ T 1 / 3, t 2 ≤ T 2 / 3, t 1 and t 2 are the heights of the large and small ends of the corrugation arrangement area on the design section, T 1 and T 2 It is the thickness of the wing at the large and small ends of the corrugation arrangement area on the design section.

[0072] 2. If Figure 7As shown, the corrugated design section 27 is selected. Any arc surface with the rotation axis as the center can be selected as the corrugated design section. The design section is located at the arc radius R 2 Place.

[0073] 3. Determine the corrugation length on the design section

[0074] ①First proposed the flattening coefficient of corrugated material k This parameter describes the flattening ability of the corrugated material. The flattening ability is determined by the material's stiffness and strength. The flattening coefficient is defined as the ratio of the unfolded width to the curve length. Fig.10 As shown in (Fig. l 1 is the width of the corrugated material corresponding to the initial state, l 2 The width of the corrugated material with partial flattening capability at its maximum expansion state. l 3 28 is the initial configuration of the corrugated material, 29 is the maximum expansion state of the corrugated material with partial flattening ability, and 30 is the maximum expansion state of the corrugated material with full flattening ability. The lengths of the three curves are equal, that is, L 28 = L 29 = L 30 = L ( L 28 is the length of the curve corresponding to the initial configuration of the corrugated material, L 29 The length of the curve corresponding to the maximum unfolded state of the corrugated material with partial flattening ability, L 30 The length of the curve corresponding to the maximum unfolded state of the corrugated material with full flattening ability, L is the length of the corrugated curve), the unfolded width is l , flattening coefficient k = l / L . Corrugated material with full flattening capability k = l 3 / L =1, corrugated material with partial flattening capability k = l 2 / L <1. Flattening coefficient k It can be obtained by flattening a specific corrugated material through experiments or numerical simulations.

[0075] ② If Fig.11As shown, when the wing is fully extended, the arc length on the design section ( , the subscript "zkhc" means "expanded arc length") is the expanded width of the corrugated skin. Considering that the corrugated skin material has only partial flattening ability, the cross-sectional corrugation curve length (L bw , the subscript "bw" means "corrugation") satisfies the arc length of the design section. Then the length of the corrugation curve on the design section is:

[0076] (1)

[0077] Among them, β is the angle between the upper and lower surfaces of the wing on the design section. It should be noted that the angles in this article are all in radians.

[0078] 4. Extract corrugation design parameters

[0079] ① Such as Fig.12 As shown, the corrugation shape design is carried out when the wing is fully folded, the corrugation design section 27 is an arc surface, and a standard corrugation is designed on its unfolding plane 31.

[0080] ② A gradient ripple in the form of a “straight line segment-circular arc” combination is proposed. Fig.13 The standard corrugation shape is determined by the arc radius r , straight line segment inclination θ , Ripple peak / valley number n To ensure that the corrugated skin does not rub against the wing structure (wing mounting seat 5, rigid edge strip 1) after installation, the first and last wave crests of the corrugation should face the air side. n Take an odd number.

[0081] ③ To achieve the ripple gradient effect, the ripple arc radius ( r 1 , r 2 , r 3 ,……, r n ) is designed as an arithmetic progression with a tolerance of j .

[0082] ④The length of the standard corrugation can be expressed as the total arc length ( , the subscript "yh" means "arc") and the total straight line segment length ( L xd , subscript "xd" means "line segment"):

[0083] (2)

[0084] Among them, the total length of the arc can be calculated by the following arithmetic progression summation formula:

[0085] (3)

[0086] The total length of the straight line segment can be inversely calculated from the projection relationship of the corrugation on the center line 32. The projection length of the corrugation on the center line ( L bwty , the subscript "bwty" means "ripple projection") is equal to the total arc chord length ( L yhxc , the subscript "yhxc" means "arc chord length") and the total straight line segment projection length ( L xdty , the subscript "xdty" means "line segment projection"), and when the wing is fully retracted, the projection length of the corrugation on the centerline is equal to the arc length on the design section ( , the subscript "sqhc" means "closed arc length"), which satisfies the following relationship:

[0087] (4)

[0088] (5)

[0089] (6)

[0090] The total straight line segment projection length and the total straight line segment length satisfy the cosine theorem, then:

[0091] (7)

[0092] but:

[0093] (8)

[0094] 5. Solution

[0095] ① Before solving, first give the arc radius r 1 ,tolerance j , Number of arcs n Initial values ​​of design parameters such as the inclination angle of the straight line segment θ as the variable to be sought.

[0096] ② Combine equations (1) and (2) to solve the inclination of the straight line segment θ .

[0097] ③ Determine whether the ripple is within the upper and lower boundaries of the layout area (this can be done by comparing the ripple arc with the Fig. 9 Tangent constraints are imposed on the upper and lower boundaries of the corrugation layout area for inspection). If so, the corrugation design result is output; otherwise, the initial value is adjusted and recalculated. θ .

[0098] 6. Generate corrugated skin

[0099] After the corrugations on the design section are completely determined, the corrugations determined on the design section are translated and scaled to obtain the front end of the skin R 1 The ripples of the position section are scaled by R 1 / R 2 Finally, the corrugated skin with thickness is obtained by sweeping the corrugations on the two sections and performing operations such as extension, boundary trimming, and thickening.

[0100] The above solution is only an illustration of a preferred embodiment, but is not limited thereto. When implementing the present invention, appropriate replacement and / or modification can be performed according to user needs.

[0101] Although the embodiments of the present invention have been disclosed above, they are not limited to the applications listed in the specification and the embodiments. It can be fully applied to various fields suitable for the present invention. For those familiar with the art, additional modifications can be easily realized. Therefore, without departing from the general concept defined by the claims and equivalent scope, the present invention is not limited to the specific details and the illustrations shown and described here.

Claims

1. A method for designing a flexible corrugated skin, characterized in that: include: S1. Determine the layout area of ​​the flexible corrugated skin in the variable sweep wing; S2, based on the layout area in S1, select the location of the corrugated design section, located at the arc radius R 2, and the corrugation curve length on the design section is obtained by the following formula L bw : In the above formula, represents the arc length on the design section of the wing in the fully expanded state, k represents the flattening coefficient of the flexible corrugated material, Φ1 represents the angle occupied by the corrugated skin in the fully expanded state, β is the angle between the upper and lower surfaces of the wing on the design section, and the arc radius R 2 The center of the arc corresponding to the rotation axis (11); S3, based on the corrugation curve length Lbw obtained in S2, the combined gradient corrugation length of straight line segment + arc segment is obtained by the following design; The combined gradual corrugation is obtained by adjusting the tolerance to j of n The radius of the corrugation arc r i Connected by straight line segments, i The values ​​are 1, 2, 3... n , is the total arc length in the ripple curve, L xd is the total straight line length in the corrugated curve; S4, judging whether the combined gradual ripple obtained in S3 is in the layout area in S1, if so, outputting the ripple design result; otherwise, returning to S3.

2. The method for designing a flexible corrugated skin according to claim 1, characterized in that: In S3, the It is characterized by the following formula: In the above formula, θ is the inclination of the straight line segment; Said L xd It is characterized by the following formula: In the above formula, L xdty is the projection length of the total straight line segment, is the arc length of the wing in the fully retracted state, L yhxc Total arc chord length.

3. The method for designing a flexible corrugated skin according to claim 2, characterized in that: In S3, in the design process of combined gradient corrugation, for a given corrugation arc radius r 1. Tolerance j , Number of arcs n After the initial design parameters are obtained, the inclination angle of the straight line segment is calculated. θ To determine the size of the corrugation, and then use the tangency constraint to determine whether the corrugation is within the upper and lower boundaries of the layout area. If so, output the corrugation design result; otherwise, adjust the initial value and recalculate θ .

4. The method for designing a flexible corrugated skin according to claim 2, characterized in that: In S1, when determining the flexible corrugated skin layout area, the thickness of the corrugated skin design area should be less than 1 / 3 of the wing thickness; For a given wing sweep angle, the required change Δ Φ The angle occupied by the corrugated skin in the fully retracted state of the wing is determined by the following formula: Φ 0, and Φ 0≥2×Δ Φ : Φ 1-D Φ = Φ 0 In the above formula, Φ 1 is the occupancy angle when the flexible corrugated skin is fully expanded.

5. A variable-sweep wing based on a flexible corrugated skin, which is applied to the flexible corrugated skin design method as claimed in any one of claims 1 to 4, comprising a wing mounting seat matched with a fuselage, characterized in that: Also includes: Rigid strakes that match the leading edge of the variable-sweep wing; The structure is arranged up and down in space, and the wing mounting seat and the rigid side strip are connected into an integrated structure to construct the flexible corrugated skin I and the flexible corrugated skin II of the swept wing; A plurality of support components arranged between the flexible corrugated skin I and the flexible corrugated skin II; A driving mechanism arranged on the wing mounting seat to pull the flexible corrugated skin to deform; A sealing mechanism I is provided at the smaller end of the flexible corrugated skin I and the flexible corrugated skin II to seal and rectify the front end of the wing; A sealing mechanism II is provided at the larger end of the flexible corrugated skin I and the flexible corrugated skin II to seal the rear end of the wing; Wherein, the smaller end of the rigid edge strip is hinged to the wing mounting seat via a rotating shaft, and the power output end of the driving mechanism is hinged to the rigid edge strip via a fisheye joint ball; The sealing mechanism I and the sealing mechanism II are both sliding structures.

6. The variable-sweep wing based on flexible corrugated skin according to claim 5, characterized in that: The support assembly is configured to include: Two metal mounting strips respectively matched with the flexible corrugated skin I and the flexible corrugated skin II; A fixed shaft disposed on a corresponding metal mounting strip; A plurality of connecting rods are arranged at predetermined intervals to connect the fixed shaft into an integral structure.

7. The variable-sweep wing based on flexible corrugated skin according to claim 6, characterized in that: A telescopic main rail and auxiliary rail are arranged between the rigid edge strip and the wing mounting seat, and sliding grooves that match in space are respectively arranged on the opposite side surfaces of the main rail and the auxiliary rail; Wherein, a central rod is arranged on the connecting rod, and pulleys or sliders which can be embedded and slid in the sliding grooves of the telescopic main guide rail and the telescopic auxiliary guide rail are arranged at both ends of the central rod; The main guide rail and the auxiliary guide rail are both inner and outer nested sliding structures.

8. The variable-sweep wing based on flexible corrugated skin according to claim 5, characterized in that: Also included is a linear displacement sensor disposed between the wing mounting seat and the rigid edge strip.

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