Morphing wing integrating telescopic variable-elongation and rotary variable-sweepback functions and morphing method

Abstract

The invention provides a morphing wing integrating telescopic variable-elongation and rotary variable-sweepback functions and a morphing method. The morphing wing comprises an inner wing section, an outer wing section and an elastic skin, the inner wing section and the outer wing section are positioned in the same spanwise plane; the inner wing section stretches and retracts in the spanwise plane along the spanwise direction of the wing, so that the span length of the inner wing section is adjusted; the outer wing sections rotate in the chordwise direction relative to the inner wing sections in the spanwise plane, and then the sweepback angles of the outer wing sections are adjusted. By adjusting the extension length and the sweepback angle of the wings, the lift force of the aircraft during low-speed flight is improved, and the resistance of the aircraft during high-speed flight is reduced. Specifically, the extension length of the wings is increased during low-speed flight to improve lift force, and the extension length is reduced and the sweepback angle is increased during high-speed flight to reduce resistance. The optimal aerodynamic performance can be achieved no matter in a low-speed flight state or a high-speed flight state, and the adaptability and the flight performance of the aircraft are remarkably improved.

Description

Technical Field

[0001] The invention belongs to the technical field of aircraft design, and in particular relates to a variant wing and a variant method that integrates telescopic variable span and rotation variable sweep functions. Background Art

[0002] The design of wide-speed range aircraft requires that it can adapt to the vast airspace from sea level to near space, and a wide speed range from subsonic to hypersonic. The aerodynamic layout requirements of this type of aircraft in different speed domains vary significantly. In the low-speed flight stage, the aircraft usually adopts a wing design with a large aspect ratio and a small sweep angle, as well as a relatively thick airfoil; while in the supersonic flight stage, it tends to use a wing with a small aspect ratio and a large sweep angle, as well as a relatively thin quadrilateral, hexagonal or double-arc airfoil. This design difference makes it difficult for fixed-wing aircraft to meet the aerodynamic performance requirements of high and low speed domains at the same time.

[0003] To address this challenge, traditional aerodynamic design of wide-speed range aircraft mainly adopts the following two methods: one is a new aerodynamic layout design of wide-speed range hypersonic aircraft that gives priority to high-speed cruise performance, such as the waverider configuration design method disclosed in application number 202210131354.4. This design cannot meet the aerodynamic performance requirements of low-speed flight; the other is a wide-speed range airfoil / wing optimization design that adopts a "compromise" approach, such as the methods disclosed in application numbers 202010734140.7 and 202210879045.5. Although it takes into account high and low speed performance to a certain extent, it still cannot achieve optimal aerodynamic characteristics in all speed ranges.

[0004] By adjusting its shape, including local and overall shapes, the morphing aircraft technology gives the aircraft the ability to maintain optimal efficiency and performance in a variety of missions and flight environments, which perfectly matches the stringent requirements of wide-speed range aircraft for aerodynamic performance. For example, patent application number 201922152013.1 discloses a long-endurance, high-maneuverability, wide-speed range unmanned aerial vehicle with retractable wings, but it has limitations in supersonic and hypersonic flight. Patent application number 202110588054.4 introduces a wing deformation device that uses shock waves to control bulges, as well as a wide-speed range hypersonic aircraft. By precisely controlling the position and shape of the bulge, the wing can be adaptively adjusted in different flight states, thereby optimizing the aerodynamic characteristics within a wide speed range.

[0005] In summary, the morphing aircraft technology provides an innovative solution for wide-speed range aircraft to seek a balance between high and low speed aerodynamic performance. However, at present, the contradiction between low-speed and high-speed flight performance is a key challenge in the design of wide-speed range aircraft. The commonly adopted design strategy is to seek a compromise between lift requirements and drag reduction requirements in order to optimize performance in different flight phases. However, this compromise inevitably leads to the aircraft shape failing to achieve optimal aerodynamic performance in all speed ranges. Summary of the invention

[0006] In view of the defects of the prior art, the present invention provides a variant wing and a variant method with integrated telescopic variable span and rotational variable sweep functions, which can effectively solve the above problems.

[0007] The technical solution adopted by the present invention is as follows:

[0008] The present invention provides a variant wing with integrated telescopic variable span and rotation variable sweep functions, comprising an inner wing section (100), an outer wing section (200) and an elastic skin;

[0009] One end of the inner wing section (100) is fixed to the fuselage, and the other end is fixed to one end of the outer wing section (200); the surfaces of the inner wing section (100) and the outer wing section (200) are covered with the elastic skin;

[0010] The inner wing section (100) and the outer wing section (200) are located in the same spanwise plane; the inner wing section (100) performs telescopic movement along the wing span direction in the spanwise plane, thereby adjusting the span length of the inner wing section (100); the outer wing section (200) performs chordwise rotation movement relative to the inner wing section (100) in the spanwise plane, thereby adjusting the sweep angle of the outer wing section (200).

[0011] Preferably, the inner wing section (100) comprises an inner wing fixed rib (101), an inner wing telescopic rib (102), an inner wing reinforcing rib (103), an inner wing telescopic longitudinal wall (104) and an inner wing driving mechanism (105);

[0012] In the span-wise plane, the inner wing fixed rib (101), a plurality of layers of the inner wing telescopic ribs (102) and the inner wing reinforcement rib (103) are sequentially arranged in parallel in a direction gradually moving away from the fuselage; and the inner wing fixed rib (101) is fixed to the fuselage; a plurality of inner wing telescopic longitudinal walls (104) are arranged in parallel between the inner wing fixed rib (101) and the innermost layer of the adjacent inner wing telescopic rib (102), between every two adjacent inner wing telescopic ribs (102), and between the outermost layer of the inner wing telescopic rib (102) and the inner wing reinforcement rib (103); the two ends of each inner wing telescopic longitudinal wall (104) are respectively connected and fixed to the corresponding wing ribs; each inner wing telescopic longitudinal wall (104) is driven by the inner wing driving mechanism (105) to perform telescopic movement along the wing span direction, thereby driving the wing ribs connected at the two ends to perform telescopic movement along the wing span direction, thereby adjusting the span length of the inner wing section (100).

[0013] Preferably, each of the inner wing telescopic longitudinal walls (104) comprises a first sliding groove (1041) and a second sliding groove (1042) which are nested and connected; under the drive of the inner wing driving mechanism (105), one end of the first sliding groove (1041) can slide along the second sliding groove (1042), thereby realizing the telescopic movement of the inner wing telescopic longitudinal wall (104) along the wing span direction.

[0014] Preferably, in a direction gradually approaching the fuselage, each inner wing telescopic longitudinal wall (104) of the outer layer is coaxially arranged with part of the inner wing telescopic longitudinal wall (104) of the adjacent inner layer;

[0015] In a direction gradually moving away from the fuselage, the chord lengths of the inner wing fixed rib (101), the plurality of layers of the inner wing telescopic ribs (102) and the inner wing reinforcement rib (103) gradually decrease, so that the plane projection shape of the inner wing section (100) is a trapezoid.

[0016] Preferably, the outer wing section (200) comprises an outer wing reinforcement rib (201), an outer wing rotation rib (202), an outer wing rotation longitudinal wall (203) and an outer wing rotation drive mechanism (204);

[0017] The outer wing reinforcement rib (201) and the inner wing reinforcement rib (103) are fixedly connected side by side; in the span-wise plane, a plurality of layers of the outer wing rotation ribs (202) are sequentially arranged in parallel in a direction gradually moving away from the outer wing reinforcement rib (201);

[0018] Each layer of the outer wing rotation ribs (202) and the outer wing reinforcement ribs (201) are connected to form a whole through at least two outer wing rotation longitudinal walls (203), and each outer wing rotation longitudinal wall (203) is arranged in parallel, and each outer wing rotation longitudinal wall (203) is hinged to the outer wing reinforcement rib (201) and to each layer of the outer wing rotation ribs (202); through every two outer wing rotation longitudinal walls (203), a parallelogram structure is formed between any two adjacent outer wing rotation ribs (202) and between the innermost layer of the outer wing rotation ribs (202) and the outer wing reinforcement rib (201);

[0019] The hinge point between each outer wing rotating longitudinal wall (203) and the outer wing reinforcing rib (201) is a root hinge point, and the outer wing rotating drive mechanism (204) is configured at the root hinge point; driven by the outer wing rotating drive mechanism (204), each outer wing rotating longitudinal wall (203) is driven to rotate around its root hinge point in the span-wise plane; when each outer wing rotating longitudinal wall (203) rotates, under the action of the parallelogram structure, each outer wing rotating rib (202) is driven to synchronously move forward or backward in the span-wise plane, thereby adjusting the sweep angle of the outer wing section (200).

[0020] Preferably, the chord length of each layer of the outer wing rotation rib (202) gradually decreases in a direction gradually moving away from the outer wing reinforcement rib (201).

[0021] Preferably, the outer wing rotating longitudinal wall (203) is provided with a rotating hole (2031) at a position where it intersects with each layer of the outer wing rotating ribs (202) and at a position where it intersects with the outer wing reinforcing ribs (201); the rotating hole (2031) is equipped with an axle pin (205), thereby realizing the hinge connection between the outer wing rotating longitudinal wall (203) and each layer of the outer wing rotating ribs (202) and the outer wing reinforcing ribs (201).

[0022] The present invention also provides a method for deforming a deformable wing with integrated telescopic variable span and rotational variable sweep functions, comprising the following steps:

[0023] Step S1, when the aircraft changes from high-speed flight to low-speed flight, the inner wing section (100) is controlled to extend along the wing span direction in the span plane, thereby increasing the span of the inner wing section (100), thereby increasing the overall span of the wing, and improving the lift of the aircraft to meet the performance requirements of low-speed flight;

[0024] Step S2, when the aircraft changes from low-speed flight to high-speed flight, on the one hand, the inner wing section (100) is controlled to perform a contraction movement along the wing span direction in the span plane, thereby reducing the span of the inner wing section (100), thereby reducing the overall span of the wing; on the other hand, the outer wing section (200) is controlled to increase the sweep angle of the outer wing section (200), thereby reducing the flight resistance to meet the high-speed flight performance requirements.

[0025] The morphing wing and the morphing method with integrated telescopic variable span and rotation variable sweep functions provided by the present invention have the following advantages:

[0026] The present invention provides a variant wing and a variant method that integrate telescopic variable span and rotation variable sweep functions, which can improve lift during low-speed flight and reduce drag during high-speed flight by adjusting the span and sweep angle of the wing. Specifically, the span of the wing is increased to improve lift during low-speed flight, while the span is reduced and the sweep angle is increased to reduce drag during high-speed flight. The present invention can achieve optimal aerodynamic performance regardless of whether it is in low-speed or high-speed flight state, and significantly improves the adaptability and flight performance of the aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] Figure 1 It is a schematic structural diagram of a variant wing of the present invention that integrates telescopic variable span and rotation variable sweep functions;

[0028] Figure 2 It is a top view of a variant wing of the present invention that integrates telescopic variable span and rotation variable sweep functions;

[0029] Figure 3 It is a structural schematic diagram of the inner wing telescopic longitudinal wall of the present invention;

[0030] Figure 4 It is a structural schematic diagram of the outer wing rotating longitudinal wall of the present invention.

[0031] The names of the components are:

[0032] in:

[0033] 100-inner wing section; 101-inner wing fixed rib; 102-inner wing telescopic rib; 103-inner wing reinforcement rib; 104-inner wing telescopic longitudinal wall; 1041-first sliding groove; 1042-second sliding groove; 105-inner wing driving mechanism;

[0034] 200-outer wing section; 201-outer wing reinforcement rib; 202-outer wing rotation rib; 203-outer wing rotation longitudinal wall; 2031-rotation hole; 204-outer wing rotation drive mechanism; 205-axle pin. DETAILED DESCRIPTION

[0035] In order to make the technical problems, technical solutions and beneficial effects solved by the present invention more clearly understood, the present invention is further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not used to limit the present invention.

[0036] The present invention provides a variant wing and a variant method with integrated telescopic variable span and rotation variable sweep functions, which are used to solve the problem of the compatibility of aerodynamic performance of a wide speed range aircraft during high and low speed flight.

[0037] The variant wing design of the present invention integrates the functions of telescopic variable span and rotation variable sweep. The span of the inner wing of the wing can be adjusted through the telescopic mechanism inside the wing; and the sweep angle of the outer wing of the wing can be changed through the rotation mechanism. Therefore, the present invention enables the aircraft to increase lift by increasing the wing span when flying at low speeds; and reduce drag by reducing the span and increasing the sweep angle when flying at high speeds. Therefore, the present invention achieves optimal aerodynamic performance regardless of whether it is in low-speed or high-speed flight state, significantly improving the adaptability and flight performance of the aircraft. The present invention also elaborates on the wing variant mechanism that realizes the deformation mode, providing a new solution for aircraft design.

[0038] See also Figure 1 to Figure 4 The present invention provides a variant wing with integrated telescopic variable span and rotation variable sweep functions. The variant wing design adopts a multi-wall structure layout to solve the problem that the aircraft is difficult to take into account low and high speed flight. The variant wing includes an inner wing section 100, an outer wing section 200 and an elastic skin;

[0039] One end of the inner wing section 100 is fixed to the fuselage, and the other end is fixed to one end of the outer wing section 200; the inner wing section 100 is used to change the span of the wing, and the outer wing section 200 is used to change the sweep angle of the wing. The surfaces of the inner wing section 100 and the outer wing section 200 are covered with the elastic skin; the elastic skin is a flexible composite material, which can achieve deformation within a certain range and keep the surface smooth.

[0040] The inner wing section 100 and the outer wing section 200 are located in the same spanwise plane.

[0041] The inner wing section 100 performs telescopic movement along the wing span direction in the span-wise plane, thereby adjusting the span length of the inner wing section 100; the outer wing section 200 performs a chord-wise rotational movement relative to the inner wing section 100 in the span-wise plane, thereby adjusting the sweep angle of the outer wing section 200.

[0042] The structures of the inner wing section 100 and the outer wing section 200 are introduced in detail below:

[0043] (I) Inner wing section 100

[0044] The inner wing section 100 includes an inner wing fixed rib 101, an inner wing telescopic rib 102, an inner wing reinforcement rib 103, an inner wing telescopic longitudinal wall 104 and an inner wing driving mechanism 105;

[0045] In the span-wise plane, the inner wing fixed rib 101, several layers of the inner wing telescopic ribs 102 and the inner wing reinforcing rib 103 are arranged in parallel in sequence in a direction gradually away from the fuselage; and the inner wing fixed rib 101 is fixed to the fuselage; a plurality of inner wing telescopic longitudinal walls 104 are arranged in parallel between the inner wing fixed rib 101 and the adjacent innermost layer of the inner wing telescopic rib 102, between every two adjacent inner wing telescopic ribs 102, and between the outermost layer of the inner wing telescopic rib 102 and the inner wing reinforcing rib 103; both ends of each inner wing telescopic longitudinal wall 104 are respectively connected and fixed to the corresponding wing ribs, and each inner wing telescopic longitudinal wall 104 is driven by the inner wing driving mechanism 105 to perform telescopic movement along the wing span direction, thereby driving the wing ribs connected at both ends to perform telescopic movement along the wing span direction, thereby adjusting the span length of the inner wing section 100. Therefore, the inner wing telescopic rib 102 and the inner wing reinforcing rib 103 can move along the wing span direction, or move toward the inner wing fixed rib 101 to reduce the wing span, or move away from the inner wing fixed rib 101 to increase the span. The power for the movement of the inner wing telescopic rib 102 and the inner wing reinforcing rib 103 is provided by the inner wing driving mechanism 105, and the inner wing driving mechanism 105 can be implemented by a driving connecting rod.

[0046] The driving connecting rod connects two adjacent wing ribs, including: the inner wing fixed rib 101 and the adjacent innermost inner wing telescopic rib 102, every two adjacent inner wing telescopic ribs 102 and the outermost inner wing telescopic rib 102 and the inner wing reinforcing rib 103.

[0047] See also Figure 3 As a specific implementation structure, each inner wing telescopic longitudinal wall 104 includes a first sliding groove 1041 and a second sliding groove 1042 which are nested and connected; under the drive of the inner wing driving mechanism 105, one end of the first sliding groove 1041 can slide along the second sliding groove 1042, thereby realizing the telescopic movement of the inner wing telescopic longitudinal wall 104 along the wing span. Therefore, when the inner wing driving mechanism 105 adopts a driving connecting rod, the driving connecting rod can be driven by a hydraulic device to drive the inner wing telescopic longitudinal wall 104 to slide along the sliding groove, thereby driving the inner wing telescopic rib 102 and the inner wing reinforcement rib 103 to move toward or away from the inner wing fixed rib 101.

[0048] As a specific implementation structure, in the direction gradually approaching the fuselage, each of the inner wing telescopic longitudinal walls 104 of the outer layer is coaxially arranged with part of the inner wing telescopic longitudinal walls 104 of the adjacent inner layer; the coaxial inner wing telescopic longitudinal walls 104 form a structure of multiple sliding grooves that are nested and connected in layers.

[0049] As a specific implementation structure, in the direction gradually away from the fuselage, the chord lengths of the inner wing fixed rib 101, several layers of the inner wing telescopic ribs 102 and the inner wing reinforcing rib 103 gradually decrease, so that the plane projection shape of the inner wing section 100 is a trapezoid.

[0050] (ii) Outer wing section 200

[0051] The outer wing section 200 includes an outer wing reinforcement rib 201, an outer wing rotation rib 202, an outer wing rotation longitudinal wall 203 and an outer wing rotation drive mechanism 204;

[0052] The outer wing reinforcement rib 201 and the inner wing reinforcement rib 103 are fixedly connected side by side; in the span-wise plane, several layers of the outer wing rotational ribs 202 are arranged in parallel in a direction gradually away from the outer wing reinforcement rib 201; and, as a preferred structure, the chord length of each layer of the outer wing rotational ribs 202 gradually decreases in a direction gradually away from the outer wing reinforcement rib 201.

[0053] Each layer of the outer wing rotation ribs 202 and the outer wing reinforcement ribs 201 are connected to form a whole through at least two outer wing rotation longitudinal walls 203, and each outer wing rotation longitudinal wall 203 is arranged in parallel, and each outer wing rotation longitudinal wall 203 is hinged to the outer wing reinforcement rib 201 and to each layer of the outer wing rotation ribs 202; through every two outer wing rotation longitudinal walls 203, a parallelogram structure is formed between any two adjacent outer wing rotation ribs 202, and between the innermost layer of the outer wing rotation ribs 202 and the outer wing reinforcement rib 201;

[0054] The hinge point position of each outer wing rotating longitudinal wall 203 and the outer wing reinforcing rib 201 is the root hinge point, and the outer wing rotating driving mechanism 204 is configured at the root hinge point position; driven by the outer wing rotating driving mechanism 204, each outer wing rotating longitudinal wall 203 is driven to rotate around its root hinge point in the span plane; when each outer wing rotating longitudinal wall 203 rotates, under the action of the parallelogram structure, each outer wing rotating rib 202 is driven to move forward or backward synchronously in the span plane, thereby adjusting the sweep angle of the outer wing section 200. Specifically, when each outer wing rotating rib 202 moves forward synchronously in the span plane, the sweep angle of the outer wing section 200 decreases; conversely, when each outer wing rotating rib 202 moves backward synchronously in the span plane, the sweep angle of the outer wing section 200 increases. In the present invention, the front-to-back direction in the forward or backward movement here refers to the direction of the fuselage axis. The direction along the fuselage axis and pointing to the nose is the forward direction; conversely, the direction along the fuselage axis and pointing to the tail is the backward direction.

[0055] Furthermore, through the effect of the parallelogram structure, when the outer wing rotating rib 202 moves forward or backward synchronously in the spanwise plane, the outer wing rotating rib 202 moves away from or close to the outer wing reinforcing rib 201 at the same time.

[0056] See also Figure 4 As a specific implementation structure, the outer wing rotating longitudinal wall 203 is provided with a rotating hole 2031 at the position where it intersects with the outer wing rotating ribs 202 of each layer and at the position where it intersects with the outer wing reinforcing rib 201; the rotating hole 2031 is equipped with an axle pin 205, thereby realizing the hinge connection between the outer wing rotating longitudinal wall 203 and the outer wing rotating ribs 202 of each layer and the outer wing reinforcing rib 201.

[0057] In practical applications, the outer wing rotation drive mechanism 204 uses an outer wing rotation drive motor; the roots of the outer wing rotation drive motor and the outer wing rotation longitudinal wall 203 are both equipped with gears, and the two gears are meshed. Therefore, the rotation of the outer wing rotation drive motor drives the outer wing rotation longitudinal wall 203 to rotate around its root hinge point in the span plane through the transmission of the meshed gears. The outer wing rotation drive motor is arranged between the outer wing reinforcement rib 201 and the inner wing reinforcement rib 103.

[0058] Furthermore, as an improved preferred structure, in addition to the rotational movement, the outer wing rotating longitudinal wall 203 can also be designed as a structure that is retractable along the span direction, so that when the outer wing rotating longitudinal wall 203 rotates and changes the sweep angle, the span of the outer wing section 200 is adjusted by the telescopic movement of the outer wing rotating longitudinal wall 203, so that the span of the outer wing section 200 remains unchanged.

[0059] The present invention also provides a method for transforming a morphing wing with integrated telescopic variable span and rotational variable sweep functions, comprising the following steps:

[0060] Step S1, when the aircraft changes from high-speed flight to low-speed flight, the inner wing section 100 is controlled to extend along the wing span direction in the span plane, thereby increasing the span of the inner wing section 100, thereby increasing the overall span of the wing and improving the lift of the aircraft to meet the low-speed flight performance requirements;

[0061] Step S2, when the aircraft changes from low-speed flight to high-speed flight, on the one hand, the inner wing section 100 is controlled to retract along the wing span direction in the span plane, thereby reducing the span of the inner wing section 100, thereby reducing the overall span of the wing; on the other hand, the outer wing section 200 is controlled to increase the sweep angle of the outer wing section 200, thereby reducing the flight resistance to meet the high-speed flight performance requirements.

[0062] Specifically, when the inner wing section 100 needs to be lengthened, the hydraulic system drives the connecting rod to extend, and the distance between two adjacent ribs (the inner wing fixed rib 101 and the adjacent innermost inner wing telescopic rib 102, every two adjacent inner wing telescopic ribs 102, and the outermost inner wing telescopic rib 102 and the inner wing reinforcing rib 103) increases, wherein the inner wing telescopic rib 102 and the inner wing reinforcing rib 103 move in a direction away from the inner wing fixed rib 101; when the inner wing section 100 needs to be lengthened, it moves in the opposite direction.

[0063] When the sweep angle of the outer wing section 200 needs to be reduced, the rotary drive motor rotates forward, driving the outer wing rotating longitudinal wall 203 to rotate through the gears, the hinged rotating shafts between the outer wing rotating longitudinal wall 203 and each outer wing rotating rib 202 rotate, the outer wing rotating rib 202 moves forward relative to itself, and each outer wing rotating rib 202 moves away from the outer wing reinforcing rib 201; when the sweep angle of the outer wing section 200 needs to be increased, it moves in the reverse direction.

[0064] Traditional fixed-wing aircraft are difficult to balance the contradiction between low and high-speed flight. The present invention proposes a variant wing design and deformation mechanism that integrates telescopic variable span and rotation variable sweep functions. It can increase the lift of the aircraft by increasing the wing span at low speed, reduce the wing span at high speed and increase the wing sweep angle to reduce the aircraft's resistance, effectively solving the above contradiction. The present invention provides a variant wing design and deformation mechanism that integrates telescopic variable span and rotation variable sweep functions. The deformation structure is simple and easy to implement.

[0065] Features described and / or illustrated above for one embodiment may be used in the same or similar manner in one or more other embodiments, and / or combined with or used in place of features in other embodiments.

[0066] The above is only a preferred embodiment of the present invention. It should be pointed out that for ordinary technicians in this technical field, several improvements and modifications can be made without departing from the principle of the present invention. These improvements and modifications should also be considered as the scope of protection of the present invention.

Claims

1. A variable-length wing with integrated telescopic variable-span and rotation variable-sweep functions, characterized in that: It comprises an inner wing section (100), an outer wing section (200) and an elastic skin; One end of the inner wing section (100) is fixed to the fuselage, and the other end is fixed to one end of the outer wing section (200); the surfaces of the inner wing section (100) and the outer wing section (200) are covered with the elastic skin; The inner wing section (100) and the outer wing section (200) are located in the same spanwise plane; the inner wing section (100) performs telescopic movement along the wing span direction in the spanwise plane, thereby adjusting the span length of the inner wing section (100); the outer wing section (200) performs chordwise rotation movement relative to the inner wing section (100) in the spanwise plane, thereby adjusting the sweep angle of the outer wing section (200).

2. The variant wing with integrated telescopic variable span and rotational variable sweep functions according to claim 1, characterized in that: The inner wing section (100) comprises an inner wing fixed rib (101), an inner wing telescopic rib (102), an inner wing reinforcing rib (103), an inner wing telescopic longitudinal wall (104) and an inner wing driving mechanism (105); In the span-wise plane, the inner wing fixed rib (101), a plurality of layers of the inner wing telescopic ribs (102) and the inner wing reinforcement rib (103) are sequentially arranged in parallel in a direction gradually moving away from the fuselage; and the inner wing fixed rib (101) is fixed to the fuselage; a plurality of inner wing telescopic longitudinal walls (104) are arranged in parallel between the inner wing fixed rib (101) and the innermost layer of the adjacent inner wing telescopic rib (102), between every two adjacent inner wing telescopic ribs (102), and between the outermost layer of the inner wing telescopic rib (102) and the inner wing reinforcement rib (103); the two ends of each inner wing telescopic longitudinal wall (104) are respectively connected and fixed to the corresponding wing ribs; each inner wing telescopic longitudinal wall (104) is driven by the inner wing driving mechanism (105) to perform telescopic movement along the wing span direction, thereby driving the wing ribs connected at the two ends to perform telescopic movement along the wing span direction, thereby adjusting the span length of the inner wing section (100).

3. The variant wing with integrated telescopic variable span and rotational variable sweep functions according to claim 2, characterized in that: Each of the inner wing telescopic longitudinal walls (104) comprises a first sliding groove (1041) and a second sliding groove (1042) which are nested and connected; under the drive of the inner wing driving mechanism (105), one end of the first sliding groove (1041) can slide along the second sliding groove (1042), thereby realizing the telescopic movement of the inner wing telescopic longitudinal wall (104) along the wing span direction.

4. The variant wing with integrated telescopic variable span and rotational variable sweep functions according to claim 2, characterized in that: In a direction gradually approaching the fuselage, each inner wing telescopic longitudinal wall (104) of the outer layer is coaxially arranged with part of the inner wing telescopic longitudinal wall (104) of the adjacent inner layer; In a direction gradually moving away from the fuselage, the chord lengths of the inner wing fixed rib (101), the plurality of layers of the inner wing telescopic ribs (102) and the inner wing reinforcement rib (103) gradually decrease, so that the plane projection shape of the inner wing section (100) is a trapezoid.

5. The variant wing with integrated telescopic variable span and rotational variable sweep functions according to claim 2, characterized in that: The outer wing section (200) comprises an outer wing reinforcement rib (201), an outer wing rotation rib (202), an outer wing rotation longitudinal wall (203) and an outer wing rotation drive mechanism (204); The outer wing reinforcement rib (201) and the inner wing reinforcement rib (103) are fixedly connected side by side; in the span-wise plane, a plurality of layers of the outer wing rotation ribs (202) are sequentially arranged in parallel in a direction gradually moving away from the outer wing reinforcement rib (201); Each layer of the outer wing rotation ribs (202) and the outer wing reinforcement ribs (201) are connected to form a whole through at least two outer wing rotation longitudinal walls (203), and each outer wing rotation longitudinal wall (203) is arranged in parallel, and each outer wing rotation longitudinal wall (203) is hinged to the outer wing reinforcement rib (201) and to each layer of the outer wing rotation ribs (202); through every two outer wing rotation longitudinal walls (203), a parallelogram structure is formed between any two adjacent outer wing rotation ribs (202) and between the innermost layer of the outer wing rotation ribs (202) and the outer wing reinforcement rib (201); The hinge point between each outer wing rotating longitudinal wall (203) and the outer wing reinforcing rib (201) is a root hinge point, and the outer wing rotating drive mechanism (204) is configured at the root hinge point; driven by the outer wing rotating drive mechanism (204), each outer wing rotating longitudinal wall (203) is driven to rotate around its root hinge point in the span-wise plane; when each outer wing rotating longitudinal wall (203) rotates, under the action of the parallelogram structure, each outer wing rotating rib (202) is driven to synchronously move forward or backward in the span-wise plane, thereby adjusting the sweep angle of the outer wing section (200).

6. The variant wing with integrated telescopic variable span and rotational variable sweep functions according to claim 5, characterized in that: In a direction gradually moving away from the outer wing reinforcement rib (201), the chord length of each layer of the outer wing rotation rib (202) gradually decreases.

7. The variant wing with integrated telescopic variable span and rotational variable sweep functions according to claim 5, characterized in that: The outer wing rotating longitudinal wall (203) is provided with a rotating hole (2031) at a position where it intersects with each layer of the outer wing rotating ribs (202) and at a position where it intersects with the outer wing reinforcing rib (201); the rotating hole (2031) is equipped with an axle pin (205), thereby realizing the hinge connection between the outer wing rotating longitudinal wall (203) and each layer of the outer wing rotating ribs (202) and the outer wing reinforcing rib (201).

8. A method for deforming a deformable wing with integrated telescopic variable span and rotational variable sweep functions as claimed in claim 5, characterized in that: The following steps are involved: Step S1, when the aircraft changes from high-speed flight to low-speed flight, the inner wing section (100) is controlled to extend along the wing span direction in the span plane, thereby increasing the span of the inner wing section (100), thereby increasing the overall span of the wing, and improving the lift of the aircraft to meet the performance requirements of low-speed flight; Step S2, when the aircraft changes from low-speed flight to high-speed flight, on the one hand, the inner wing section (100) is controlled to perform a contraction movement along the wing span direction in the span plane, thereby reducing the span of the inner wing section (100), thereby reducing the overall span of the wing; on the other hand, the outer wing section (200) is controlled to increase the sweep angle of the outer wing section (200), thereby reducing the flight resistance to meet the high-speed flight performance requirements.

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