Wing structure capable of multi-dimensional continuous variant

Abstract

The invention belongs to the technical field of aviation aircrafts, and particularly discloses a multi-dimensional continuous variant wing structure which comprises a fixed plate, an inner wing section, an outer wing section, a sweepback actuating mechanism and a telescopic actuating mechanism, the inner wing section is driven by a sweepback actuating mechanism to rotate around the wing root in a spanwise plane so as to change the sweepback angle of the wing; the outer wing section is slidably connected to the inner wing section and is driven by a telescopic actuating mechanism to stretch in the spanwise direction so as to change the extension length of the wing; the front end and the tail end of the rear side of the inner wing section are connected with the flexible rear edge and the rigid rear edge correspondingly, and the flexible rear edge is used for changing the bending degree of the rear edge. The rigid trailing edge is used for changing the trailing edge deflection angle; the sweepback actuating mechanism comprises a rotating disc, a push rod motor and a rocker arm, and the push rod motor drives the rocker arm to enable the inner wing section to rotate around the rotating disc to achieve sweepback changing. According to the invention, the multi-dimensional variation of the wings can be realized through simple mechanism combination, and the aerodynamic performance of the aircraft is improved, so that the aircraft can adapt to different flight conditions, and various flight task requirements are realized.

Description

Technical Field

[0001] The present invention relates to the technical field of aviation aircraft, and in particular to a wing structure capable of multi-dimensional continuous deformation. Background Art

[0002] Traditional aircraft designs employ fixed wings with fixed geometric shapes. This design has significant limitations: Because it cannot dynamically and adaptively adjust key aerodynamic parameters such as wing camber, span, and sweep angle during flight, fixed-wing aircraft struggle to simultaneously meet the combined demands of wide-speed range and multi-mission flight.

[0003] Specifically, the main contradictions faced by fixed-wing design are: on the one hand, when the aircraft is flying at low speed, the wing is usually required to have a large aspect ratio to provide more lift. By increasing the trailing edge curvature, the lift coefficient can be increased and the stall angle range can be expanded; on the other hand, when the aircraft is flying at high speed, the wing is usually required to have a large sweep angle to delay the generation of shock waves and reduce wave drag; in addition, by changing the deflection angle of the rudder, the active control of the aircraft's flight attitude and aerodynamic load can be achieved.

[0004] This shows that fixed-geometry wing designs inherently lack adaptability when handling diverse flight conditions and mission profiles, from low-speed to high-speed, and from takeoff and landing to cruising. The contradiction between increased shock wave drag during high-speed cruising and insufficient lift reserve during low-speed takeoff and landing is particularly prominent. Therefore, there is an urgent need to develop an intelligent wing structure with multi-dimensional morphing capabilities that can autonomously adjust its key aerodynamic shape parameters in real time based on flight conditions and mission requirements, and coordinate control with control surfaces, thereby fundamentally improving the overall performance of the aircraft in complex flight environments. Summary of the Invention

[0005] The purpose of the present invention is to provide a wing structure that can be continuously deformed in multiple dimensions to solve the above-mentioned technical problems existing in the prior art.

[0006] To achieve the above-mentioned objectives, the present invention provides the following solutions: a wing structure that can be continuously deformed in multiple dimensions, comprising: a fixed plate for connecting to the aircraft fuselage; an inner wing section, comprising an inner wing section base plate, an inner wing section frame and an inner wing section skin; one end of the inner wing section base plate is hinged to the fixed plate, and is driven by a sweep actuator to rotate around the wing root in the span-wise plane to change the wing sweep angle; an outer wing section, slidably connected to the inner wing section, and is driven by a telescopic actuator to telescope along the span-wise direction to change the wing span; a flexible trailing edge, connected to the rear side of the front end of the inner wing section, for changing the trailing edge curvature; a rigid trailing edge, hinged to the rear side of the end of the inner wing section, for changing the trailing edge deflection angle; the sweep actuator comprises a turntable, a push rod motor and a rocker arm, the two ends of the rocker arm are respectively hinged to the push rod motor and the inner wing section, and the push rod motor drives the rocker arm to rotate the inner wing section around the turntable to achieve variable sweep. Based on the above structure, the present invention realizes active coordinated adjustment of the wing sweep angle, span, trailing edge camber and deflection angle by integrating the swept actuator mechanism, telescopic actuator mechanism, flexible trailing edge and rigid trailing edge, thereby solving the problem that traditional fixed wings cannot take into account wide speed range and multi-task requirements.

[0007] Furthermore, the telescopic actuating mechanism includes: a rotating servo and bidirectional winch fixed to the inner wing section; A guide pulley and a fixed pulley fixed to the inner wing section frame; A wire rope with one end fixed to the outer wing section and the other end wound around a fixed pulley and a two-way winch; A telescopic tube is sleeved inside the telescopic sleeve of the inner wing section and fixed to the outer wing section.

[0008] Furthermore, the bidirectional winch is provided with two layers of grooves, one end of the steel wire rope is wound clockwise around the upper groove, and the other end is wound counterclockwise around the lower groove; when the bidirectional winch rotates counterclockwise, the upper groove tightens the steel wire rope and the lower groove releases the steel wire rope; when the bidirectional winch rotates clockwise, the upper groove releases the steel wire rope and the lower groove retracts the steel wire rope, driving the outer wing section to retract the inner wing section.

[0009] Furthermore, the telescopic actuating mechanism also includes a tensioning device, which includes a fixed block fixed to the inner wing section base plate, a tensioning block connected to the fixed block through a long screw, and a return spring sleeved on the long screw, and the rotary servo is fixed on the tensioning block.

[0010] Furthermore, the flexible trailing edge includes a flexible base plate, a flexible inner rotation plate and a flexible outer rotation plate which are hinged in sequence, the flexible base plate is hinged to the inner wing section, and the flexible inner rotation plate and the flexible outer rotation plate are driven by a dual-axis servo.

[0011] Furthermore, the dual-axis servos are provided with two groups; one group is fixed on the flexible substrate, and its output shaft is connected to the servo rocker, and the end of the servo rocker is connected to the rigid shaft through a slot, and the rigid shaft is fixed to the rotating shaft of the flexible inner rotating plate to drive the flexible inner rotating plate; the other group is fixed on the flexible inner rotating plate, and its output shaft is transmission-connected to the flexible outer rotating plate to drive the flexible outer rotating plate.

[0012] Furthermore, the flexible trailing edge further comprises an elastic skin, and porous flexible material is filled between the flexible substrate, the flexible inner turning plate, the flexible outer turning plate and the elastic skin.

[0013] Furthermore, an extension arm is added to the rocker arm of the sweep actuating mechanism, and the extension arm is hinged to the inner wing section of the other wing system, so that a single push rod motor can synchronously drive the two wing systems to change the sweep.

[0014] Furthermore, the inner wing section skeleton includes a rear short wing rib and a rear long wing rib, and the rear short wing rib and the rear long wing rib are provided with a slot for accommodating the outer wing section, and the size of the slot is larger than the cross section of the outer wing section.

[0015] Furthermore, a sealing device is installed on the penultimate rear short rib and the rear long rib at the end of the inner wing section skeleton, and the sealing device is made of elastic material.

[0016] As can be seen from the above technical solution, the present invention proposes a multi-dimensional, continuously variable wing structure, integrating variable sweep, variable span, variable trailing edge camber, and variable trailing edge deflection angle. This solves the problem that traditional fixed wings or single-variable wings cannot meet the requirements of a wide speed range and multiple missions. This multi-dimensional wing configuration, achieved through a simple combination of mechanisms, improves the aerodynamic performance of the aircraft, enables it to adapt to different flight conditions, and fulfills various flight mission requirements. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0018] Figure 1 This is a schematic structural diagram of an outer wing section of a wing structure capable of multi-dimensional continuous deformation in an embodiment of the present invention in an extended state; Figure 2 This is a schematic structural diagram of the inner wing section of the wing structure capable of multi-dimensional continuous deformation according to an embodiment of the present invention with the skin removed; Figure 3 Schematic diagram of the structure of the inner wing section skeleton in an embodiment of the present invention; Figure 4 Schematic diagram of the structure of the swept actuating mechanism in an embodiment of the present invention; Figure 5 Schematic diagram of posture transformation of the swept-back actuating mechanism in an embodiment of the present invention; Figure 6 This is a schematic structural diagram of the telescopic actuating mechanism in an embodiment of the present invention; Figure 7 for Figure 6 A partial enlarged view of point A in the middle; Figure 8 for Figure 6 A partial enlarged view of point B in the middle; Figure 9 for Figure 6 A partial enlarged view of point C in the middle; Figure 10 Schematic diagram of the connection position of the steel wire rope in the bidirectional winch in an embodiment of the present invention; Figure 11 A top view of the outer wing section extending beyond the inner wing section in an embodiment of the present invention; Figure 12 for Figure 11 A partial enlarged view of point D in the middle; Figure 13 Schematic diagram of the structure of the rigid trailing edge in an embodiment of the present invention; Figure 14 Schematic diagram of the structure of the flexible trailing edge in an embodiment of the present invention; Figure 15 for Figure 14 Cross-sectional view of EE; Figure 16 Schematic diagram of the connection between the dual-axis servo, the servo rocker, and the rigid shaft in an embodiment of the present invention.

[0019] Figure 17 This is a diagram showing the change in the flexible trailing edge curvature achieved by the steering gear rotating in an embodiment of the present invention; In the figure: 1. fixed plate; 2. turntable; 21. turntable base; 22. runner; 3. inner wing section; 31. inner wing section base plate; 32. tensioning device; 321. fixed block; 322. tensioning block; 323. return spring; 324. long screw; 33. rotary servo; 34. two-way winch; 35. wire rope; 36. inner wing section frame; 361. horizontal bar; 362. long wing spar; 363. front short wing spar; 364. rear short wing spar; 365. front long wing rib; 366. front short wing rib; 367. rear long wing rib; 368. rear short wing rib; 369. telescopic sleeve; 37. sealing device; 38. guide pulley; 39. fixed Pulley; 4. Push rod motor; 5. Rocker arm; 6. Flexible trailing edge; 61. Flexible base plate; 62. Flexible inner rotating plate; 63. Flexible outer rotating plate; 64. Dual-axis servo; 641. First dual-axis servo; 642. Second dual-axis servo; 643. Third dual-axis servo; 644. Fourth dual-axis servo; 65. Servo rocker; 66. Rigid shaft; 7. Outer wing section; 71. Winglet rib; 72. Winglet spar; 73. Small cross bar; 74. Telescopic tube; 75. Rope fixing block; 76. Winglet front plate; 8. Rigid trailing edge; 81. Rudder surface servo; 82. Rudder surface rib; 83. Rudder surface reinforcement tube; 84. Rudder surface spar; 85. Rudder surface turntable. DETAILED DESCRIPTION

[0020] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0021] In order to make the above-mentioned objects, features and advantages of the present invention more obvious and easy to understand, the present invention is further described in detail below with reference to the accompanying drawings and specific embodiments.

[0022] Reference Figures 1 to 17 As shown, this embodiment provides a wing structure capable of multi-dimensional continuous deformation, including a fixed plate 1, an inner wing section 3, a flexible trailing edge 6, an outer wing section 7, a rigid trailing edge 8, and a sweep actuating mechanism for driving the inner wing section 3 to rotate and change the sweep, and a telescopic actuating mechanism for driving the outer wing section 7 to telescope and change the length. For the convenience of description, the end of the inner wing section 3 close to the fixed plate 1 is defined as the front end, and the end close to the outer wing section 7 is defined as the end. The flexible trailing edge 6 is connected to the rear side of the front end of the inner wing section 3, and the rigid trailing edge 8 is connected to the rear side of the end of the inner wing section 3. The inner wing section 3 and the outer wing section 7 are located in the same spanwise plane.

[0023] like Figure 1 、 Figure 2 and Figure 6As shown, in this embodiment, the fixed plate 1 is provided with a plurality of through holes for fixed connection with the aircraft. A turntable 2 is connected to the fixed plate 1. The turntable 2 includes a turntable base 21 and a runner 22. The turntable base 21 is fixedly connected to the fixed plate 1, and the runner 22 is rotatably connected to the turntable base 21. The inner wing section 3 is mounted on the runner 22. A protruding structure is provided on the inner wing section base plate 31 of the inner wing section 3, and a rocker arm 5 is hinged on the protruding structure. The rocker arm 5 has a large end and a small end, wherein the large end is hinged to the protruding structure, and the small end is hinged to the output end of the push rod motor 4. The inner wing section 3 is connected to the outer wing section 7 via a telescopic guide mechanism and a steel wire rope 35. The telescopic guide mechanism consists of a telescopic sleeve 369 and a telescopic tube 74. A flexible trailing edge 6 is provided on the rear side of the front end of the inner wing section 3, and a rigid trailing edge 8 is provided on the rear side of the end of the inner wing section 3.

[0024] like Figure 4 and Figure 5 As shown, in this embodiment, the variable sweep function of the inner wing section 3 is achieved by a sweep actuation mechanism, which includes a turntable 2, a push rod motor 4, and a rocker arm 5. The push rod motor 4 is fixed to the fixed plate 1. One end of the rocker arm 5 is hinged to the output end of the push rod motor 4, and the other end is hinged to a raised structure on the wing section base plate. The push rod motor 4 and the rocker arm 5 together form an offset crank slider mechanism. The push rod motor 4 drives the rocker arm 5, causing the inner wing section base plate 31 to rotate about the turntable base 21, and the remaining parts fixed to the inner wing section base plate 31 rotate accordingly, thereby achieving the variable sweep function of the entire inner wing section 3.

[0025] In a specific embodiment, an extension arm may be added to the rocker arm 5 of the sweep actuator mechanism, which is hinged to the inner wing section 3 of another wing system, so that a single push rod motor 4 can simultaneously drive the two wing systems to change the sweep angle.

[0026] like Figure 3 and Figure 4As shown, in this embodiment, the inner wing section 3 includes an inner wing section base plate 31, a tensioning device 32, a rotary servo 33, a bidirectional winch 34, a steel cable 35, an inner wing section frame 36, a sealing device 37, a pulley assembly, and an inner wing section skin. The inner wing section frame 36 includes a horizontal bar 361, a long wing spar 362, a front short wing spar 363, a rear short wing spar 364, a front long wing rib 365, a front short wing rib 366, a rear long wing rib 367, a rear short wing rib 368, and a telescopic sleeve 369. The first front long wing rib 365, the first front short wing rib 366, and the second front short wing rib 366 at the front end of the inner wing section frame 36 are provided with through slots. The inner wing section base plate 31 is provided with a flange, the base of which is fixedly connected to the front surface of the first front long rib 365 at the front end of the inner wing section frame 36. The flange extends from the through slot between the second and third front short ribs 366 at the front end of the inner wing section frame 36, and is fixed to the first front long rib 365 and the first two front short ribs 366. Two telescopic sleeves 369 are fixed to the through holes set between the front long rib 365 and the front short rib 366, and extend all the way to the front end of the first rear long rib 367. The telescopic sleeves 369 are hollow structures. The pulley assembly includes several guide pulleys 38 and fixed pulleys 39. The guide pulleys 38 are arranged at regular intervals on each rib of the inner wing section frame 36. The fixed pulley 39 is fixed to the upper end of the penultimate rear short rib 368 at the end of the inner wing section frame 36. The sealing device 37 is installed on the penultimate rear short rib 368 and the rear long rib 367 at the end of the inner wing section frame 36.

[0027] In this embodiment, the telescopic actuation mechanism includes a tensioning device 32, a rotary servo 33, a bidirectional winch 34, a telescopic sleeve 369, a telescopic tube 74, a steel wire rope 35, a guide pulley 38, a fixed pulley 39, and a rope fixing block 75. The tensioning device 32 is fixed to a notch in the inner wing section base plate 31, the rotary servo 33 is fixed to the tensioning device 32, and the output end of the servo is tightly connected to the bidirectional winch 34. The guide pulley 38 is fixed to a rib of the inner wing section frame 36, the fixed pulley 39 is fixed to the end rib of the inner wing section frame 36, the telescopic sleeve 369 is connected to the front long rib 365 and the front short rib 366 of the inner wing section frame 36, and a portion of the telescopic tube 74 is fixed to the outer wing section 7, while the other portion is sheathed in the telescopic sleeve 369 and can slide within the telescopic sleeve 369. The steel wire rope 35 is wound between the bidirectional winch 34 and the fixed pulley 39 and fixed to the outer wing section 7 via the rope fixing block 75.

[0028] The rotary servo 33 in the telescopic actuating mechanism is a 360-degree continuously rotating servo, which can rotate continuously. The wire rope 35 is always in a tensioned state. Each rib of the inner wing section 3 is provided with a through hole. After one end of the wire rope 35 is fixed to the outer wing section 7, it passes through the through hole and is wound around the lower groove of the two-way capstan 34. After the other end of the wire rope 35 passes around the fixed pulley 39 on the rib of the inner wing section skeleton 36, it passes through the through hole and is wound around the upper groove of the two-way capstan 34.

[0029] like Figure 3 and Figure 6 As shown, the outer wing section 7 described in this embodiment includes a number of small wing ribs 71, small wing spars 72, small cross bars 73, telescopic tubes 74, rope fixing blocks 75, winglet front plates 76, and outer wing section skin. The telescopic tubes 74 are twice the length of the main structure of the outer wing section 7. Half of the length of the telescopic tubes 74 is connected to the small wing ribs 71 through holes in the small wing ribs 71, which is used to strengthen the structural strength of the outer wing section 7. The outer ring of the other half of the length of the telescopic tubes 74 is inserted into the inner ring of the telescopic sleeve 369 of the inner wing section 3. The outer diameter of the telescopic tube 74 is slightly smaller than the inner diameter of the telescopic sleeve 369, allowing the telescopic tube 74 to slide within the inner ring of the telescopic sleeve 369. The rear short ribs 368 and rear long ribs 367 of the inner wing section frame 36 are provided with slots, the size of which is slightly larger than the cross-section of the outer wing section 7. The sealing device 37 is made of elastic materials such as rubber. On the one hand, it is used to ensure a certain airtightness between the inner wing section 3 and the outer wing section 7. On the other hand, it supports and guides the outer wing section 7. At the same time, it can also buffer the vibration generated by the outer wing section 7 during flight.

[0030] like Figure 7 As shown, the tensioning device 32 includes a fixed block 321, a tensioning block 322, a return spring 323 and a long screw 324. The fixed block 321 is installed at the front end of the slot of the inner wing section base plate 31. The tensioning block 322 is provided with a slot and is installed at a certain distance behind the fixed block 321. The long screw 324 connects the fixed block 321 and the tensioning block 322. The return spring 323 is sleeved on the long screw 324 located between the fixed block 321 and the tensioning block 322. By twisting the long screw 324, the tensioning block 322 can be driven to move in a small range relative to the fixed block 321. The rotary servo 33 is installed on the tensioning block 322. The bidirectional capstan 34 is fixed to the output shaft of the rotary servo 33.

[0031] like Figures 6 to 10As shown, in this embodiment, one end of the wire rope 35 is fixed in the upper groove of the bidirectional winch 34. It is wound clockwise a certain number of times, then drawn out, passing through the guide pulley 38 and the fixed pulley 39, and finally fixed to the rope fixing block 75 on the outer wing section 7. The other end of the wire rope 35 is fixed in the lower groove of the bidirectional winch 34. It is wound counterclockwise a certain number of times, then drawn out, passing through the guide pulley 38, and finally fixed to another rope fixing block 75 on the outer wing section 7. After the wire rope 35 is installed, the long screw 324 of the tensioning device 32 is tightened to ensure the stability of the outer wing section 7 in its telescopic state. The total length of the wire rope 35 wound around the bidirectional winch 34 is greater than the travel of the outer wing section 7 on the inner wing section 3. This connection method forms a closed loop between the bidirectional winch 34, the fixed pulley 39, and the rope fixing block 75. When the two-way winch 34 rotates clockwise under the drive of the rotary servo 33, the wire rope 35 is released from the upper layer of the two-way winch 34, passes through the loop and finally enters the lower layer of the two-way winch 34, while driving the outer wing section 7 to retract into the inner wing section 3. Similarly, when the two-way winch 34 rotates counterclockwise, the wire rope 35 drives the outer wing section 7 to extend out of the inner wing section 3. The guide pulley 38 is used to guide the movement path of the wire rope 35 to ensure that its movement process will not interfere with the aircraft body, thereby ensuring the reliability of the movement. Figure 6 and Figure 13 As shown, when the outer wing section 7 is extended, the steel wire rope 35 drives the rope fixing block 75 to move toward the fixed pulley 39, thereby driving the outer wing section 7 to extend.

[0032] like Figure 13 As shown, the rigid trailing edge 8 in this embodiment includes a rudder surface servo 81, a rudder surface rib 82, a rudder surface reinforcement tube 83, a rudder surface spar 84, a rudder surface turntable 85, and a rudder surface skin. The rudder surface rib 82, the rudder surface reinforcement tube 83, and the rudder surface spar 84 together form the rudder surface skeleton. There are two rudder surface servos 81, mounted on the rudder surface ribs 82 at both ends of the rudder surface skeleton. The two rudder surface turntables 85 are respectively fixed to the output shafts of the two rudder surface servos 81. The rudder surface ribs 82 at both ends are provided with through holes to ensure that the relative rotation of the rudder surface turntables 85 and the output shafts of the rudder surface servos 81 is not hindered. The two rudder surface turntables 85 are respectively fixed to the rear long rib 367 at the end of the inner wing section skeleton 36. In the initial state of the servo, the rudder surface skin is flush with the surface of the inner wing section skin. When the rudder servo 81 rotates, since the rudder turntable 85 is fixed on the rib of the inner wing section frame 36, the rudder servo 81 and the rudder frame fixed to it rotate relative to the rudder turntable 85, that is, rotate relative to the inner wing section 3, thereby realizing the function of changing the rudder deflection angle.

[0033] like Figures 14 to 17As shown, the flexible trailing edge 6 in this embodiment includes a flexible substrate 61, a flexible inner rotation plate 62, a flexible outer rotation plate 63, a dual-axis servo 64, a servo rocker 65, a rigid shaft 66 and an elastic skin. The flexible substrate 61 is fixed on the front short wing beam 363 of the inner wing section skeleton 36. The flexible inner rotation plate 62 is hinged to the flexible substrate 61. The flexible outer rotation plate 63 is hinged to the flexible inner rotation plate 62. Porous flexible materials such as sponge are filled between the flexible substrate 61, the flexible inner rotation plate 62 and the flexible outer rotation plate 63 and the elastic skin. Slots are provided on the flexible inner rotation plate 62, the flexible outer rotation plate 63 and the flexible substrate 61 for installing the dual-axis servo 64. The dual-axis servo 64 has two synchronously rotating output shafts. In this embodiment, the dual-axis servo 64 is provided in two groups. The first group is fixed on the flexible substrate 61, including: Figure 14 The first dual-axis servo 641 and the second dual-axis servo 642 are shown. The output shafts at both ends of the two servos are mounted with servo rockers 65. The servo rockers 65 are concentrically arranged with the rotation axis of the flexible inner rotating plate 62. A rigid shaft 66 is fixed to the distal end of the rotation axis of the flexible inner rotating plate 62. The distal end of the servo rocker 65 is provided with a notch, forming a groove connection with the corresponding rigid shaft 66. Similarly, the second set of servos is fixed to the flexible inner rotating plate 62, including Figure 14 The third dual-axis servo 643 and the fourth dual-axis servo 644 are shown, and the servo rocker 65 on the two servos is connected to the rigid shaft 66 fixed at the far end of the rotating shaft of the flexible outer rotating plate 63.

[0034] When the dual-axis servo 64 rotates, it drives the servo rocker 65 to rotate. The servo rocker 65 acts on the rigid shaft 66, thereby driving the flexible outer rotating plate 63 to rotate relative to the flexible inner rotating plate 62, or the flexible inner rotating plate 62 to rotate relative to the flexible substrate 61. The structures of the flexible substrate 61 and the flexible inner rotating plate 62 mechanically limit the relative rotation angle. For example, when the flexible inner rotating plate 62 rotates relative to the flexible substrate 61, the servo first drives the flexible inner rotating plate 62 to perform rigid rotation. When the rotation limit is reached, the servo continues to rotate. Because the flexible inner rotating plate 62 is made of elastically deformable flexible material, the rigid shaft 66 produces relative displacement within the notch of the servo rocker 65, simultaneously driving the flexible inner rotating plate 62 to undergo elastic bending deformation, achieving a change in curvature. Similarly, the movement of the flexible outer rotating plate 63 relative to the flexible inner rotating plate 62 also involves rigid rotation first, followed by a change in flexible curvature. Both the flexible inner rotating plate 62 and the flexible outer rotating plate 63 are driven by their corresponding dual-axis servo 64, ensuring uniform rotation. Through the joint control of the four dual-axis steering gears 64, smooth and stable camber changes of the flexible trailing edge 6 can be achieved.

[0035] Compared with the prior art, the present invention has at least the following beneficial effects: The present invention proposes a wing structure capable of continuous multi-dimensional change, achieving multi-dimensional wing changeability through a simple combination of mechanisms. A push rod motor 4 drives a rocker arm 5 to change the wing's sweep angle, maintaining the wing's variable sweep state through the push rod motor 4's excellent self-locking properties. A rotating servo 33 drives the movement of a wire rope 35 to extend and retract the outer wing section 7, reducing the weight of the inner wing section 3 while reducing the number of components. The servo's excellent holding torque and the constant tension of the wire rope 35 effectively maintain the outer wing section 7 in its extended or retracted state. Furthermore, the flexible trailing edge 6 utilizes a combination of a flexible structure and an elastic skin, as well as rigid and flexible rotation, to achieve smooth changes in trailing edge camber. Both the trailing edge camber and the rudder deflection angle are driven by the servo, effectively maintaining the stability of the trailing edge camber and deflection angle of the inner wing section 3. The wing's variable sweep, variable span, variable trailing edge camber, and variable trailing edge deflection angle are all actively driven, which can actively adjust the wing's shape according to actual working conditions, solving the problem that traditional fixed-wing aircraft cannot take into account wide speed range and multi-task requirements.

[0036] In the description of the present invention, it should be understood that the terms "longitudinal", "transverse", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating the orientation or position relationship, are based on the orientation or position relationship shown in the accompanying drawings, and are only for the convenience of describing the present invention, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention.

[0037] The embodiments described above are merely descriptions of preferred embodiments of the present invention and are not intended to limit the scope of the present invention. Without departing from the spirit of the present invention, various modifications and improvements made to the technical solutions of the present invention by persons skilled in the art should fall within the scope of protection defined by the claims of the present invention.

Claims

1. A wing structure capable of multi-dimensional continuous deformation, characterized in that: include: A fixing plate (1) for connecting to the aircraft fuselage; An inner wing section (3) comprises an inner wing section base plate (31), an inner wing section frame (36) and an inner wing section skin; one end of the inner wing section base plate (31) is hinged to the fixed plate (1), and is driven by a sweep actuator to rotate around the wing root in the spanwise plane to change the wing sweep angle; An outer wing section (7) is slidably connected to the inner wing section (3) and is driven to extend and retract along the span direction by a telescopic actuating mechanism to change the wing span; A flexible trailing edge (6) connected to the rear side of the front end of the inner wing section (3) for changing the curvature of the trailing edge; A rigid trailing edge (8) is hinged to the rear side of the end of the inner wing section (3) and is used to change the trailing edge deflection angle; The sweepback actuating mechanism comprises a turntable (2), a push rod motor (4) and a rocker arm (5), wherein both ends of the rocker arm (5) are respectively hinged to the push rod motor (4) and the inner wing section (3), and the push rod motor (4) drives the rocker arm (5) to rotate the inner wing section (3) around the turntable (2) to achieve variable sweepback.

2. The multi-dimensional continuously deformable wing structure according to claim 1, characterized in that: The telescopic actuating mechanism comprises: A rotary servo (33) and a bidirectional winch (34) fixed to the inner wing section (3); A guide pulley (38) and a fixed pulley (39) fixed to the inner wing section frame (36); A steel wire rope (35) having one end fixed to the outer wing section (7) and the other end wound around a fixed pulley (39) and a bidirectional winch (34); A telescopic tube (74) is sleeved inside the telescopic sleeve (369) of the inner wing section (3) and fixed to the outer wing section (7).

3. The multi-dimensional continuously deformable wing structure according to claim 2, characterized in that: The bidirectional winch (34) is provided with upper and lower grooves, one end of the steel wire rope (35) is wound clockwise around the upper groove, and the other end is wound counterclockwise around the lower groove; when the bidirectional winch (34) rotates counterclockwise, the upper groove tightens the steel wire rope (35) while the lower groove releases the steel wire rope (35); when the bidirectional winch (34) rotates clockwise, the upper groove releases the steel wire rope (35) while the lower groove retracts the steel wire rope (35), thereby driving the outer wing section (7) to retract into the inner wing section (3).

4. The multi-dimensional continuously deformable wing structure according to claim 2, characterized in that: The telescopic actuating mechanism further includes a tensioning device (32), the tensioning device (32) including a fixed block (321) fixed to the inner wing section base plate (31), a tensioning block (322) connected to the fixed block (321) via a long screw (324), and a return spring (323) sleeved on the long screw (324), and the rotary servo (33) is fixed on the tensioning block (322).

5. The multi-dimensional continuously deformable wing structure according to claim 1, characterized in that: The flexible trailing edge (6) comprises a flexible base plate (61), a flexible inner rotation plate (62), and a flexible outer rotation plate (63) which are hinged in sequence, the flexible base plate (61) being hinged to the inner wing section (3), and the flexible inner rotation plate (62) and the flexible outer rotation plate (63) being driven by a dual-axis steering gear (64).

6. The multi-dimensional continuously deformable wing structure according to claim 5, characterized in that: The dual-axis servos (64) are provided with two groups; one group is fixed on the flexible substrate (61), and its output shaft is connected to the servo rocker (65), and the end of the servo rocker (65) is connected to the rigid shaft (66) through a notch, and the rigid shaft (66) is fixedly connected to the rotating shaft of the flexible inner rotating plate (62) to drive the flexible inner rotating plate (62); the other group is fixed on the flexible inner rotating plate (62), and its output shaft is transmission-connected to the flexible outer rotating plate (63) to drive the flexible outer rotating plate (63).

7. The multi-dimensional continuously deformable wing structure according to claim 5, characterized in that: The flexible trailing edge (6) further comprises an elastic skin, and porous flexible material is filled between the flexible substrate (61), the flexible inner rotation plate (62), the flexible outer rotation plate (63) and the elastic skin.

8. The multi-dimensional continuously deformable wing structure according to claim 1, characterized in that: An extension arm is added to the rocker arm (5) of the swept actuating mechanism, and the extension arm is hinged to the inner wing section (3) of the other wing system, so that a single push rod motor (4) can synchronously drive the two wing systems to change the swept position.

9. The multi-dimensional continuously deformable wing structure according to claim 1, characterized in that: The inner wing section skeleton (36) includes a rear short wing rib (368) and a rear long wing rib (367), and the rear short wing rib (368) and the rear long wing rib (367) are provided with a notch for accommodating the outer wing section (7), and the size of the notch is larger than the cross section of the outer wing section (7).

10. The multi-dimensional continuously deformable wing structure according to claim 9, characterized in that: The penultimate rear short wing rib (368) and the rear long wing rib (367) at the end of the inner wing section skeleton (36) are provided with a sealing device (37), and the sealing device (37) is made of an elastic material.

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