A wing structure capable of multidimensional continuous transformation

Abstract

This invention belongs to the field of aircraft technology, specifically disclosing a multi-dimensional continuously variable wing structure, including a fixed plate, an inner wing section, an outer wing section, a sweep actuation mechanism, and a telescopic actuation mechanism. The inner wing section is driven by the sweep actuation mechanism to rotate around the wing root in the spanwise plane to change the wing sweep angle. The outer wing section is slidably connected to the inner wing section and is driven by the telescopic actuation mechanism to extend or retract along the spanwise direction to change the wing span. The leading and trailing edges of the rear side of the inner wing section are respectively connected to a flexible trailing edge and a rigid trailing edge. The flexible trailing edge is used to change the trailing edge camber; the rigid trailing edge is used to change the trailing edge deflection angle. The sweep actuation mechanism includes a turntable, a push rod motor, and a rocker arm. The push rod motor drives the rocker arm to rotate the inner wing section around the turntable to achieve variable sweep. This invention can achieve multi-dimensional wing variability through a simple combination of mechanisms, improving the aerodynamic performance of the aircraft and enabling the aircraft to adapt to different flight conditions and meet various flight mission requirements.

Description

Technical Field

[0001] This invention relates to the field of aircraft technology, and more particularly to a wing structure capable of multidimensional continuous transformation. Background Technology

[0002] In traditional aircraft design, wings employ a fixed geometry. This design has significant limitations: because it cannot adaptively and dynamically adjust key aerodynamic parameters such as airfoil camber, wingspan, and sweep angle during flight, fixed-wing aircraft struggle to simultaneously meet the combined requirements of wide speed range and multi-mission flight.

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

[0004] It is evident that fixed-geometry wing designs inherently lack adaptability when dealing with different flight states and mission profiles, from low to high speeds and from takeoff and landing to cruise. The contradiction between increased shock wave drag during high-speed cruise and insufficient lift reserve during low-speed takeoff and landing is particularly pronounced. Therefore, there is an urgent need to develop an intelligent wing structure with multi-dimensional variability capabilities, capable of autonomously adjusting its key aerodynamic parameters in real time according to flight conditions and mission requirements, and coordinating with control surfaces to fundamentally improve the overall performance of the aircraft in complex flight environments. Summary of the Invention

[0005] The purpose of this invention is to provide a wing structure that can undergo multidimensional continuous transformation, in order to solve the aforementioned technical problems existing in the prior art.

[0006] To achieve the above objectives, the present invention provides the following solution: a wing structure capable of multidimensional continuous variation, comprising: a fixed plate for connecting to the aircraft fuselage; an inner wing section including 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 driven by a sweep actuation mechanism to rotate around the wing root in the spanwise plane to change the wing sweep angle; an outer wing section slidably connected to the inner wing section and driven by a telescopic actuation mechanism to telescopically extend and retract along the spanwise 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 camber; and 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 actuation mechanism includes a turntable, a push rod motor, and a rocker arm, with the push rod motor and the inner wing section respectively hinged at both ends of the rocker arm, and the push rod motor driving the rocker arm to rotate the inner wing section around the turntable to achieve variable sweep. Based on the above structure, this invention integrates a sweep actuation mechanism, a telescopic actuation mechanism, a flexible trailing edge, and a rigid trailing edge to achieve active coordinated adjustment of the wing's sweep angle, span, trailing edge camber, and deflection angle, thus solving the problem that traditional fixed wings cannot simultaneously meet the needs of a wide speed range and multiple missions.

[0007] Furthermore, the telescopic actuation mechanism includes:

[0008] A rotating servo motor and a two-way winch fixed to the inner wing section;

[0009] Guide pulleys and fixed pulleys are fixed to the inner wing section frame;

[0010] A steel wire rope with one end fixed to the outer wing section and the other end wound around a fixed pulley and a bidirectional winch;

[0011] A telescopic tube that is fitted inside the telescopic sleeve of the inner wing section and fixed to the outer wing section.

[0012] Furthermore, the bidirectional winch has upper and lower grooves. One end of the 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 wire rope while the lower groove releases it. When the bidirectional winch rotates clockwise, the upper groove releases the wire rope while the lower groove retracts it, driving the outer wing section to retract into the inner wing section.

[0013] Furthermore, the telescopic actuation mechanism also includes a tensioning device, which includes a fixing block fixed to the inner wing section base plate, a tensioning block connected to the fixing block via a long screw, and a return spring sleeved on the long screw. The rotary servo is fixed to the tensioning block.

[0014] Furthermore, the flexible trailing edge includes a flexible base plate, a flexible inner rotating plate, and a flexible outer rotating plate that are hinged in sequence. The flexible base plate is hinged to the inner wing section, and the flexible inner rotating plate and the flexible outer rotating plate are driven by a dual-axis servo motor.

[0015] Furthermore, the dual-axis servo motor is provided in two sets; one set is fixed on the flexible substrate, and its output shaft is connected to the servo motor rocker arm. The end of the servo motor rocker arm is connected to the rigid shaft through a slot. The rigid shaft is fixed to the rotation shaft of the flexible inner rotating plate to drive the flexible inner rotating plate; the other set is fixed on the flexible inner rotating plate, and its output shaft is connected to the flexible outer rotating plate to drive the flexible outer rotating plate.

[0016] Furthermore, the flexible trailing edge also includes an elastic skin, and a porous flexible material is filled between the flexible substrate, the flexible inner rotating plate, the flexible outer rotating plate, and the elastic skin.

[0017] Furthermore, the rocker arm of the sweep-back actuation mechanism is equipped with an extension arm, which is hinged to the inner wing section of another wing system, so as to realize the synchronous drive of a single push rod motor to change the sweep-back of the two wing systems.

[0018] Furthermore, the inner wing section frame 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 slots for accommodating the outer wing section, the size of which is larger than the cross-section of the outer wing section.

[0019] Furthermore, the penultimate short wing rib and the last long wing rib at the end of the inner wing section frame are equipped with sealing devices made of elastic material.

[0020] As can be seen from the above technical solution, this invention proposes a multi-dimensional continuously variable wing structure that integrates variable sweep, variable span, variable trailing edge camber, and variable trailing edge deflection angle, solving the problem that traditional fixed wings or single-variable wings cannot simultaneously meet the needs of wide speed ranges and multiple missions. Through a simple combination of mechanisms, multi-dimensional wing variability can be achieved, improving the aerodynamic performance of the aircraft and enabling it to adapt to different flight conditions and fulfill various flight mission requirements. Attached Figure Description

[0021] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0022] Figure 1 This is a schematic diagram of the outer wing section of the multidimensionally continuously variable wing structure according to an embodiment of the present invention in the extended state;

[0023] Figure 2 This is a schematic diagram of the inner wing section of the multidimensionally continuously variable wing structure according to an embodiment of the present invention after the skin has been removed.

[0024] Figure 3This is a schematic diagram of the inner wing section skeleton in an embodiment of the present invention;

[0025] Figure 4 This is a schematic diagram of the sweep-back actuation mechanism in an embodiment of the present invention;

[0026] Figure 5 This is a schematic diagram of the attitude transformation of the sweep-back actuator in an embodiment of the present invention;

[0027] Figure 6 This is a schematic diagram of the telescopic actuation mechanism in an embodiment of the present invention;

[0028] Figure 7 for Figure 6 A magnified view of a section at point A in the middle;

[0029] Figure 8 for Figure 6 A magnified view of a section at point B in the middle;

[0030] Figure 9 for Figure 6 A magnified view of a section at point C;

[0031] Figure 10 This is a schematic diagram showing the connection position of the wire rope in the bidirectional winch in an embodiment of the present invention;

[0032] Figure 11 This is a top view of the outer wing section extending beyond the inner wing section at its extreme position in an embodiment of the present invention;

[0033] Figure 12 for Figure 11 A magnified view of a section at point D;

[0034] Figure 13 This is a schematic diagram of the rigid trailing edge structure in an embodiment of the present invention;

[0035] Figure 14 This is a schematic diagram of the flexible trailing edge structure in an embodiment of the present invention;

[0036] Figure 15 for Figure 14 Sectional view of EE;

[0037] Figure 16 This is a schematic diagram showing the connection relationship between the dual-axis servo motor, the servo motor joystick, and the rigid shaft in an embodiment of the present invention.

[0038] Figure 17 This is a diagram showing the change in flexible trailing edge curvature achieved by servo motor rotation in an embodiment of the present invention.

[0039] In the diagram: 1. Fixed plate; 2. Turntable; 21. Turntable base; 22. Rotary wheel; 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. Bidirectional winch; 35. Steel wire rope; 36. Inner wing section frame; 361. Crossbar; 362. Long wing spars; 363. Front short wing spars; 364. Rear short wing spars; 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... 4. Pulley; 5. Push rod motor; 6. Rocker arm; 7. Flexible trailing edge; 8. Flexible base plate; 9. Flexible inner rotating plate; 10. Flexible outer rotating plate; 11. Dual-axis servo; 12. First dual-axis servo; 13. Second dual-axis servo; 14. Third dual-axis servo; 15. Fourth dual-axis servo; 16. Servo rocker arm; 17. Rigid shaft; 18. Outer wing section; 19. Small wing rib; 10. Small wing spars; 11. Small crossbar; 12. Telescopic tube; 13. Rope fixing block; 14. Small winglet front plate; 15. Rigid trailing edge; 16. Control surface servo; 17. Control surface rib; 18. Control surface reinforcing tube; 19. Control surface spars; 20. Control surface turntable. Detailed Implementation

[0040] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0041] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0042] Reference Figures 1 to 17 As shown, this embodiment provides a multi-dimensional continuously variable wing structure, 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, a sweep-back actuation mechanism for driving the inner wing section 3 to rotate and change sweepback, and a telescopic actuation mechanism for driving the outer wing section 7 to telescop and change span. For ease of description, the end of the inner wing section 3 closest to the fixed plate 1 is defined as the front end, and the end closest to the outer wing section 7 is defined as the rear 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 rear 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.

[0043] like Figure 1 , Figure 2 and Figure 6As shown, in this embodiment, the fixing plate 1 has several through holes for fixed connection with the aircraft. A turntable 2 is connected to the fixing plate 1. The turntable 2 includes a turntable base 21 and a rotating wheel 22. The turntable base 21 is fixedly connected to the fixing plate 1, and the rotating wheel 22 is rotatably connected to the turntable base 21. An inner wing section 3 is mounted on the rotating wheel 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 to the protruding structure. The rocker arm 5 has a large end and a small end, the large end of which is hinged to the protruding structure, and the small end of which 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 through 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 rear end of the inner wing section 3.

[0044] 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 on the fixed plate 1, and one end of the rocker arm 5 is hinged to the output end of the push rod motor 4, while the other end is hinged to a protruding 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 to move, causing the inner wing section base plate 31 to rotate around the turntable base 21. The remaining parts fixed on the inner wing section base plate 31 rotate accordingly, thereby realizing the variable sweep function of the inner wing section 3 as a whole.

[0045] In one specific embodiment, the rocker arm 5 of the sweep actuation mechanism may be equipped with an extension arm, 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 perform sweep angle change actions.

[0046] 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 motor 33, a two-way winch 34, a steel wire rope 35, an inner wing section frame 36, a sealing device 37, a pulley system, and an inner wing section skin. The inner wing section frame 36 includes a crossbar 361, a long wing spars 362, a front short wing spars 363, a rear short wing spars 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 root of the flange is fixedly connected to the front surface of the first front long wing rib 365 at the front end of the inner wing section frame 36. The flange extends from the through groove into the space between the second and third front short wing ribs 366 at the front end of the inner wing section frame 36, and is fixed to the first front long wing rib 365 and the first two front short wing ribs 366. Two telescopic sleeves 369 are fixed to the through holes provided between the front long wing ribs 365 and the front short wing ribs 366, and extend all the way to the front end of the first rear long wing rib 367. The telescopic sleeves 369 are hollow. The pulley system includes several guide pulleys 38 and fixed pulleys 39. The guide pulleys 38 are arranged at certain intervals on each wing rib of the inner wing section frame 36. The fixed pulleys 39 are fixed to the upper end of the penultimate rear short wing rib 368 at the end of the inner wing section frame 36. Sealing devices 37 are installed on the penultimate short wing rib 368 and the long wing rib 367 at the end of the inner wing section frame 36.

[0047] In this embodiment, the telescopic actuation mechanism includes a tensioning device 32, a rotary servo motor 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 at the slot of the inner wing section base plate 31, the rotary servo motor 33 is fixed on the tensioning device 32, and the output end of the servo motor is tightly connected to the bidirectional winch 34; the guide pulley 38 is fixed on the wing rib of the inner wing section frame 36, the fixed pulley 39 is fixed on the end wing rib of the inner wing section frame 36, the telescopic sleeve 369 is connected to the front long wing rib 365 and the front short wing rib 366 of the inner wing section frame 36, a portion of the telescopic tube 74 is fixed to the outer wing section 7, and the other portion is fitted inside the telescopic sleeve 369 and can slide inside the telescopic sleeve 369; the steel wire rope 35 is wound between the bidirectional winch 34 and the fixed pulley 39, and is fixed to the outer wing section 7 by the rope fixing block 75.

[0048] The rotary servo 33 in the telescopic actuation mechanism is a 360-degree continuous rotary servo, which can rotate continuously. The wire rope 35 is always in a taut 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 bidirectional winch 34. The other end of the wire rope 35 passes over the fixed pulley 39 on the rib of the inner wing section frame 36 and then passes through the through hole and is wound around the upper groove of the bidirectional winch 34.

[0049] like Figure 3 and Figure 6 As shown, the outer wing section 7 in this embodiment includes several small wing ribs 71, small wing beams 72, small crossbars 73, telescopic tubes 74, rope fixing blocks 75, small wing front plates 76, and outer wing section skin. The length of the telescopic tube 74 is twice the length of the main structure of the outer wing section 7. Half of the telescopic tube 74 is connected to the small wing ribs 71 through through holes in the small wing ribs 71 to strengthen the structural strength of the outer wing section 7; the outer ring of the other half of the telescopic tube 74 fits 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 wing ribs 368 and rear long wing ribs 367 of the inner wing section frame 36 have 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 ensures a certain airtightness between the inner wing section 3 and the outer wing section 7. On the other hand, it supports and guides the extension and retraction of the outer wing section 7. It also buffers the vibration generated by the outer wing section 7 during flight.

[0050] 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 on the inner wing section base plate 31. The tensioning block 322 is provided with slots and is installed behind the fixed block 321 at intervals. 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 turning the long screw 324, the tensioning block 322 can be driven to move within a small range relative to the fixed block 321. The rotary servo 33 is installed on the tensioning block 322. The bidirectional winch 34 is fixed to the output shaft of the rotary servo 33.

[0051] 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. After being wound clockwise a certain number of times from top to bottom, it is led out, passing through the guide pulley 38 and the fixed pulley 39 in sequence, 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. After being wound counterclockwise a certain number of times from top to bottom, it is led out, passing through the guide pulley 38 and then 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 turned to keep the wire rope 35 in a taut state to ensure the stability of the extension and retraction of the outer wing section 7. The total length of the wire rope 35 wound on the bidirectional winch 34 is greater than the travel distance of the outer wing section 7 on the inner wing section 3. Through this connection method, the wire rope 35 forms a closed loop between the bidirectional winch 34, the fixed pulley 39, and the rope fixing block 75. When the bidirectional winch 34 rotates clockwise under the drive of the rotary servo motor 33, the wire rope 35 is released from the upper layer of the bidirectional winch 34, passes through a circuit, and finally enters the lower layer of the bidirectional winch 34, simultaneously causing the outer wing section 7 to retract into the inner wing section 3. Similarly, when the bidirectional winch 34 rotates counterclockwise, the wire rope 35 causes 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, ensuring that its movement does not interfere with the aircraft body and guaranteeing the reliability of the movement. Figure 6 and Figure 13 As shown, when the outer wing section 7 extends, the wire rope 35 drives the rope fixing block 75 to move towards the fixed pulley 39, thereby causing the outer wing section 7 to extend.

[0052] like Figure 13 As shown, the rigid trailing edge 8 in this embodiment includes a control surface servo 81, a control surface rib 82, a control surface reinforcing tube 83, a control surface spars 84, a control surface turntable 85, and a control surface skin. The control surface rib 82, the control surface reinforcing tube 83, and the control surface spars 84 together form the control surface frame. There are two control surface servos 81, which are respectively installed on the control surface ribs 82 at both ends of the control surface frame. The two control surface turntables 85 are respectively fixed on the output shafts of the two control surface servos 81. The control surface ribs 82 at both ends are provided with through holes to ensure that the relative rotation between the control surface turntables 85 and the output shafts of the control surface servos 81 is not hindered. The two control surface turntables 85 are respectively fixed on the rear long ribs 367 at the end of the inner wing section frame 36. In the initial state of the servo, the control surface skin is flush with the surface of the inner wing section skin. When the control surface servo motor 81 rotates, since the control surface turntable 85 is fixed to the wing rib of the inner wing section frame 36, the control surface servo motor 81 and the control surface frame fixed thereto rotate relative to the control surface turntable 85, that is, relative to the inner wing section 3, thereby realizing the function of changing the control surface deflection angle.

[0053] like Figures 14 to 17As shown, the flexible trailing edge 6 in this embodiment includes a flexible substrate 61, a flexible inner rotating plate 62, a flexible outer rotating plate 63, a dual-axis servo 64, a servo rocker arm 65, a rigid shaft 66, and an elastic skin. The flexible substrate 61 is fixed to the front short spar 363 of the inner wing section frame 36. The flexible inner rotating plate 62 is hinged to the flexible substrate 61. The flexible outer rotating plate 63 is hinged to the flexible inner rotating plate 62. The space between the flexible substrate 61, the flexible inner rotating plate 62, the flexible outer rotating plate 63, and the elastic skin is filled with a porous flexible material such as sponge. Slots are provided on the flexible inner rotating plate 62, the flexible outer rotating plate 63, and the flexible substrate 61 for mounting the dual-axis servo 64. The dual-axis servo 64 has two synchronously rotating output shafts. In this embodiment, two sets of dual-axis servos 64 are provided. The first set is fixed to the flexible substrate 61, including, for example... Figure 14 The first dual-axis servo motor 641 and the second dual-axis servo motor 642 shown have servo joysticks 65 mounted on their output shafts at both ends. The servo joysticks 65 are concentrically aligned 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 end of the servo joystick 65 has a slot that forms a groove connection with the corresponding rigid shaft 66. Similarly, the second set of servos is fixed on the flexible inner rotating plate 62, including... Figure 14 The third dual-axis servo 643 and the fourth dual-axis servo 644 shown are connected by servo rocker arms 65 on the two servos to a rigid shaft 66 fixed at the far end of the rotating shaft of the flexible outer rotating plate 63.

[0054] When the dual-axis servo motor 64 rotates, it drives the servo joystick 65 to rotate. The servo joystick 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 driving 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 have a mechanical limiting effect on the relative rotation angle. Taking the rotation of the flexible inner rotating plate 62 relative to the flexible substrate 61 as an example: the servo motor first drives the flexible inner rotating plate 62 to rotate rigidly; when the rotation limit is reached, the servo motor continues to rotate. Since the flexible inner rotating plate 62 is made of a flexible material that can deform elastically, the rigid shaft 66 generates relative displacement within the slot of the servo joystick 65, and at the same time, it causes the flexible inner rotating plate 62 to undergo elastic bending deformation, realizing a change in curvature. Similarly, the movement of the flexible outer rotating plate 63 relative to the flexible inner rotating plate 62 is also first a rigid rotation and then a flexible curvature change. Both the flexible inner rotating plate 62 and the flexible outer rotating plate 63 are driven by the corresponding dual-axis servo motor 64 to ensure uniform rotation. By combining the control of four dual-axis servos 64, a smooth and stable curvature change of the flexible trailing edge 6 can be achieved.

[0055] Compared with the prior art, the present invention discloses at least the following beneficial effects:

[0056] This invention proposes a multi-dimensional continuously variable wing structure that achieves multi-dimensional wing variability through a simple combination of mechanisms. A pushrod motor 4 drives a rocker arm 5 to change the wing's sweep angle, and the pushrod motor 4's good self-locking property maintains the wing's variable sweep state. A rotary servo motor 33 drives a steel cable 35 to extend and retract the outer wing section 7, reducing the number of parts and weight of the inner wing section 3. The servo motor's good holding torque and the constant tension of the steel cable 35 effectively maintain the extended or retracted state of the outer wing section 7. Furthermore, the flexible trailing edge 6 employs a combination of flexible structure and elastic skin, as well as a combination of rigid and flexible rotation, to achieve smooth changes in trailing edge camber. Both the variable trailing edge camber and variable control surface deflection angle are driven by servos, effectively maintaining the stability of the inner wing section 3's trailing edge camber and deflection angle. The variable sweep, variable span, variable trailing edge camber, and variable trailing edge deflection of the wing are all actively driven, which can actively adjust the shape of the wing according to the actual working conditions, solving the problem that traditional fixed wings cannot meet the needs of wide speed range and multiple missions.

[0057] In the description of this invention, it should be understood that the terms "longitudinal", "lateral", "up", "down", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing this invention, and are not intended to indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this invention.

[0058] The embodiments described above are merely preferred embodiments of the present invention and are not intended to limit the scope of the present invention. Various modifications and improvements made by those skilled in the art to the technical solutions of the present invention without departing from the spirit of the present invention should fall within the protection scope defined by the claims of the present invention.

Claims

1. A wing structure capable of multidimensional continuous transformation, characterized in that, include: Fixing plate (1) is used to connect the aircraft fuselage; The inner wing section (3) includes an inner wing section base plate (31), an inner wing section frame (36), and an inner wing section (3) skin; one end of the inner wing section base plate (31) is hinged to the fixed plate (1), and is driven by a sweep actuation mechanism to rotate around the wing root in the spanwise plane to change the wing sweep angle. The 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 actuation mechanism to change the wing span. The flexible trailing edge (6) is connected to the rear side of the front end of the inner wing section (3) and is used to change the curvature of the trailing edge; The 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 actuation mechanism includes a turntable (2), a push rod motor (4) and a rocker arm (5). The push rod motor (4) and the inner wing section (3) are respectively hinged at both ends of the rocker arm (5). The push rod motor (4) drives the rocker arm (5) to make the inner wing section (3) rotate around the turntable (2) to achieve variable sweepback. The telescopic actuation mechanism includes: a rotary servo motor (33) and a two-way winch (34) fixed to the inner wing section (3), a guide pulley (381) and a fixed pulley (382) fixed to the inner wing section frame (36), and a wire rope (35) with one end fixed to the outer wing section (7) and the other end wrapped around the fixed pulley (382) and the two-way winch (34). The bidirectional winch (34) has two layers of grooves, one end of the 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 wire rope (35) while the lower groove releases the wire rope (35). When the bidirectional winch (34) rotates clockwise, the upper groove releases the wire rope (35) while the lower groove retracts the wire rope (35), driving the outer wing section (7) to retract the inner wing section (3). The telescopic actuation mechanism also includes a tensioning device (32), which includes a fixing block (321) fixed to the inner wing section base plate (31), a tensioning block (322) connected to the fixing block (321) via a long screw (324), and a return spring (323) sleeved on the long screw (324). The rotary servo (33) is fixed on the tensioning block (322).

2. The wing structure capable of multidimensional continuous transformation according to claim 1, characterized in that, The flexible trailing edge (6) includes a flexible base plate (61), a flexible inner rotating plate (62) and a flexible outer rotating plate (63) that are hinged in sequence. The flexible base plate (61) is hinged to the inner wing section (3). The flexible inner rotating plate (62) and the flexible outer rotating plate (63) are driven by a dual-axis servo motor (64).

3. The wing structure capable of multidimensional continuous transformation according to claim 2, characterized in that, The dual-axis servo motor (64) is provided in two sets; one set is fixed on the flexible substrate (61), and its output shaft is connected to the servo motor rocker arm (65). The end of the servo motor rocker arm (65) is connected to the rigid shaft (66) through a slot. The rigid shaft (66) is fixed to the rotating shaft of the flexible inner rotating plate (62) to drive the flexible inner rotating plate (62); the other set is fixed on the flexible inner rotating plate (62), and its output shaft is connected to the flexible outer rotating plate (63) to drive the flexible outer rotating plate (63).

4. The multidimensionally continuously variable wing structure according to claim 2, characterized in that, The flexible trailing edge (6) also includes an elastic skin, and the space between the flexible substrate (61), the flexible inner rotating plate (62) and the flexible outer rotating plate (63) and the elastic skin is filled with a porous flexible material.

5. The wing structure capable of multidimensional continuous transformation according to claim 1, characterized in that, An extension arm is added to the rocker arm (5) of the sweep-back actuation mechanism. The extension arm is hinged to the inner wing section (3) of another wing system, so that a single push rod motor (4) can synchronously drive the two wing systems to change sweep.

6. The wing structure capable of multidimensional continuous transformation according to claim 1, characterized in that, The inner wing section frame (36) includes a rear short wing rib (368) and a rear long wing rib (367). The rear short wing rib (368) and the rear long wing rib (367) are provided with slots to accommodate the outer wing section (7). The size of the slots is larger than the cross section of the outer wing section (7).

7. The wing structure capable of multidimensional continuous variation according to claim 6, characterized in that, Sealing devices (37) are installed on the penultimate short wing rib (368) and the rear long wing rib (367) at the end of the inner wing section frame (36), and the sealing devices (37) are made of elastic material.

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