A concealed variable geometry wing mechanism with controllable rotation

Abstract

The application discloses a controllable rotation built-in variable wing mechanism, which comprises a fixed wing, a rotating wing, a driving motor and a transmission device, the rotating wing is rotationally connected with the fixed wing, the transmission device is arranged in the fixed wing, one end of the transmission device is connected with the driving motor, the other end of the transmission device is connected with the rotating wing, the driving motor is connected with the rotating wing through the transmission device, the fixed wing and the driving motor are installed on an aircraft body, and the driving motor drives the rotating wing to rotate through the transmission device. The controllable rotation built-in variable wing mechanism can effectively improve the flight performance of the fixed wing aircraft, adapt to different flight environments, meet the task requirements of high-speed, low-speed and short-distance take-off and landing, and realize the high-speed range and full-time period maneuvering flight of the aircraft.

Description

Technical Field

[0001] This invention belongs to the field of mechanical design technology, specifically relating to a controllable rotating built-in variator wing mechanism. Background Technology

[0002] The wing is a key component of an aircraft and a crucial factor affecting aerodynamic performance. Traditional fixed-shape wings can meet the needs of conventional flight missions and limited flight conditions, but they are insufficient to meet the future demands of large airspace and high-speed flight. Therefore, morphing wing technology has received widespread attention and importance in order to improve aircraft flight performance. Currently, many morphing wing structures have emerged. Examples include morphing wing structures with variable airfoil camber, thickness, span, and torsion; morphing skin technology; variable leading-edge flaps; variable sweep wings; and folding wings. In 1920, BUBERT et al. proposed a variable airfoil camber wing structure. Morphing wing technology involves significant modifications to the wing structure and is highly challenging to design.

[0003] Currently, fixed-wing aircraft are the most numerous, technologically mature, and widely used type of aircraft. However, with the increasing complexity of flight missions and the ever-changing flight environment, fixed-wing aircraft are required to have a wider speed range and higher flight performance. Therefore, vari-propelled aircraft have attracted considerable attention. Summary of the Invention

[0004] The purpose of this invention is to solve the above-mentioned problems and provide a built-in variator wing mechanism that can effectively improve the flight performance of fixed-wing aircraft to adapt to different flight environments, meet the mission requirements of high-speed, low-speed, and short-distance take-off and landing, and thus realize the controllable rotation of the aircraft's high-speed range and all-time maneuvering flight.

[0005] To solve the above-mentioned technical problems, the technical solution of the present invention is: a controllable rotating built-in variator wing mechanism, including a fixed wing, a rotating wing, a drive motor and a transmission device, wherein the rotating wing is rotatably connected to the fixed wing, the transmission device is inserted through the fixed wing, one end of the transmission device is connected to the drive motor, the other end of the transmission device is connected to the rotating wing, the drive motor is connected to the rotating wing through the transmission device, the fixed wing and the drive motor are mounted on the fuselage, and the drive motor drives the rotating wing to rotate through the transmission device.

[0006] Preferably, the fixed wing includes a fixed wing skin, and the fixed wing skin is provided with fan-shaped ribs, supporting longitudinal ribs and supporting transverse ribs. The supporting longitudinal ribs and supporting transverse ribs are cross-fixed and connected. The fan-shaped ribs are located between adjacent supporting longitudinal ribs. A drive shaft fixing beam passes through the supporting longitudinal ribs, and the transmission device passes through the drive shaft fixing beam.

[0007] Preferably, the drive shaft fixing beam includes a fixing beam body, and a first worm support seat, a second worm support seat, a third worm support seat, and a worm wheel support frame arranged in parallel on the fixing beam body, with the worm wheel support frame located between the first worm support seat and the second worm support seat.

[0008] Preferably, the worm gear support frame includes a worm gear support frame ring and a worm gear support frame body fixedly connected as one piece. The worm gear support frame ring has a ring-shaped structure and a worm gear support frame ring through hole. The worm gear support frame body has a bent plate-shaped structure. The end of the worm gear support frame body is fixedly connected to the fixed beam as one piece. Reinforcing ribs are provided between adjacent worm gear support frames.

[0009] Preferably, the fan-shaped rib is an arc-shaped plate structure, the projection of the fan-shaped rib is a fan-shaped structure, the top of the fan-shaped rib is sleeved on the fixed beam body, the bottom of the fan-shaped rib is fixedly connected to the supporting longitudinal rib and the supporting transverse rib, and the upper end of the fan-shaped rib is provided with a fan-shaped rib through hole.

[0010] Preferably, the cross-section of the supporting longitudinal rib is a "teardrop" shape.

[0011] Preferably, the rotor includes a rotor skin, within which are disposed a rotor front beam, rotor crossbeam, rotor longitudinal beam, rotor side beam, rotor side beam, and worm gear. The rotor crossbeam and rotor longitudinal beam are arranged intersectingly. The rotor front beam passes through the top of the rotor longitudinal beam, the rotor side beam passes through the bottom of the rotor longitudinal beam, and the rotor side beam passes through the end of the rotor crossbeam. The ends of the rotor front beam and the ends of the rotor side beam are connected to the worm gear. The worm gear has a through hole in the middle, and a spline groove is provided on the inner surface of the worm gear. A worm gear connecting shaft is provided inside the worm gear. The end of the worm gear connecting shaft is located inside the worm gear support frame ring. The worm gear connecting shaft is provided with a spline, and the spline and spline groove cooperate to make the worm gear and the worm gear connecting shaft rotate synchronously.

[0012] Preferably, the transmission device includes a transmission bevel gear and a transmission worm. The transmission bevel gear is sleeved on the end of the transmission worm, and the other end of the transmission worm is engaged with a worm wheel. The transmission worm passes through a first worm support seat, a second worm support seat, a third worm support seat, and a fan-shaped rib through hole.

[0013] The beneficial effects of this invention are:

[0014] 1. The controllable rotation of the built-in variator wing mechanism provided by the present invention can effectively improve the flight performance of fixed-wing aircraft to adapt to different flight environments and meet the mission requirements of high speed, low speed and short take-off and landing, thereby realizing the high speed range and all-time maneuvering flight of the aircraft.

[0015] 2. The rotor of this invention is installed at the end of the fixed wing and can rotate around a fixed axis under the control of a drive motor. The rotor achieves controllable movement and reliable self-locking through a worm gear. In high-speed flight, the rotor is rotated inward towards the fixed wing to retract and reduce flight drag. In low-speed flight, the rotor is rotated outward towards the fixed wing to deploy, increasing the wing area and improving lift.

[0016] 3. During the inward and outward expansion of the rotating wing of the present invention, the overall wing area changes continuously, and therefore its aerodynamic characteristics also change continuously. Attached Figure Description

[0017] Figure 1 This is a schematic diagram of the structure of a controllable rotating built-in variator wing mechanism according to the present invention;

[0018] Figure 2 This is a schematic diagram of the fixed wing structure of the present invention;

[0019] Figure 3 This is a schematic diagram of the internal structure of the fixed wing of the present invention;

[0020] Figure 4 This is a schematic diagram of the side structure of the fixed wing of the present invention;

[0021] Figure 5 This is a schematic diagram of the rotating wing structure of the present invention;

[0022] Figure 6 This is a schematic diagram of the internal structure of the rotating wing of the present invention;

[0023] Figure 7 This is a schematic diagram of the transmission device structure of the present invention;

[0024] Figure 8 This is a schematic diagram of the worm gear connecting shaft structure of the present invention.

[0025] Explanation of reference numerals in the attached drawings: 1. Fixed wing; 2. Rotary wing; 3. Drive motor; 4. Transmission device; 10. Fixed wing skin; 11. Fan-shaped rib; 12. Supporting longitudinal rib; 13. Supporting transverse rib; 14. Drive shaft fixed beam; 15. Straight rib; 20. Rotary wing skin; 21. Rotary wing front beam; 22. Rotary wing crossbeam; 23. Rotary wing longitudinal beam; 24. Rotary wing side beam; 25. Rotary wing side beam; 26. Worm gear; 41. Drive bevel gear; 42. Drive worm; 140. Fixed beam body; 141. First worm support seat; 142. Second worm support seat; 143. Third worm support seat; 144. Worm gear support frame; 261. Worm gear connecting shaft; 1441. Worm gear support frame ring; 1442. Worm gear support frame body. Detailed Implementation

[0026] The present invention will be further described below with reference to the accompanying drawings and specific embodiments:

[0027] like Figures 1 to 8 As shown, the present invention provides a controllable rotating built-in variator wing mechanism, including a fixed wing 1, a rotating wing 2, a drive motor 3, and a transmission device 4. The rotating wing 2 is rotatably connected to the fixed wing 1. The transmission device 4 passes through the fixed wing 1. One end of the transmission device 4 is connected to the drive motor 3, and the other end of the transmission device 4 is connected to the rotating wing 2. The drive motor 3 is connected to the rotating wing 2 through the transmission device 4. The fixed wing 1 and the drive motor 3 are mounted on the fuselage. The drive motor 3 drives the rotating wing 2 to rotate through the transmission device 4.

[0028] In this embodiment, both the fixed wing 1 and the drive motor 3 are fixedly connected to the existing aircraft fuselage. The fixed wing 1, the rotating wing 2, and the transmission device 4 are arranged in pairs symmetrically at both ends of the drive motor 3. During operation, the drive motor 3 drives the rotating wing 2 to rotate via the transmission device 4. During movement, the rotating wing 2 can retract from the end of the fixed wing 1 into the interior of the fixed wing 1. In actual use, depending on the flight mission, the rotating wing 2 can retract into the fixed wing 1. The drive motor 3 drives the rotating wing 2 to rotate along a fixed axis via the transmission device 4, thereby achieving the retraction or extension of the two movable wing surfaces.

[0029] The fixed wing 1 includes a fixed wing skin 10. The fixed wing skin 10 is provided with a fan-shaped rib 11, a supporting longitudinal rib 12 and a supporting transverse rib 13. The supporting longitudinal rib 12 and the supporting transverse rib 13 are cross-fixed. The fan-shaped rib 11 is located between adjacent supporting longitudinal ribs 12. A drive shaft fixing beam 14 passes through the supporting longitudinal rib 12. The transmission device 4 passes through the drive shaft fixing beam 14.

[0030] The cross-section of the supporting longitudinal rib 12 is a "teardrop" structure. The supporting longitudinal rib 12 has a hollow ring structure, and multiple supporting longitudinal ribs 12 are arranged in parallel. When the rotating wing 2 moves, it can be retracted into the supporting longitudinal rib 12.

[0031] In this embodiment, to enhance structural strength and accommodate the rotating wing 2, the number of fan-shaped ribs 11 is two and arranged in parallel, with straight ribs 15 provided between adjacent fan-shaped ribs 11. The straight ribs 15 are rectangular plate-like structures with rounded tops. The supporting transverse ribs 13 and supporting longitudinal ribs 12 are cross-fixed and connected to form the basic support for the fixed wing skin 10.

[0032] The drive shaft fixing beam 14 includes a fixing beam body 140, on which a first worm support seat 141, a second worm support seat 142, a third worm support seat 143 and a worm wheel support frame 144 are arranged in parallel. The worm wheel support frame 144 is located between the first worm support seat 141 and the second worm support seat 142.

[0033] The worm gear support frame 144 includes a worm gear support frame ring 1441 and a worm gear support frame body 1442 that are fixedly connected together. The worm gear support frame ring 1441 has a ring-shaped structure and a worm gear support frame ring through hole. The worm gear support frame body 1442 has a bent plate-shaped structure. The end of the worm gear support frame body 1442 is fixedly connected to the fixed beam 140 as an integral structure. Reinforcing ribs are provided between adjacent worm gear support frames 144.

[0034] In this embodiment, there are two worm gear support frames 144, which are symmetrically and parallelly distributed on the fixed beam body 140.

[0035] The fan-shaped rib 11 is an arc-shaped plate structure. The projection of the fan-shaped rib 11 is a fan-shaped structure. The top of the fan-shaped rib 11 is fitted onto the fixed beam body 140. The bottom of the fan-shaped rib 11 is fixedly connected to the supporting longitudinal rib 12 and the supporting transverse rib 13. The upper end of the fan-shaped rib 11 is provided with a fan-shaped rib through hole.

[0036] The slewing 2 includes a slewing skin 20, within which are a slewing front beam 21, a slewing crossbeam 22, a slewing longitudinal beam 23, a slewing side beam 24, a slewing side beam 25, and a worm gear 26. The slewing crossbeam 22 and the slewing longitudinal beam 23 are arranged intersectingly. The slewing front beam 21 passes through the top of the slewing longitudinal beam 23, the slewing side beam 24 passes through the bottom of the slewing longitudinal beam 23, and the slewing side beam 25 passes through the end of the slewing crossbeam 22. The ends of the front beam 21 and the side beam 25 of the swivel are connected to the worm gear 26. The worm gear 26 has a through hole in the middle and a spline groove on its inner surface. The worm gear 26 has a worm gear connecting shaft 261 inside it. The end of the worm gear connecting shaft 261 is located inside the worm gear support ring 1441. The worm gear connecting shaft 261 has a spline. The spline and the spline groove cooperate to make the worm gear 26 and the worm gear connecting shaft 261 rotate synchronously.

[0037] The worm gear support frame 144 is connected to the worm gear 26 via the worm gear connecting shaft 261. The worm gear support frame ring 1441 is equipped with a thrust bearing, and the two ends of the worm gear connecting shaft 261 are respectively inserted into the inner ring of the thrust bearing.

[0038] In this embodiment, there are three longitudinal beams 23 of the rotating wing, arranged in parallel, and the longitudinal beams 23 are plate-like structures with an elliptical cross-section. There are three transverse beams 22 of the rotating wing, arranged in parallel, and the longitudinal beams 22 are plate-like structures with a trapezoidal cross-section.

[0039] The wing crossbeam 22 is cross-fixed with the wing longitudinal beam 23. The wing front beam 21 and the wing side beam 24 are cross-fixed with the wing longitudinal beam 23 respectively. The wing side beam 25 is cross-fixed with the wing crossbeam. Since the worm wheel 26 does not need to rotate a full circle, half-circumference worm wheel teeth are opened along the periphery of the worm wheel 26. The worm wheel teeth mesh with the worm to form a worm wheel and worm gear transmission structure.

[0040] The transmission device 4 includes a transmission bevel gear 41 and a transmission worm 42. The transmission bevel gear 41 is sleeved on the end of the transmission worm 42, and the other end of the transmission worm 42 is engaged with the worm wheel 26. The transmission worm 42 passes through the first worm support seat 141, the second worm support seat 142, the third worm support seat 143 and the fan-shaped rib through hole.

[0041] Sliding bearings are installed on the first worm support 141, the second worm support 142, and the third worm support 143. The three sliding bearings are coaxial, and the transmission worm 42 passes through the inner ring of the sliding bearing.

[0042] A drive motor bevel gear is mounted on the shaft end of the drive motor 3, and the drive motor bevel gear meshes with the transmission bevel gear 41. When the drive motor 3 is working, it drives the transmission worm 42 to rotate through the transmission bevel gear 41, which in turn drives the worm wheel 26 to rotate.

[0043] When the state of the rotor 2 needs to be changed, the drive motor 3 operates, driving two symmetrically arranged transmission worm gears 42 to rotate via symmetrically arranged bevel gears. After passing through the transmission worm gears 42, the worm wheel 26 rotates. The worm wheel 26 then drives the rotor 2 to achieve fixed-axis rotation.

[0044] This invention patent proposes a controllable rotating, concealed variator wing mechanism that improves the flight performance of fixed-wing aircraft. The variator 2 is mounted at the end of the fixed wing 1 and can rotate around a fixed axis under the control of a drive motor 3. The variator 2 achieves controllable movement and reliable self-locking through a worm gear. In high-speed flight, the variator 2 rotates inward towards the fixed wing 1, reducing drag. In low-speed flight, the variator 2 rotates outward towards the fixed wing 1, increasing wing area and lift. During the inward and outward rotation of the variator 2, the overall wing area changes continuously, thus its aerodynamic characteristics also change continuously.

[0045] The controllable rotation of the built-in variator wing mechanism proposed in this invention patent can effectively improve the flight performance of fixed-wing aircraft to adapt to different flight environments and meet the mission requirements of high-speed, low-speed, and short-distance takeoff and landing, thereby realizing the aircraft's high-speed-range and all-time maneuvering flight.

[0046] Those skilled in the art will recognize that the embodiments described herein are intended to help the reader understand the principles of the invention, and should be understood that the scope of protection of the invention is not limited to such specific statements and embodiments. Those skilled in the art can make various other specific modifications and combinations based on the technical teachings disclosed in this invention without departing from the spirit of the invention, and these modifications and combinations are still within the scope of protection of this invention.

Claims

1. A controllable rotation, inboard variable geometry wing mechanism, characterised in that: It includes a fixed wing (1), a rotating wing (2), a drive motor (3) and a transmission device (4). The rotating wing (2) is rotatably connected to the fixed wing (1). The transmission device (4) passes through the fixed wing (1). One end of the transmission device (4) is connected to the drive motor (3), and the other end of the transmission device (4) is connected to the rotating wing (2). The drive motor (3) is connected to the rotating wing (2) through the transmission device (4). The fixed wing (1) and the drive motor (3) are mounted on the fuselage. The drive motor (3) drives the rotating wing (2) to rotate through the transmission device (4). The fixed wing (1) includes a fixed wing skin (10), and the fixed wing skin (10) is provided with a fan-shaped rib (11), a supporting longitudinal rib (12) and a supporting transverse rib (13). The supporting longitudinal rib (12) and the supporting transverse rib (13) are cross-fixed. The fan-shaped rib (11) is located between adjacent supporting longitudinal ribs (12). A drive shaft fixing beam (14) is passed through the supporting longitudinal rib (12), and the transmission device (4) is passed through the drive shaft fixing beam (14). The cross section of the supporting longitudinal rib (12) is a "teardrop" structure; the supporting longitudinal rib (12) is a hollow ring structure, and multiple supporting longitudinal ribs (12) are arranged in parallel. When the rotating wing (2) moves, it can be retracted into the supporting longitudinal rib (12). The drive shaft fixing beam (14) includes a fixing beam body (140), and a first worm support seat (141), a second worm support seat (142), a third worm support seat (143) and a worm wheel support frame (144) arranged in parallel on the fixing beam body (140). The worm wheel support frame (144) is located between the first worm support seat (141) and the second worm support seat (142). The worm gear support frame (144) includes a worm gear support frame ring (1441) and a worm gear support frame body (1442) that are fixed together. The worm gear support frame ring (1441) has a ring structure and a worm gear support frame ring through hole. The worm gear support frame body (1442) has a bent plate structure. The end of the worm gear support frame body (1442) is fixed together with the main body of the fixed beam (140). Reinforcing ribs are provided between adjacent worm gear support frames (144).

2. A concealed variable geometry wing mechanism with controllable rotation according to claim 1, characterized in that: The fan-shaped rib (11) is an arc-shaped plate structure. The projection of the fan-shaped rib (11) is a fan-shaped structure. The top of the fan-shaped rib (11) is sleeved on the fixed beam body (140). The bottom of the fan-shaped rib (11) is fixedly connected to the supporting longitudinal rib (12) and the supporting transverse rib (13). The upper end of the fan-shaped rib (11) is provided with a fan-shaped rib through hole.

3. A concealed variable geometry wing mechanism with controllable rotation according to claim 2, characterized in that: The rotor (2) includes a rotor skin (20), which contains a rotor front beam (21), a rotor crossbeam (22), a rotor longitudinal beam (23), a rotor side beam (24), a rotor side beam (25), and a worm gear (26). The rotor crossbeam (22) and the rotor longitudinal beam (23) are arranged intersectingly. The rotor front beam (21) passes through the top of the rotor longitudinal beam (23), the rotor side beam (24) passes through the bottom of the rotor longitudinal beam (23), and the rotor side beam (25) passes through the rotor crossbeam (26). 2) The ends of the front beam (21) and the side beam (25) of the wing are connected to the worm wheel (26). The worm wheel (26) has a through hole in the middle and a spline groove on the inner surface of the worm wheel (26). The worm wheel (26) has a worm wheel connecting shaft (261) inside. The end of the worm wheel connecting shaft (261) is located inside the worm wheel support frame ring (1441). The worm wheel connecting shaft (261) has a spline. The spline and the spline groove cooperate to make the worm wheel (26) and the worm wheel connecting shaft (261) rotate synchronously.

4. A concealed variable geometry wing mechanism with controllable rotation according to claim 3, characterized in that: The transmission device (4) includes a transmission bevel gear (41) and a transmission worm (42). The transmission bevel gear (41) is sleeved on the end of the transmission worm (42). The other end of the transmission worm (42) is engaged with the worm wheel (26). The transmission worm (42) passes through the first worm support seat (141), the second worm support seat (142), the third worm support seat (143), and the fan-shaped rib through hole.

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