Self-adaptive wing structure and aircraft

Abstract

The utility model discloses a self-adaptive wing structure and an aircraft, the self-adaptive wing structure comprises a venturi tube, the venturi tube is provided with an inlet, a throat and an outlet which are communicated in sequence; the valve device is provided with a movable valve body, the inlet and the throat are respectively communicated with the valve device, and the valve body moves under the action of the pressure difference between the inlet and the throat; one end of the transmission structure is connected with the valve body; and the other end of the transmission structure is connected with the other end of the wing body. According to the application of the self-adaptive wing structure, the self-adaptive wing structure suitable for the aircraft is provided, and unfolding and folding of the wing body can be automatically adjusted through the venturi tube matched with the valve device according to the real-time flight speed of the aircraft; the wing bodies are folded and shortened during high-altitude flight, so that the resistance is reduced and the flight efficiency is improved; during low-speed flight, the wing bodies are unfolded and extended, so that the lift force and the pitching control capability are improved; and it is further guaranteed that the aircraft can obtain the optimal aerodynamic performance.

Description

TECHNICAL FIELD

[0001] The utility model relates to the field of aircraft technology, especially to a self-adaptive wing structure and an aircraft. BACKGROUND

[0002] In the prior art, the design of canard wings has a significant impact on the aerodynamic performance of electric vertical take-off and landing (eVTOL) aircraft during flight. The gain effect produced by canard wings at different flight speeds varies, for example, long canard wings can provide greater control moment and lift at low speed flight, while short canard wings help to reduce drag and improve flight efficiency at high speed flight.

[0003] However, the traditional fixed canard wing design often has defects when facing different working condition requirements, that is, it is difficult to simultaneously meet the requirements of lift and pitch control ability at low speed flight stage and the requirement of reducing drag at high speed flight stage. This design limitation makes it difficult to achieve optimal aerodynamic performance of the aircraft at different flight stages, affecting the overall flight efficiency and performance. SUMMARY

[0004] Therefore, in order to solve the above problems, the purpose of the utility model is to provide a self-adaptive wing structure, comprising:

[0005] a Venturi tube having an inlet, a throat and an outlet connected in sequence;

[0006] a valve device having a movable valve body, the inlet and the throat being communicated with the valve device respectively, the valve body being movable under the action of pressure difference between the inlet and the throat;

[0007] a transmission structure, one end of the transmission structure being connected with the valve body;

[0008] a wing body, the other end of the transmission structure being connected with the other end of the transmission structure, the transmission structure driving the wing body to be in an unfolded state or a folded state under the drive of the valve body.

[0009] In another preferred embodiment, the valve device comprises a cylinder, a first pipe and a second pipe, the valve body being movably arranged in the valve body, the valve body dividing the inside of the cylinder into a first cavity and a second cavity, two ends of the first pipe being communicated with the first cavity and the inlet respectively, two ends of the second pipe being communicated with the second cavity and the throat respectively.

[0010] In another preferred embodiment, the valve device further comprises a spring, the spring being arranged in the second cavity, one end of the spring contacting the valve body, the other end of the spring contacting the inner wall of the end of the cylinder connected with the second pipe.

[0011] In another preferred embodiment, at least one guide hole is formed on the cylinder, and one end of the transmission structure is movably arranged through the guide hole.

[0012] In another preferred embodiment, the transmission structure comprises a guide rod, a rotating cylinder and a connecting rod, one end of the guide rod is connected with the valve body, a slide channel is formed on the rotating cylinder, the other end of the guide rod is slidably arranged in the slide channel, the rotating cylinder is rotatably arranged around an axis, one end of the connecting rod is connected with the rotating cylinder, and the other end of the connecting rod is connected with the wing body.

[0013] In another preferred embodiment, the transmission structure comprises a mounting frame, a first bearing and a second bearing, the first bearing is mounted on the upper end of the mounting frame, the second bearing is mounted on the lower end of the mounting frame, the upper end of the rotating cylinder has a first shaft end, the lower end of the rotating cylinder has a second shaft end, the first shaft end is rotatably connected with the first bearing, and the second shaft end is rotatably connected with the second bearing.

[0014] In another preferred embodiment, the slide channel is arranged along the upper end to the lower end of the rotating cylinder, and the upper end of the slide channel is staggered with the lower end of the slide channel in the circumferential direction of the rotating cylinder.

[0015] The utility model discloses a kind of aircrafts, including at least one self-adapting wing structure described in any one of the above.

[0016] In another preferred embodiment, further comprising: a fuselage, an air inlet is provided on the fuselage, the Venturi tube is installed in the air inlet, the fuselage has at least one opening, and the wing body is movably installed at the opening.

[0017] When the wing body is in the unfolded state, the wing body is arranged to extend outward through the opening.

[0018] When the wing body is in the folded state, the wing body is on the inside of the opening.

[0019] In another preferred embodiment, the number of the transmission structure and the wing body is two, both the transmission structures are connected with the same valve body, both the wing bodies are connected with the transmission structures respectively, and both the wing bodies are arranged on both sides of the fuselage.

[0020] The utility model discloses the technical scheme, compared with prior art, has the positive effect that:

[0021] The utility model discloses a kind of adaptive wing structures suitable for aircraft, can be automatically adjusted the unfolding and folding of wing body according to the real-time flight speed of aircraft by venturi cooperation valve device;So when flying at high altitude, wing body is folded and shortened, to reduce drag and improve flight efficiency;When flying at low speed, wing body is unfolded and lengthened, to increase lift and pitch control ability;Further, aircraft can obtain the best aerodynamic performance, and does not need to rely on external energy, its reliability and stability are stronger. BRIEF DESCRIPTION OF DRAWINGS

[0022] Figure 1 It is the first schematic view of a kind of adaptive wing structures of the utility model;

[0023] Figure 2 It is the second schematic view of a kind of adaptive wing structures of the utility model;

[0024] Figure 3 It is the third schematic view of a kind of adaptive wing structures of the utility model;

[0025] Figure 4 It is the overall schematic view of a kind of aircraft of the utility model.

[0026] In the drawings:

[0027] 1, venturi;2, inlet;3, throat;4, outlet;5, valve device;6, valve body;7, transmission structure;8, wing body;9, cylinder body;10, first pipe;11, second pipe;12, first cavity;13, second cavity;14, spring;15, guide rod;16, rotating cylinder;17, connecting rod;18, slide;19, mounting frame;20, first bearing;21, second bearing;22, first shaft end;23, second shaft end;24, fuselage;25, air inlet;26, wing;27, ducted fan;28, bearing seat;29, first support;30, second support. DETAILED DESCRIPTION

[0028] The technical solutions of the utility model will be described clearly and completely in conjunction with the drawings, obviously, the described embodiment is a part of the embodiment of the utility model, not all the embodiment. Based on the embodiment in the utility model, all other embodiments obtained by the person skilled in the art without making creative labor belong to the range of protection of the utility model.

[0029] In the description of the utility model, it is understood that the orientation or position relation indicated by the terms such as ''up'', ''down'', ''left'', ''right'', ''inner'', ''outer'', ''front'', ''back'', ''horizontal direction'', ''vertical direction'' is the orientation or position relation based on the orientation or position relation shown in the drawings, and is only for the convenience of describing the utility model, and does not indicate or imply that the indicated device or element must have a particular orientation, so it can not be understood as a limitation on the utility model.

[0030] It needs to be specially pointed out that ''horizontal'', ''vertical'' in the utility model are all used for explaining approximate position relation, and not strict ''horizontal plane'' or ''vertical plane''.

[0031] As shown in Figures 1 to 3 The adaptive wing structure of a preferred embodiment comprises: a Venturi tube 1, the Venturi tube 1 has inlet 2, throat 3 and outlet 4 communicated in sequence; valve device 5, the valve device 5 has a movable valve body 6, the inlet 2 and the throat 3 are communicated with the valve device 5 respectively, the valve body 6 moves under the action of pressure difference between the inlet 2 and the throat 3; transmission structure 7, one end of the transmission structure 7 is connected with the valve body 6; wing body 8, the other end of the transmission structure 7 is connected with the other end of the transmission structure 7, the transmission structure 7 drives the wing body 8 to be in the unfolded state or the folded state under the drive of the valve body 6.Further, based on the fluid mechanics characteristics of the Venturi tube 1, when in low-speed movement state, the velocity of the incoming airflow is low, the pressure difference formed when flowing through the Venturi tube 1 is small at the inlet 2 and the throat 3, the valve body 6 remains in the lower end position, and the wing body 8 does not activate and is in the unfolded state; in the acceleration movement stage, with the gradual increase of the velocity, the pressure difference generated at the inlet 2 and the throat 3 increases, the valve body 6 moves upward, thereby driving the wing body 8 to shrink inward through the transmission structure 7; in the high-speed cruising state, when the pressure difference reaches the maximum value, the transmission structure 7 drives the wing body 8 to shrink to the inside and be in the folded state, so as to minimize the movement resistance.

[0032] Further, as a preferred embodiment, the valve device 5 comprises: cylinder body 9, first pipe 10 and second pipe 11, the valve body 6 is movably arranged in the valve body 6, the valve body 6 divides the inside of the cylinder body 9 into first cavity 12 and second cavity 13, the two ends of the first pipe 10 are communicated with the first cavity 12 and the inlet 2 respectively, and the two ends of the second pipe 11 are communicated with the second cavity 13 and the throat 3 respectively.Further, through the arrangement of the first pipe 10 and the second pipe 11, the fluid pressure at the inlet 2 and the throat 3 of the Venturi tube 1 is transmitted to the first cavity 12 and the second cavity 13, and then the corresponding pressure difference is formed at the upper and lower ends of the valve body 6.

[0033] Further, as a preferred embodiment, the cylinder 9 is in a cylindrical structure extending along the vertical direction, the upper end and the lower end of the cylinder 9 are provided with connecting ports to be connected with the second pipe 11 and the first pipe 10 respectively, and the moving direction of the valve body 6 is along the vertical direction.

[0034] Further, as a preferred embodiment, the valve device 5 further comprises a spring 14, the spring 14 is arranged in the second cavity 13, one end of the spring 14 contacts the valve body 6, and the other end of the spring 14 contacts the inner wall of the end of the cylinder 9 connected with the second pipe 11. Further, the spring 14 is arranged at the upper end of the valve body 6, so that in the low-speed moving state, the valve body 6 can be kept stationary at the bottom of the cylinder 9 under the elastic force of the spring 14, and after the speed is further increased, the valve body 6 gradually overcomes the elastic force of the spring 14 to compress the spring 14 and moves upward to drive the movement of the transmission structure 7.

[0035] Further, as a preferred embodiment, at least one guide port is provided on the cylinder 9, and one end of the transmission structure 7 is movably arranged through the guide port. Further, the guide port extends along the vertical direction and penetrates the cylinder 9 along the radial direction of the cylinder 9, and one end of the transmission structure 7 is movably arranged along the vertical direction.

[0036] Further, as a preferred embodiment, the guide port is arranged in a closed and isolated manner with respect to the first cavity 12 and the second cavity 13.

[0037] Further, as a preferred embodiment, the outer edges of the upper end and the lower end of the valve body 6 are provided with sealing rings, and the sealing rings are in sealing contact with the inner wall of the cylinder 9.

[0038] Further, as a preferred embodiment, the transmission structure 7 comprises a guide rod 15, a rotating cylinder 16, and a connecting rod 17, one end of the guide rod 15 is connected with the valve body 6, the rotating cylinder 16 is provided with a sliding channel 18, the other end of the guide rod 15 is slidably arranged in the sliding channel 18, the rotating cylinder 16 is rotatably arranged about an axis, one end of the connecting rod 17 is connected with the rotating cylinder 16, and the other end of the connecting rod 17 is connected with the wing body 8. Further, the cooperation of the guide rod 15 and the rotating cylinder 16 converts the linear motion of the guide rod 15 up and down into the rotating motion of the rotating cylinder 16, and the conversion of the motion is realized by the guiding direction of the sliding channel 18, so as to drive the rotation of the connecting rod 17 and further drive the rotation of the wing body 8.

[0039] Further, as a preferred embodiment, the guide rod 15 is in a rod structure extending along the horizontal direction.

[0040] Further, as a preferred embodiment, the rotating cylinder 16 extends along the vertical direction, and the overall outer contour of the rotating cylinder 16 is in a cylindrical structure.

[0041] Further, as a preferred embodiment, the transmission structure 7 comprises a mounting frame 19, a first bearing 20 and a second bearing 21, the first bearing 20 is mounted on the upper end of the mounting frame 19, the second bearing 21 is mounted on the lower end of the mounting frame 19, the upper end of the rotating cylinder 16 has a first shaft end 22, the lower end of the rotating cylinder 16 has a second shaft end 23, the first shaft end 22 is rotatably connected with the first bearing 20, and the second shaft end 23 is rotatably connected with the second bearing 21.

[0042] Further, as a preferred embodiment, the mounting frame 19 comprises a H-shaped frame body and two bearing seats 28, the two bearing seats 28 are respectively arranged on the upper end and the lower end of the H-shaped frame body, and the first bearing 20 and the second bearing 21 are respectively mounted in the two bearing seats 28.

[0043] Further, as a preferred embodiment, the first shaft end 22, the rotating cylinder 16 and the second shaft end 23 are coaxially arranged, the first shaft end 22 protrudes from the upper end of the rotating cylinder 16, the second shaft end 23 protrudes from the lower end of the rotating cylinder 16, and the first shaft end 22 and the second shaft end 23 are both in a cylindrical structure.

[0044] Further, as a preferred embodiment, the slide 18 extends along the upper end to the lower end of the rotating cylinder 16, and the upper end of the slide 18 is staggered with the lower end of the slide 18 in the circumferential direction of the rotating cylinder 16. Further, the above-mentioned staggered refers to that the upper end of the slide 18 is relatively displaced from the lower end on the outer circumferential surface of the rotating cylinder 16 in the circumferential direction, preferably so that the slide is arranged obliquely relative to the surface of the rotating cylinder 16, so that when the other end of the guide rod 15 moves up and down in the inclined slide 18, the rotating cylinder 16 is driven to rotate.

[0045] Further, as a preferred embodiment, the slide 18 can be an opening structure penetrating through the rotating cylinder 16 or a groove structure recessed in the circumferential outer surface of the rotating cylinder 16.

[0046] The above only describes preferred embodiments of the present application, and does not limit the implementation and protection scope of the present application.

[0047] The present application further has the following implementation based on the above:

[0048] As shown in the accompanying drawings, a preferred embodiment of an aircraft is shown, which comprises at least one self-adaptive wing structure according to any one of the above. Figure 4

[0049] In a further embodiment of the present application, it further comprises a fuselage 24, the fuselage 24 is provided with an air inlet 25, the Venturi tube 1 is mounted in the air inlet 25, the fuselage 24 has at least one opening, and the wing body 8 is movably mounted at the opening.

[0050] ​In a further embodiment of the utility model, the air inlet 25 is preferably arranged at the lower surface of the head of the fuselage 24.

[0051] In a further embodiment of the utility model, the air inlet 25 is preferably a ring structure, so that when the aircraft is flying, sufficient air flow will enter from the front end of the ring structure and exit from the rear end of the ring structure.

[0052] In a further embodiment of the utility model, the Venturi tube 1, the valve device 5 and the transmission structure 7 are all arranged at the inner side of the head of the fuselage 24.

[0053] In a further embodiment of the utility model, when the wing body 8 is in the unfolded state, the wing body 8 is arranged to extend outward through the opening. When the wing body 8 is in the folded state, the wing body 8 is on the inner side of the opening. Further, at least most of the structure of the wing body 8 on the inner side of the opening is arranged on the inner side of the opening, so that the part of the wing body 8 on the outer side of the opening is sufficiently small or completely hidden in the opening.

[0054] In a further embodiment of the utility model, the utility model further comprises: a first support 29 and a second support 30, the lower end of the first support 29 is fixed to the bottom surface of the inner wall of the air inlet 25, and the upper end of the first support 29 is fixedly connected with the Venturi tube 1 to form support for the Venturi tube 1; the second support 30 is arranged in the interior of the head of the fuselage 24, the lower end of the second support 30 is fixedly connected with the bottom of the inner wall of the fuselage 24, and the upper end of the second support 30 is fixedly connected with the lower part of the cylinder body 9 to form support for the cylinder body 9.

[0055] In a further embodiment of the utility model, the number of the transmission structure 7 and the wing body 8 is both two, both transmission structures 7 are connected with the same valve body 6, both wing bodies 8 are connected with the two transmission structures 7 respectively, and both wing bodies 8 are arranged on both sides of the fuselage 24.

[0056] In a further embodiment of the utility model, both transmission structures 7 are movably arranged on the left and right sides of the valve body 6.

[0057] In a further embodiment of the utility model, the aircraft is preferably an electric vertical take-off and landing type aircraft, and the aircraft further comprises: a wing 26 and a ducted fan 27, the wing 26 is arranged on the outer side of the fuselage 24, and the ducted fan 27 is arranged on the wing 26.

[0058] In a further embodiment of the utility model, two or four wings 26 can be arranged on the aircraft, and a plurality of ducted fans 27 are arranged on each wing 26 along the length direction.

[0059] In a further embodiment of the utility model, the wing body 8 is a canard wing, the wing body 8 is arranged closer to the head of the fuselage 24 relative to the wing 26, and the size of the wing body 8 is much smaller than the size of the wing 26.

[0060] The above merely describes preferred embodiments of the present application, and is not intended to limit the embodiments and the protection scope of the present application. It should be understood by those skilled in the art that any equivalent substitutions and obvious changes made according to the content of the present application should be included in the protection scope of the present application.

Claims

1. An adaptive wing structure, characterized in that, include: A venturi tube having an inlet, a throat, and an outlet connected in sequence; A valve device having a movable valve body, an inlet and a throat respectively connected to the valve device, the valve body moving under the action of a pressure difference between the inlet and the throat; A transmission structure, one end of which is connected to the valve body; The wing body has one end connected to the other end of the transmission structure, and the transmission structure drives the wing body to be in an unfolded or folded state under the drive of the valve body.

2. The adaptive wing structure according to claim 1, characterized in that, The valve device includes a cylinder, a first pipe, and a second pipe. The valve body is movably disposed within the valve body and divides the interior of the cylinder into a first chamber and a second chamber. The two ends of the first pipe are respectively connected to the first chamber and the inlet, and the two ends of the second pipe are respectively connected to the second chamber and the throat.

3. The adaptive wing structure according to claim 2, characterized in that, The valve device further includes a spring, which is disposed in the second cavity, with one end of the spring contacting the valve body and the other end of the spring contacting the inner wall of the end of the cylinder that is connected to the second pipe.

4. The adaptive wing structure according to claim 2, characterized in that, The cylinder body has at least one guide port, and one end of the transmission structure is movably disposed through the guide port.

5. The adaptive wing structure according to claim 1, characterized in that, The transmission structure includes a guide rod, a rotating cylinder, and a connecting rod. One end of the guide rod is connected to the valve body. A slide rail is provided on the rotating cylinder. The other end of the guide rod is slidably disposed in the slide rail. The rotating cylinder is rotatably disposed around an axis. One end of the connecting rod is connected to the rotating cylinder, and the other end of the connecting rod is connected to the wing body.

6. The adaptive wing structure according to claim 5, characterized in that, The transmission structure includes: a mounting bracket, a first bearing, and a second bearing. The first bearing is mounted on the upper end of the mounting bracket, and the second bearing is mounted on the lower end of the mounting bracket. The upper end of the rotating cylinder has a first shaft end, and the lower end of the rotating cylinder has a second shaft end. The first shaft end is rotatably connected to the first bearing, and the second shaft end is rotatably connected to the second bearing.

7. The adaptive wing structure according to claim 5, characterized in that, The slide rail extends from the upper end to the lower end of the rotating cylinder, and the upper end and the lower end of the slide rail are offset from each other in the circumferential direction of the rotating cylinder.

8. An aircraft, characterized in that, It includes at least one adaptive wing structure as described in any one of claims 1 to 7 above.

9. The aircraft according to claim 8, characterized in that, Also includes: The fuselage has an air intake duct, the venturi tube is installed in the air intake duct, the fuselage has at least one opening, and the wing is movably installed at the opening; When the wing is in the deployed state, the wing extends outward through the opening; When the wing is in the folded state, the wing is inside the opening.

10. The aircraft according to claim 9, characterized in that, The number of transmission structures and wing bodies are both two. Both transmission structures are connected to the same valve body, and the two wing bodies are respectively connected to the two transmission structures. The two wing bodies are respectively located on both sides of the fuselage.

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