CN219467983U - Co-rotating folding film wing structure of co-rotating vertical take-off and landing film wing aircraft - Google Patents

Abstract

The utility model relates to a co-rotating vertical take-off and landing film wing aircraft, in particular to a co-rotating folding film wing structure of a co-rotating vertical take-off and landing film wing aircraft, which comprises a wing bracket and wing beams arranged on the wing bracket, wherein each wing beam comprises an outer beam rotationally arranged at two outer sides of the wing bracket, a folding angle adjusting mechanism is arranged in the middle of each outer beam, a plurality of film wing plates are fixedly arranged on each wing beam, and the wing beams and the plurality of film wing plates form a flying wing of the aircraft. The utility model discloses a set up folding angle adjustment mechanism on the wing spar, make the outer crossbeam of aircraft can carry out multistage ground, multi-angle folding to can improve the navigable scope and the flight stability of aircraft by a maximum margin when flying, extend the optimal cruising speed of aircraft when certain altitude into a scope by a point.

Description

Co-rotating folding film wing structure of co-rotating vertical take-off and landing film wing aircraft

Technical Field

The utility model relates to a co-rotating vertical take-off and landing film wing aircraft, in particular to a co-rotating folding film wing structure of a co-rotating vertical take-off and landing film wing aircraft.

Background

The existing aircraft are various in different classification methods and are mainly divided into two types according to take-off and landing modes, wherein the take-off and landing aircraft is a jogging take-off and landing aircraft and a vertical take-off and landing aircraft adopts a fixed wing, the vertical take-off and landing aircraft adopts a propeller wing, the fixed wing aircraft has high requirements on take-off and landing sites, a fixed airport is usually required to take-off and landing, the wings of the fixed wing aircraft are stressed greatly, the wing structure of the fixed wing aircraft is complex, the general rotor wings of the spiral wing aircraft are huge, the noise and the oil consumption are large in the flight process, and the technical difficulty of the vertical take-off and landing of the fixed wing aircraft or the jogging take-off and landing of the propeller wing aircraft is great at present.

In the vertical take-off and landing film wing aircraft disclosed at present, a power wing beam structure with rotatable front and rear ends is adopted, vertical lifting force is provided for the aircraft during parking and take-off, the angle of the power wing beam can be rotated after take-off, forward power is provided for the aircraft, in addition, the aircraft adopts a foldable film wing structure, the interference effect between an aircraft rotor wing and the film wing is mainly reduced before and after take-off and landing, and the resistance effect of the wing in the vertical lifting of the aircraft is reduced. However, such aircraft are not capable of overcoming the problems of flying altitude and flying stability during flight.

Disclosure of Invention

Aiming at the problems, the utility model aims to provide a co-rotating folding film wing structure of a co-rotating vertical take-off and landing film wing aircraft, which is characterized in that a folding angle adjusting mechanism is arranged on a wing beam, so that an outer cross beam of the aircraft can be folded in a multi-section mode and a multi-angle mode, the navigability range and the flight stability of the aircraft can be improved to the greatest extent during flight, the optimal cruising speed of the aircraft at a certain altitude is expanded from one point to one range, and the stable flying height and the stable flying speed of the aircraft are realized.

The technical aim of the utility model is achieved by the following technical scheme that the co-rotating folding membrane wing structure of the co-rotating vertical take-off and landing membrane wing aircraft comprises a wing bracket and a wing cross beam arranged on the wing bracket, wherein the wing cross beam comprises an outer cross beam rotationally arranged on two outer sides of the wing bracket, a folding angle adjusting mechanism is arranged in the middle of the outer cross beam, a plurality of membrane wing plates are fixedly arranged on the wing cross beam, and the wing cross beam and the membrane wing plates form a flying wing of the aircraft.

The inventor finds that if the wing cross beam of the vertical take-off and landing film wing aircraft is divided into an inner cross beam corresponding to the width of the aircraft and an outer cross beam extending from two ends of the inner cross beam to the outer edge of the aircraft, and the outer cross beam rotates relative to the inner cross beam through adjustment of a rotating mechanism, when the aircraft adopting the improved structure cruises and flies, the aircraft can obtain a stable flying speed and height, however, as the cruising speed of the aircraft increases, in order to ensure that the aircraft cruises and flies at a constant height, the outer cross beam needs to fold, and when the outer cross beam is folded to a certain angle, the lifting force provided by the outer cross beam on the horizontal plane is limited, so that the cruising aircraft is difficult to keep a stable height.

In one embodiment, the outer beam comprises at least two sections of film wing beam modules arranged along the film wing span direction, the film wing plates are arranged on the film wing beam modules, and the folding angle adjusting mechanism is arranged between the adjacent film wing beam modules.

In one embodiment, the adjacent membrane wing beam modules are hinged through a first bearing, the folding angle adjusting mechanism comprises a driving device and a rotating connecting rod, one end of the driving device is installed in one of the adjacent membrane wing beam modules, the other end of the driving device is hinged with one end of the rotating connecting rod through a third bearing, and the other end of the rotating connecting rod is hinged with the other adjacent membrane wing beam module through a second bearing.

In one embodiment, the first bearing is located above the second bearing.

In one embodiment, the driving device comprises a rotating motor, a push-pull screw rod and a power screw sleeve, the rotating motor is connected with and drives the power screw sleeve to rotate, the power screw sleeve is rotationally installed in the membrane wing beam module, the power screw sleeve is sleeved on the push-pull screw rod and is in threaded connection with the push-pull screw rod, and one end of the push-pull screw rod is rotationally connected with one end of the rotating connecting rod.

In one embodiment, the folding angle adjusting mechanism further comprises a plurality of reduction gears connected to the output end of the rotating motor, and the reduction gears are meshed with the spiral sleeve.

In one embodiment, the folding angle adjusting mechanism further comprises a matched structural shell, and the power screw sleeve and the plurality of reduction gears are rotatably installed inside the matched structural shell.

In one embodiment, the membrane flap is made of carbon fiber.

In one embodiment, the aircraft further comprises a control box body, wherein the control box body is fixedly arranged inside the aircraft, is connected with the wing cross beam through a control sleeve stay cable and drives the wing cross beam to rotate relative to the wing bracket.

In one embodiment, the wing cross beam further comprises an inner cross beam rotatably arranged on the wing bracket, and the inner cross beam is connected between the outer cross beams at two ends of the wing cross beam.

The utility model has the advantages that:

(1) The outer cross beam of the co-rotating vertical take-off and landing film wing aircraft can be folded in a multi-section mode and a multi-angle mode through arranging the folding angle adjusting mechanism on the wing beam, so that the navigability range and the flight stability of the aircraft are improved to the greatest extent during cruising flight, the optimal cruising speed of the aircraft at a certain altitude is expanded from one point to one range, and the stable flying height and the stable flying speed of the aircraft during flight are realized;

(2) When the aircraft is parked and not used, the outer cross beam can be vertically folded and retracted through the folding angle adjusting mechanism, so that the occupied space is reduced, and the effect of conveniently warehousing and stopping is achieved;

(3) The flight stability of the co-rotating vertical take-off and landing membrane wing aircraft is improved by the cooperative cooperation of the plurality of groups of wing cross beams, and the damage of part of membrane wings caused by extremely bad weather or unexpected factors such as attack by bird groups during cruising and flying is prevented, so that the aircraft loses cruising ability;

(4) The whole membrane wing layer is divided into a plurality of small membrane wing plates and combined with the corresponding membrane wing beam modules, so that the resistance of the outer beam of the co-rotating vertical take-off and landing membrane wing aircraft during folding is reduced, meanwhile, the membrane wing plates at the damaged parts can be replaced in a targeted manner when the membrane wings are damaged, the maintenance cost of the co-rotating vertical take-off and landing membrane wing aircraft is reduced, and the co-rotating vertical take-off and landing membrane wing aircraft is convenient to replace and maintain.

Drawings

FIG. 1 is a front view of a co-rotating vertical takeoff and landing membrane wing aircraft;

FIG. 2 is a top view of a co-rotating vertical takeoff and landing membrane wing aircraft;

FIG. 3 is a left side view of a wing spar of a co-rotating vertical take-off and landing film wing aircraft when folded;

FIG. 4 is a perspective view of a co-rotating folded film web;

FIG. 5 is a partial right side view of the first wing cross member with the folding angle adjustment mechanism removed;

FIG. 6 is a partial right side view of the first wing cross member;

FIG. 7 is an enlarged view of a portion of the first wing cross member at B;

FIG. 8 is a cross-sectional view of 4-4 at B in the first wing cross-beam;

FIG. 9 is a partial cross-sectional view of 1-1 at B in a first wing cross-beam;

FIG. 10 is a partial cross-sectional view of 1-1 at right angles to B in the first wing cross-beam;

FIG. 11 is a cross-sectional view of 2-2 at B in the first wing cross-beam;

FIG. 12 is a partial cross-sectional view of A-A in a first wing cross-beam;

FIG. 13 is a partial top view of a wing cross member and wing co-rotation linkage;

FIG. 14 is a front view of a wing cross member and wing co-rotation linkage;

FIG. 15 is a partial view of the linkage rod;

FIG. 16 is a partial top view of a wing cross member and linkage legs;

FIG. 17 is a front view of a circlip;

FIG. 18 is a perspective view of the control housing;

fig. 19 is a partial cross-sectional view of a first single slot drive sheave.

In the figure: 1. a wing bracket; 2. a wing cross beam; 21. a first wing cross member; 211. a first single-slot drive sheave; 212. a rope locking bolt; 22. a second wing cross member; 23. a third wing cross member; 3. wing corotation linkage mechanism; 31. a linkage rod; 311. a collar; 32. linkage support legs; 321. attachment Liang Zhiban; 322. a protruding shaft; 323. a clasp groove; 33. an elastic clasp; 4. an inner cross beam; 5. an outer cross beam; 6. a folding angle adjusting mechanism; 7. a membrane wing plate; 8. a membrane wing beam module; 81. a first membrane wing beam module; 812. an access panel; 82. a second membrane wing beam module; 9. a first bearing; 10. a second bearing; 11. a third bearing; 12. controlling a sleeve inhaul cable; 13. rotating the connecting rod; 14. a rotating motor; 15. push-pull screw; 16. a power screw sleeve; 17. a reduction gear; 18. a structural shell; 19. and controlling the box body.

Detailed Description

As shown in fig. 1-3, a co-rotating folding film wing structure of a co-rotating vertical take-off and landing film wing aircraft comprises a wing bracket 1 and a wing cross beam 2, wherein three groups of the wing cross beams 2 are respectively a first wing cross beam 21, a second wing cross beam 22 and a third wing cross beam 23, a wing co-rotating linkage mechanism 3 is further arranged among the first wing cross beam 21, the second wing cross beam 22 and the third wing cross beam 23, the wing cross beam 2 comprises an inner cross beam 4 rotatably arranged on the wing bracket 1 and outer cross beams 5 connected to two ends of the inner cross beam 4, a folding angle adjusting mechanism 6 capable of enabling the outer cross beam 5 to carry out at least two-section folding is arranged on the outer cross beam 5, a plurality of film wing plates 7 are fixedly arranged on the wing cross beam 2, and the wing cross beam 2 and the film wing plates 7 form a flying wing of the aircraft. When the aircraft parks to land or take off, the outer cross beam 5 is perpendicular to the inner cross beam 4 by rotating the folding angle adjusting mechanism 6, so that the resistance action of the outer cross beam 5 on the aircraft in the vertical direction is reduced, and the stability of the aircraft in vertical lifting is ensured. When the aircraft is in cruising flight, the outer cross beams 5 can be folded in a multi-section mode, and when part of the outer cross beams 5 are folded, part of the outer cross beams 5 are still in a horizontal state, so that lift force is provided for cruising of the aircraft, the navigable range and the flight stability of the aircraft are improved to a greater extent, the optimal cruising speed of the aircraft at a certain height is expanded into a range from one point, and the energy-saving stable flight of the co-rotating vertical take-off and landing film wing aircraft is realized. In addition, the utility model also provides three groups of wing cross beams 2, and the flight stability of the co-rotating vertical take-off and landing film wing aircraft is improved through the cooperative cooperation of the three groups of wing cross beams 2, so that partial film wings are prevented from being damaged due to severe weather or unexpected factors such as attack by bird groups when the aircraft is cruising and flying, and the aircraft loses cruising ability.

Further, the outer beam 5 includes at least two sections of membrane wing beam modules 8 arranged in the membrane wing span direction, the membrane wing plates 7 are provided on the membrane wing beam modules 8, and the folding angle adjusting mechanism 6 is provided between adjacent membrane wing beam modules 8. The folding angle adjusting mechanism 6 is disposed between the adjacent membrane wing beam modules 8, and is used for adjusting one of the membrane wing beam modules 8, which is relatively far away from the inner beam 4, of the adjacent membrane wing beam modules 8 to rotate around the other membrane wing beam module 8 in the horizontal direction.

Further, the adjacent membrane wing beam modules 8 are hinged through the first bearing 9, the folding angle adjusting mechanism 6 comprises a driving device and a rotating connecting rod 13, one end of the driving device is installed in one of the adjacent membrane wing beam modules 8, the other end of the driving device is hinged with one end of the rotating connecting rod 13 through a third bearing 11, and the other end of the rotating connecting rod 13 is hinged with the other adjacent membrane wing beam module 8 through a second bearing 10. Further, the first bearing 9 is located above the second bearing 10. Through dividing into a plurality of little membrane pterygoid lamina 7 with monoblock membrane winglayer to combine together with corresponding membrane winged beam module 8, reduced the resistance of the outer crossbeam 5 of wing of corotation perpendicular take-off and landing membrane winged aircraft when folding, membrane pterygoid lamina 7 at the damage position can be purposefully replaced when damaging simultaneously, and the membrane pterygoid lamina on whole wing crossbeam 2 need not be changed, reduced the maintenance cost of corotation perpendicular take-off and landing membrane winged aircraft, the change maintenance of being convenient for.

Further, in the present embodiment, the membrane wing beam module 8 is provided with two sections, one of the membrane wing beam modules relatively close to the inner beam 4 is a first membrane wing beam module 81, and one of the membrane wing beam modules 8 relatively far from the inner beam 4 is a second membrane wing beam module 82.

Further, in this embodiment, the driving device includes a rotating motor 14, a push-pull screw rod 15 and a power screw sleeve 16, the rotating motor 14 is fixedly disposed in the first membrane wing beam module 81, the first membrane wing beam module 81 has a cavity, an access cover plate 812 is disposed on the cavity, the rotating motor 14 is connected to and drives the power screw sleeve 16 to rotate, the power screw sleeve 16 is rotationally mounted in the first membrane wing beam module 81, the power screw sleeve 16 is sleeved on the push-pull screw rod 15 and is in threaded connection with the push-pull screw rod 15, and one end of the push-pull screw rod 15 is rotationally connected with one end of the rotating connecting rod 13. The operation principle of the folding angle adjusting mechanism 6 is as follows: the output shaft of the rotating motor 14 drives the power screw sleeve 16 to rotate, and as the power screw sleeve 16 is sleeved on the push-pull screw rod 15 which is slidably arranged in the first film wing beam module 81 and is in threaded connection with the push-pull screw rod 15, the power screw sleeve 16 can achieve the purpose of pushing the push-pull screw rod 15 to move in the first film wing beam module 81, when the push-pull screw rod 15 pushes the rotating connecting rod 13 to move towards the second film wing beam module 82, the rotating connecting rod 13 can push the second film wing beam module 82 to rotate around a rotating hinge point between the second film wing beam module 82 and the first film wing beam module 81 due to the fact that the first film wing beam module 81 and the second film wing beam module 82 are hinged through the first bearing 9, and the second film wing beam module 82 can rotate relative to the first film wing beam module 81.

Further, the folding angle adjusting mechanism 6 further includes a plurality of reduction gears 17 and a plurality of matched structure shells 18 connected to the output end of the rotating motor 14, the reduction gears 17 are meshed with the power screw sleeve 16, the matched structure shells 18 are installed in the first membrane wing beam module 81, and the power screw sleeve 16 and the plurality of reduction gears 17 are rotatably installed inside the matched structure shells 18.

Further, the material of the membrane wing is carbon fiber. The carbon fiber material has excellent tensile property, and the average tensile strength can reach 5000Mpa or more, so the film wing prepared from the carbon fiber material has the tensile strength which is enough to meet the requirement of low-altitude flight, and the film can greatly reduce the weight of the wing. Of course, ultrathin high aluminum alloy plates or other light high tensile film materials can also be adopted.

Further, the inner cross beam 4 and the outer cross beam 5 are made of high-strength aluminum alloy aviation materials, the weight is light, and the structural strength can meet the flight requirement.

Further, a control box 19 is fixedly installed in the co-rotating vertical take-off and landing film wing aircraft, the control box 19 is connected with the wing beam 2 through a control sleeve cable 12, the control box 19 drives the wing beam 2 to rotate relative to the wing bracket 1, in this embodiment, a first single-groove transmission wheel disc 211 is fixedly arranged on the outer edge of the first wing beam 21, the control sleeve cable 12 is fixed on the first single-groove transmission wheel disc 211 through a locking bolt 212, so that the control sleeve cable 12 and the first single-groove transmission wheel disc 211 have no relative displacement, and when the control box 19 pulls the control sleeve cable 12, the control sleeve cable 12 is fixed with the first single-groove transmission wheel disc 211, so that the first single-groove transmission wheel disc 211 is driven to rotate, and the first wing beam 21 is driven to rotate.

Further, the wing co-rotating linkage mechanism 3 comprises two linkage rods 31, wherein the two linkage rods 31 are arranged in parallel, three lantern rings 311 are respectively arranged at corresponding positions of the two linkage rods 31, linkage support legs 32 are connected between the corresponding lantern rings 311 of the two linkage rods 31, and the three linkage support legs 32 are arranged.

Further, the three linkage support legs 32 are respectively clamped on the first wing beam 21, the second wing beam 22 and the third wing beam 23, the linkage support legs 32 comprise an attachment Liang Zhiban 321 and convex shafts 322 arranged at two ends of the attachment Liang Zhiban, lantern rings 311 at corresponding positions on the two linkage rods 31 are sleeved on the convex shafts 322 at two ends of the attachment Liang Zhiban 321, a clamping ring groove 323 is further formed in the convex shafts 322, and an elastic clamping ring 33 is clamped on the clamping ring groove 323. The principle of the wing co-rotation linkage mechanism is as follows: in this embodiment, the first wing beam 21 is a driving beam, the second wing beam 22 and the third wing beam 23 are driven beams, when the first wing beam 21 rotates, the linkage support legs 32 on the first wing beam 21 are driven to rotate, the two ends of the linkage support legs 32 are connected with the linkage rods 31, so that the linkage rods 31 are driven to move mutually, the other linkage support legs 32 on the linkage rods 31 are driven to rotate, and the linkage support legs 32 are clamped with the second wing beam 22 and the third wing beam 23, so that the second wing beam 22 and the third wing beam 23 are driven to synchronously rotate, and synchronous rotation among multiple groups of wing beams 2 is realized.

In summary, the principle of the co-rotating vertical take-off and landing film wing aircraft is as follows:

1. wing function singleization—only to provide lift. The stress working condition of the wing is simple, so that the wing can adopt an ultralight structure of a light framework and a film, and the folding and rotating functions of the film wing can be well realized.

2. The engine is arranged on the power wing spar, and the stress working condition of the power wing spar is simple, so that the power wing spar can easily realize the rotation and folding functions.

3. The power wing spar and the wing are staggered, so that the mutual influence of the engine and the wing when the respective functions are exerted is avoided.

4. Multiple engines are employed to reduce noise and improve safety.

5. Large spans are employed to achieve low-altitude economy and to improve safety.

6. The adoption of the active tail rotor system makes the aircraft easier to operate.

7. The power wing beam and the film wing realize single control and synchronous corotation, so that the engine and the film wing are always in the optimal cooperative state, and the control is simple.

8. The co-rotating vertical take-off and landing membrane wing aircraft should take off and land like a helicopter, climb and cruise like a fixed wing aircraft, slide down like a power glider, and take off and land on the water surface in an emergency.

It will be apparent to those skilled in the art from this disclosure that various other changes and modifications can be made which are within the scope of the utility model as defined in the appended claims.

Claims (10)

1. The utility model provides a corotation folding membrane wing structure of corotation vertical take-off and landing membrane wing aircraft, its characterized in that includes wing support (1) and sets up wing crossbeam (2) on wing support (1), wing crossbeam (2) are including rotating outer crossbeam (5) that set up in wing support (1) both outsides, the middle part of outer crossbeam (5) is equipped with folding angle adjustment mechanism (6), fixed being provided with a plurality of membrane pterygoid lamina (7) on wing crossbeam (2), wing crossbeam (2) with a plurality of membrane pterygoid lamina (7) constitute the flight wing of aircraft.

2. A co-rotating folding membrane wing structure of a co-rotating vertical take-off and landing membrane wing aircraft according to claim 1, characterized in that the outer cross beam (5) comprises at least two sections of membrane wing cross beam modules (8) arranged in a membrane wing span direction, the membrane wing plates (7) are arranged on the membrane wing cross beam modules (8), and the folding angle adjusting mechanism (6) is arranged between adjacent membrane wing cross beam modules (8).

3. A co-rotating folding membrane wing structure of a co-rotating vertical take-off and landing membrane wing aircraft according to claim 2, characterized in that the adjacent membrane wing beam modules (8) are hinged by means of a first bearing (9), the folding angle adjusting mechanism (6) comprises a driving device and a rotating connecting rod (13), one end of the driving device is mounted in one of the adjacent membrane wing beam modules (8), the other end of the driving device is hinged with one end of the rotating connecting rod (13) by means of a third bearing (11), and the other end of the rotating connecting rod (13) is hinged with the other adjacent membrane wing beam module (8) by means of a second bearing (10).

4. A co-rotating folded film wing structure of a co-rotating vertical take-off and landing film wing aircraft according to claim 3, characterized in that the first bearing (9) is located above the second bearing (10).

5. A co-rotating folding membrane wing structure of a co-rotating vertical take-off and landing membrane wing aircraft according to claim 3, characterized in that the driving device comprises a rotating motor (14), a push-pull screw (15) and a power screw sleeve (16), the rotating motor (14) is connected with and drives the power screw sleeve (16) to rotate, the power screw sleeve (16) is rotationally arranged in the membrane wing beam module (8), the power screw sleeve (16) is sleeved on the push-pull screw (15) and is in threaded connection with the push-pull screw (15), and one end of the push-pull screw (15) is rotationally connected with one end of the rotating connecting rod (13).

6. A co-rotating folding membrane wing structure of a co-rotating vertical take-off and landing membrane wing aircraft according to claim 5, characterized in that the folding angle adjusting mechanism (6) further comprises a plurality of reduction gears (17) connected to the output end of the rotating motor (14), said reduction gears (17) being meshed with the power screw bushings (16).

7. A co-rotating folding membrane wing structure of a co-rotating vertical take-off and landing membrane wing aircraft according to claim 6, characterized in that the folding angle adjusting mechanism (6) further comprises a profile structural shell (18), the power screw sleeve (16) and the plurality of reduction gears (17) being rotatably mounted inside the profile structural shell (18).

8. A co-rotating folded film wing structure of a co-rotating vertical take-off and landing film wing aircraft according to claim 1, characterized in that the material of the film wing panel (7) is carbon fiber.

9. The co-rotating folding film wing structure of the co-rotating vertical take-off and landing film wing aircraft according to claim 1, further comprising a control box body (19), wherein the control box body (19) is fixedly arranged inside the aircraft, and the control box body (19) is connected with the wing cross beam (2) through a control sleeve stay rope (12) and drives the wing cross beam (2) to rotate relative to the wing bracket (1).

10. A co-rotating folding membrane wing structure of a co-rotating vertical take-off and landing membrane wing aircraft according to claim 1, characterized in that the wing cross beam (2) further comprises an inner cross beam (4) rotatably arranged on the wing bracket (1), the inner cross beam (4) being connected between outer cross beams (5) at both ends of the wing cross beam (2).