CN218967178U

CN218967178U - Variable front wing vertical take-off and landing high-speed aircraft

Info

Publication number: CN218967178U
Application number: CN202223093843.XU
Authority: CN
Inventors: 刘昱含; 陈诗萌; 田巍; 高岚
Original assignee: Shenyang Yuncheng Navigation Technology Co ltd
Current assignee: Shenyang Kailong Jiuying Technology Co ltd
Priority date: 2022-11-21
Filing date: 2022-11-21
Publication date: 2023-05-05
Anticipated expiration: 2032-11-21

Abstract

The utility model discloses a variable front wing vertical take-off and landing high-speed aircraft, which relates to the field of unmanned aircraft structures and comprises a fuselage, wherein a tail wing is arranged at the tail end of the fuselage, a top rotor wing is arranged at the top side of the fuselage close to the tail wing, wings are arranged on two sides of the fuselage, front rotor wings are horizontally arranged on the front sides of the two wings, a cabin is arranged at the front end of the fuselage, and a rotating hole is formed in the inner wall of the cabin and a rotating shaft is rotatably arranged on the inner wall of the cabin. According to the utility model, the width of the two wings is larger than the thickness of the wings, when the vertical take-off and landing is required, the driving unit drives the straight racks to move along the T-shaped sliding grooves for a distance, under the meshing effect, the gears are rotated and rotated by 90 degrees, so that the rotating shafts and the rotating plates are rotated, the wings finally drive the front rotor wings to rotate by 90 degrees, the wings are in a vertical state, the front rotor wings face upwards, and therefore, the air resistance of the machine body during the vertical take-off and landing is reduced, and the vertical take-off and landing high-speed flight is realized.

Description

Variable front wing vertical take-off and landing high-speed aircraft

Technical Field

The utility model relates to the field of unmanned aircraft structures, in particular to a variable front wing vertical take-off and landing high-speed aircraft.

Background

The unmanned aerial vehicle is a unmanned aerial vehicle which is mainly controlled by radio remote control or self, is widely applied to the fields of aerial photography, rescue, inspection, monitoring, mapping, investigation, video shooting, news reporting, express delivery transportation and the like, the wind resistance of most existing multi-rotor unmanned aerial vehicles is weak, the unmanned aerial vehicle is mainly enabled to move forwards by the aid of thrust generated by a propeller or a turbine engine, the main lifting force is from the relative motion of wings and air, and the unmanned aerial vehicle is economical, but the unmanned aerial vehicle is very high in requirements on the landing field and flight operation.

Among the prior art, the utility model discloses a three rotor unmanned aerial vehicle that takes off and land perpendicularly, through installing the wing respectively in fuselage both sides, and install the rotor in one side of fuselage topside and both sides wing, the rotor of installing on the wing simultaneously is through tilting the mechanism installation, realize that the rotor can rotate 90, realize power device effectively to combine, make unmanned aerial vehicle can realize taking off and land perpendicularly again and can realize steady flat flight, however the wing can produce great resistance when taking off and land perpendicularly, influence the speed of taking off and land perpendicularly, therefore we disclose a variable front wing high-speed aircraft that takes off and land perpendicularly and satisfies people's demand.

Disclosure of Invention

The purpose of the application is to provide a variable front wing vertical take-off and landing high-speed aircraft, so as to solve the problem that the wing provided in the background art can generate larger resistance when taking off and landing vertically, and the vertical take-off and landing speed is influenced.

In order to achieve the above purpose, the present application provides the following technical solutions: the utility model provides a variable front wing high-speed aircraft that takes off and land perpendicularly, includes the fuselage, the tail end of fuselage is installed the fin, the topside of fuselage is close to the fin position is installed the top rotor, the both sides of fuselage all are equipped with the wing, two the front side of wing all installs the front rotor horizontally, the front end of fuselage is equipped with the cabin, the pivot has been seted up on the inner wall of cabin and is rotated and install the axis of rotation, the both ends of axis of rotation all run through the pivot and extend to the outside of fuselage, the rotor plate is all installed at the both ends of axis of rotation, the one end of wing with the rotor plate is connected, cup jointed on the axis of rotation and installed the gear, install T shape spout through the support on the inside wall of cabin, install T shape slider in the sliding motion in the T shape spout, straight rack is installed to the bottom side of T shape slider, straight rack with the gear meshes, drive unit is installed to one side of straight, be located on the fuselage the top side of cabin has seted up the opening, be located on the fuselage the opening position installs the rack.

Preferably, the drive unit comprises a threaded rod, a motor is mounted on the inner side wall of the engine room, the threaded rod is connected with an output shaft of the motor in the same shaft mode, a thread bush is mounted on one side of the straight rack, and the threaded rod is in threaded connection with the thread bush.

Preferably, a rotating shaft sleeve is arranged on the cabin wall of the cabin on the machine body, and the rotating shaft is rotatably arranged in the rotating shaft sleeve.

Preferably, the inner wall of the bottom side of the cabin is an inclined plane, and the inner wall of the bottom side of the cabin is provided with a liquid leakage hole at the lowest position.

Preferably, the position of one end of the wing close to the rear side edge is rotatably connected with the corresponding rotating plate through a hinge, and a fixing unit is arranged at the position of one end of the wing close to the front side edge.

Preferably, the fixing unit comprises a bolt, a fixing seat is installed on one side of the rotating plate, a threaded hole is formed in one side of the fixing seat, a mounting seat is correspondingly installed on one side of the wing, a mounting hole is formed in the mounting seat, and one end of the bolt penetrates through the mounting hole and is in threaded connection with the threaded hole.

Preferably, the outer side walls of the two wings are provided with belts.

In summary, the utility model has the technical effects and advantages that:

1. according to the utility model, the width of the two wings is larger than the thickness of the wings, when the two front rotors are in a horizontal state, the machine body can fly horizontally, when the machine body needs to take off and land vertically, the driving unit drives the straight rack to move along the T-shaped sliding groove for a distance, under the meshing action, the gear rotates and rotates 90 degrees, so that the rotating shaft and the rotating plate rotate, and finally the wings drive the front rotors to rotate 90 degrees, so that the wings are in a standing state, the front rotors face upwards, the air resistance of the machine body in the vertical take off and land is reduced, and the vertical take off and land high-speed flight is realized.

2. According to the utility model, through the arrangement of the hinge, when the wing folding device is not used, the wings at two sides can be folded and folded through the hinge, the occupied space is reduced, and after the wings at two sides are folded through the arrangement of the binding belt, the wings and the fuselage are fixed through the binding belt, so that the wing folding device is convenient to store, and the mounting seat and the fixing seat can be quickly connected or detached through the bolts, so that the wing folding device is quick to assemble and convenient to use.

Drawings

In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings that are required in the embodiments or the description of the prior art will be briefly described below, it being obvious that the drawings in the following description are only some embodiments of the present application, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.

FIG. 1 is a schematic perspective view of the present utility model;

FIG. 2 is a schematic view of a partial cut-away view of a gear area in accordance with the present utility model;

FIG. 3 is a schematic view of a partial cut-away view of a rotating plate area according to the present utility model;

FIG. 4 is a schematic perspective view of the wing of the present utility model in a rotated state;

fig. 5 is a schematic perspective view of a wing in a folded state in the present utility model.

In the figure: 1. a body; 2. a cover plate; 3. a wing; 4. a tail wing; 5. a top rotor; 6. a front rotor; 7. a bolt; 8. a binding belt; 9. a nacelle; 10. a straight rack; 11. t-shaped sliding grooves; 12. a T-shaped slider; 13. a threaded rod; 14. a motor; 15. a gear; 16. a rotating shaft; 17. a thread sleeve; 18. a weeping hole; 19. a swivel sleeve; 20. a rotating plate; 21. a hinge; 22. a fixing seat; 23. and (5) a mounting seat.

Detailed Description

The following description of the embodiments of the present utility model will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present utility model, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the utility model without making any inventive effort, are intended to be within the scope of the utility model.

Examples: referring to fig. 1-5, a variable front wing vertical take-off and landing high-speed aircraft comprises a fuselage 1, wherein a tail wing 4 is installed at the tail end of the fuselage 1, a top rotor 5 is installed at the position, close to the tail wing 4, of the top side of the fuselage 1, wings 3 are arranged on two sides of the fuselage 1, front rotors 6 are horizontally installed on the front sides of the two wings 3, a cabin 9 is arranged at the front end of the fuselage 1, a rotating hole is formed in the inner wall of the cabin 9 and is rotatably provided with a rotating shaft 16, two ends of the rotating shaft 16 penetrate through the rotating hole and extend to the outer side of the fuselage 1, rotating plates 20 are installed at two ends of the rotating shaft 16, one end of the wings 3 is connected with the rotating plates 20, a gear 15 is sleeved on the rotating shaft 16, a T-shaped sliding groove 11 is installed on the inner side wall of the cabin 9 through a support, a T-shaped sliding block 12 is slidably installed in the T-shaped sliding groove 11, a straight rack 10 is installed on the bottom side of the T-shaped sliding block 12, the straight rack 10 is meshed with the gear 15, a driving unit is installed on one side of the straight rack 10, an opening is formed in the top side of the cabin 9, an opening is formed in the fuselage 1, one end, and a cover plate 2 is installed at the opening position on the fuselage 1.

Based on the above mechanism, the width of two wings 3 is greater than the thickness of wing 3, and when two front rotor 6 is the horizontality, fuselage 1 can fly horizontally, when needs take off and land perpendicularly, drive unit drive rack 10 removes one end distance along T shape spout 11, under the meshing effect, make gear 15 rotate and rotate 90 to make axis of rotation 16 and rotor plate 20 rotate, finally make wing 3 drive front rotor 6 rotate 90, make wing 3 be the state of erecting, and make front rotor 6 upwards, thereby reduce the air resistance when fuselage 1 takes off and land perpendicularly, realize taking off and land perpendicularly high-speed flight.

As shown in fig. 2, the driving unit includes a threaded rod 13, a motor 14 is installed on the inner side wall of the nacelle 9, the threaded rod 13 is coaxially connected with an output shaft of the motor 14, a thread bush 17 is installed on one side of the straight rack 10, the threaded rod 13 is in threaded connection with the thread bush 17, the threaded rod 13 is driven to rotate by the motor 14, and in the rotating process, the thread bush 17 moves along the threaded rod 13 to synchronously drive the straight rack 10 to move, so that the driving function is realized.

As shown in fig. 3, a rotating shaft sleeve 19 is installed on the cabin wall of the machine body 1, the rotating shaft 16 is rotatably installed in the rotating shaft sleeve 19, and the rotating shaft sleeve 19 facilitates the rotation of the rotating shaft 16 and improves the rotating smoothness.

As shown in fig. 2, the inner wall of the bottom side of the cabin 9 is an inclined plane, the inner wall of the bottom side of the cabin 9 is provided with a weeping hole 18 at the lowest position, when the rain water enters the cabin 9 through the gap of the cover plate 2 and the like during rainy days, the inclined plane of the bottom side wall can guide the accumulated water to flow to the lowest position and flow out through the weeping hole 18, and a large amount of accumulated water is prevented.

As shown in fig. 3 and 5, the position of one end of the wing 3 near the rear side edge is rotationally connected with the corresponding rotating plate 20 through the hinge 21, the position of one end of the wing 3 near the front side edge is provided with a fixing unit, and when not in use, the wing 3 on two sides can be folded and retracted through the hinge 21, so that the occupied space is reduced, and the storage is facilitated.

As shown in fig. 3, the fixing unit includes a bolt 7, a fixing seat 22 is installed on one side of the rotating plate 20, a threaded hole is formed in one side of the fixing seat 22, a mounting seat 23 is correspondingly installed on one side of the wing 3, a mounting hole is formed in the mounting seat 23, one end of the bolt 7 penetrates through the mounting hole and is matched with the threaded hole in a threaded manner, and the mounting seat 23 and the fixing seat 22 can be connected or detached through the bolt 7, so that quick assembly is realized, and the wing is convenient to use.

As shown in fig. 5, the outer side walls of the two wings 3 are provided with the belts 8, and after the wings 3 on two sides are folded by the arrangement of the belts 8, the wings 3 and the fuselage 1 are fixed by the belts 8, so that the wing is convenient to store.

The working principle of the utility model is as follows:

the width of two wings 3 is greater than the thickness of wing 3, and when two front rotor 6 were the horizontality, fuselage 1 can fly horizontally, when taking off and land perpendicularly is needed, drive unit drive rack 10 removes one end distance along T shape spout 11, under the meshing effect, make gear 15 rotate and rotate 90 to make axis of rotation 16 and rotor plate 20 rotate, finally make wing 3 drive front rotor 6 rotate 90, make wing 3 be the state of erecting, and make front rotor 6 upwards, thereby reduce the air resistance when taking off and land perpendicularly of fuselage 1, realize taking off and land perpendicularly high-speed flight.

Finally, it should be noted that: the foregoing description of the preferred embodiments of the present utility model is not intended to be limiting, but rather, it will be apparent to those skilled in the art that the foregoing description of the preferred embodiments of the present utility model can be modified or equivalents can be substituted for some of the features thereof, and any modification, equivalent substitution, improvement or the like that is within the spirit and principles of the present utility model should be included in the scope of the present utility model.

Claims

1. Variable front wing vertical take-off and landing high speed aircraft, including fuselage (1), its characterized in that: tail fin (4) is installed to the tail end of fuselage (1), top rotor (5) is installed near fin (4) position to the topside of fuselage (1), both sides of fuselage (1) all are equipped with wing (3), and front side of both wings (3) all install front rotor (6) horizontally, the front end of fuselage (1) is equipped with cabin (9), set up on the inner wall of cabin (9) and changeed and install axis of rotation (16), the both ends of axis of rotation (16) all run through the change hole and extend to the outside of fuselage (1), rotating plate (20) are all installed at the both ends of axis of rotation (16), one end of wing (3) with rotating plate (20) are connected, install gear (15) on axis of rotation (16) cup joint, install T shape spout (11) on the inside wall of cabin (9) through the support mounting, install T shape slider (12) in the slip, the bottom of T shape slider (12) is installed and is installed rack (10) is directly on the side, rack (10) is installed in order to drive the side of the rack (10) is equipped with on the top of fuselage (1), and a cover plate (2) is arranged on the machine body (1) at the opening position.

2. A variable front wing vertical take-off and landing high speed aircraft as defined in claim 1, wherein: the driving unit comprises a threaded rod (13), a motor (14) is arranged on the inner side wall of the engine room (9), the threaded rod (13) is connected with an output shaft of the motor (14) in the same shaft mode, a thread bush (17) is arranged on one side of the straight rack (10), and the threaded rod (13) is in threaded connection with the thread bush (17).

3. A variable front wing vertical take-off and landing high speed aircraft as defined in claim 1, wherein: a rotating shaft sleeve (19) is arranged on the bulkhead of the machine body (1) and positioned on the cabin (9), and the rotating shaft (16) is rotatably arranged in the rotating shaft sleeve (19).

4. A variable front wing vertical take-off and landing high speed aircraft as defined in claim 1, wherein: the inner wall of the bottom side of the engine room (9) is an inclined plane, and a liquid leakage hole (18) is formed in the lowest position of the inner wall of the bottom side of the engine room (9).

5. A variable front wing vertical take-off and landing high speed aircraft as defined in claim 1, wherein: one end of the wing (3) is in rotary connection with the corresponding rotary plate (20) through a hinge (21), and a fixing unit is arranged at one end of the wing (3) near the front side edge.

6. A variable front wing vertical take-off and landing high speed aircraft as defined in claim 5, wherein: the fixing unit comprises a bolt (7), a fixing seat (22) is arranged on one side of the rotating plate (20), a threaded hole is formed in one side of the fixing seat (22), a mounting seat (23) is correspondingly arranged on one side of the wing (3), a mounting hole is formed in the mounting seat (23), and one end of the bolt (7) penetrates through the mounting hole and is in threaded connection with the threaded hole.

7. A variable front wing vertical take-off and landing high speed aircraft as defined in claim 1, wherein: the outer side walls of the two wings (3) are provided with belts (8).