CN218839801U

CN218839801U - Vertical take-off and landing fixed wing unmanned aerial vehicle

Info

Publication number: CN218839801U
Application number: CN202320190025.7U
Authority: CN
Inventors: 彭辉; 葛贺宇; 潘震东
Original assignee: Beijing Jimu Zhishang Technology Co ltd
Current assignee: Beijing Jimu Zhishang Technology Co ltd
Priority date: 2023-01-29
Filing date: 2023-01-29
Publication date: 2023-04-11
Anticipated expiration: 2033-01-29

Abstract

The utility model relates to a VTOL fixed wing unmanned aerial vehicle relates to unmanned aerial vehicle's field, its include the fuselage, set up in the aircraft nose of fuselage head, set up in main wing on the fuselage, set up in the main wing is kept away from the outer wing of fuselage one end, set up in rotor horn between main wing and the outer wing, set up in the tail pipe of fuselage afterbody and set up in the fin of tail pipe, detachable connection between main wing and the outer wing, rotor horn is through keeping somewhere type connecting piece and main wing and outer wing detachable connection, tail pipe one end is pegged graft in the fuselage afterbody. According to the method, the outer wing is detached from the shape-preserving connecting piece, and the tail pipe is detached from the tail part of the unmanned plane body, so that the fixed-wing unmanned plane is converted into the rotary-wing unmanned plane; the outer wing is connected with the shape-preserving connecting piece, and the tail pipe is fixed on the tail part of the unmanned aerial vehicle body, so that the rotary wing type unmanned aerial vehicle is changed into a fixed wing type unmanned aerial vehicle, and the practicability of the unmanned aerial vehicle is improved.

Description

Vertical take-off and landing fixed wing unmanned aerial vehicle

Technical Field

The application relates to the field of unmanned aerial vehicles, in particular to a vertical take-off and landing fixed wing unmanned aerial vehicle.

Background

Unmanned aerial vehicle is called unmanned aerial vehicle for short, and is unmanned aerial vehicle operated by radio remote control equipment and self-contained program control device. The machine has no cockpit, but is provided with an automatic pilot, a program control device, an information acquisition device and other equipment.

The unmanned aerial vehicle generally comprises a fixed-wing unmanned aerial vehicle and a rotor unmanned aerial vehicle, wherein the fixed-wing unmanned aerial vehicle has the advantages of high flying speed, long flying distance, large cruising area, high flying height and the like, but has the defects of high operation difficulty, high risk, incapability of obtaining continuous images when flying according to a fixed route, hovering and the like; and rotor unmanned aerial vehicle has flight height and hangs down, mobility is strong, carry out special task ability reinforce, small, disguised good, can hover, violently fly and fly back the advantage such as, but have flight speed slowly, defect such as flying distance is short.

To unmanned aerial vehicle, its structure comprises aircraft nose, fuselage, wing, tail pipe, and unmanned aerial vehicle fuselage among the prior art adopts integrated into one piece's structure preparation to form.

In view of the above-mentioned related art, the inventor thinks that the integrated structure can only be used as a type of unmanned aerial vehicle, and the practicability is not high.

SUMMERY OF THE UTILITY MODEL

In order to improve unmanned aerial vehicle's practicality, this application provides VTOL fixed wing unmanned aerial vehicle.

The application provides VTOL fixed wing unmanned aerial vehicle adopts following technical scheme:

vertical take-off and landing fixed wing unmanned aerial vehicle, including the fuselage, set up in the aircraft nose of fuselage head, still including set up in main wing on the fuselage, set up in the main wing is kept away from the outer wing of fuselage one end, set up in rotor horn between main wing and the outer wing, set up in the tail pipe of fuselage afterbody and set up in the fin of tail pipe, detachable connection between main wing and the outer wing, rotor horn is through the detachable connection of shape-preserving connecting piece with main wing and outer wing, tail pipe one end is pegged graft in the fuselage afterbody.

By adopting the technical scheme, the outer wing is detached from the shape-preserving connecting piece, and the tail pipe is detached from the tail part of the unmanned aerial vehicle body, so that the fixed wing unmanned aerial vehicle is converted into the rotary wing unmanned aerial vehicle; the outer wing is connected with the shape-preserving connecting piece, and the tail pipe is fixed on the tail part of the unmanned aerial vehicle body, so that the rotary wing type unmanned aerial vehicle is changed into a fixed wing type unmanned aerial vehicle, and the practicability of the unmanned aerial vehicle is improved.

Optionally, an inner insertion groove is formed in one end, far away from the body, of the main wing, an inner insertion connector in interference fit with the inner insertion groove is arranged at one end of the shape-preserving connector, an outer insertion groove is formed in one end of the shape-preserving connector, and an outer insertion connector in interference fit with the outer insertion groove is arranged at one end of the outer wing.

By adopting the technical scheme, the detachable fixed connection between the main wing and the shape-preserving connecting piece is realized, and the detachable connection between the side wing and the shape-preserving connecting piece is realized.

Optionally, a mounting groove is formed in the top of the body, a mounting frame is arranged at a position, close to the body, of the main wing, and the mounting frame is connected with the mounting groove through fixing screws.

Through adopting above-mentioned technical scheme for through the detachable fixed connection of set screw and fixation nut between installing frame and the fuselage, the installation and the dismantlement of the main wing of being convenient for.

Optionally, a horizontal tail is arranged at one end of the tail pipe, a rear insertion groove is formed in the end portion of the horizontal tail, and a rear insertion piece in interference fit with the rear insertion groove is arranged on the end portion of the tail wing.

By adopting the technical scheme, the detachable fixed connection between the tail wing and the horizontal tail can be realized, and the tail wing is convenient to install and disassemble.

Optionally, the outer wing comprises a side spar and a hard shell skin arranged outside the side spar.

By adopting the technical scheme, the wing beam serves as a main supporting piece, and the hard shell skin can bear main stress.

Optionally, two sets of middle wing beams are arranged inside the main wing and the mounting frame together, a beam seat is arranged at the bottom of each middle wing beam, and a plurality of seat cushions are arranged on the beam seat in a penetrating mode.

Through adopting above-mentioned technical scheme, the intensity of main wing can be improved in the setting of well wing roof beam, and the setting of seatpad can support the beam seat.

Optionally, a connecting beam is arranged between the two middle spars.

By adopting the technical scheme, the connection stability between the two groups of middle wing beams can be further improved, so that the strength of the main wing is improved.

Optionally, a support frame is arranged at the bottom of the machine body.

Through adopting above-mentioned technical scheme, the support frame can play the effect of supporting unmanned aerial vehicle.

In summary, the present application includes at least one of the following beneficial technical effects:

1. the outer wing is detached from the shape-preserving connecting piece, and the tail pipe is detached from the tail part of the unmanned plane body, so that the fixed wing unmanned plane is changed into a rotor wing unmanned plane; connecting the outer wing with the shape-preserving connecting piece, and fixing the tail pipe at the tail part of the machine body, thereby converting the rotary wing type unmanned aerial vehicle into a fixed wing type unmanned aerial vehicle; on fixed wing unmanned aerial vehicle's basis, be fixed in between main wing and the sideline with the guarantor type connecting piece to can realize the conversion between the unmanned aerial vehicle of three kinds of rotor type unmanned aerial vehicle, fixed wing unmanned aerial vehicle and compound wing unmanned aerial vehicle

2. The side spars act as the primary support members, while the hard shell skin can withstand the primary stresses.

Drawings

Fig. 1 is a schematic diagram of the combined drone status of the present application;

FIG. 2 is a schematic view of the mounting frame and main wing of the present application;

FIG. 3 is a schematic view of a form-retaining connector of the present application;

FIG. 4 is a schematic view of the outer wing of the present application;

fig. 5 is a schematic diagram of the rotor drone state of the present application;

fig. 6 is a schematic diagram of the stationary drone state of the present application;

fig. 7 is a schematic view of the tail and horizontal tail of the present application.

Description of the reference numerals: 1. a body; 2. a machine head; 3. a support frame; 4. a main wing; 5. mounting grooves; 6. installing a frame; 7. a middle wing beam; 8. a beam seat; 9. a seat cushion; 10. a connecting beam; 11. an outer wing; 12. a rotorcraft arm; 13. a tail pipe; 14. a tail fin; 15. a shape-preserving connecting piece; 16. an inner plugging slot; 17. an inner plug-in connector; 18. an outer plug-in groove; 19. an outer plug-in connector; 20. flattening the tail; 21. a side spar; 22. a hard shell skin; 23. a rear insertion groove; 24. and a rear plug connector.

Detailed Description

The present application is described in further detail below with reference to figures 1-7.

The embodiment of the application discloses VTOL fixed wing unmanned aerial vehicle. Referring to fig. 1, VTOL fixed wing unmanned aerial vehicle includes fuselage 1, aircraft nose 2, and aircraft nose 2 is installed in the head position of fuselage 1, and 1 bottom fixed mounting of fuselage has support frame 3, and support frame 3 is provided with two sets ofly, and support frame 3 can play unmanned aerial vehicle before taking off and descending stable the placing on the holding surface in back.

Referring to fig. 1 and 2, VTOL fixed wing unmanned aerial vehicle still includes the main wing 4, 1 top integrated into one piece of fuselage has mounting groove 5, the 5 top surfaces of mounting groove are the plane setting, 4 bottom integrated into one piece of main wing have installing frame 6, installing frame 6 agrees with mutually with mounting groove 5, and four set screws are worn to be equipped with by the screw thread on the installing frame 6, pre-buried four fixation nut in the mounting groove 5, set screw and fixation nut threaded connection, make through the detachable fixed connection of set screw and fixation nut between installing frame 6 and the fuselage 1, be convenient for the installation and the dismantlement of main wing 4.

Further, the inside of main wing 4 and installing frame 6 is hollow setting and is linked together, the inside of main wing 4 and installing frame 6 is fixed with two sets of well spars 7 jointly, the length direction of well spars 7 is parallel with the length direction of main wing 4, and two sets of well spars 7 are arranged along the width direction of main wing 4, well 7 bottom fixedly connected with beam seats of spar 8, beam seats 8 and the inside fixed connection of installing frame 6, it is required to explain, wear to establish between two sets of beam seats 8 and be connected with seatpad 9, and the bottom is used for supporting seatpad 9 bottom in the installing frame 6. Set up the inside of main wing 4 and installing frame 6 to hollow for reduce unmanned aerial vehicle's weight, the intensity of main wing 4 can be improved in setting up of well pterygoid lamina 7, and the setting up of seatpad 9 not only can support beam seat 8, can also improve the connection stability between two sets of well spars 7.

Preferably, the connecting beam 10 is fixedly connected between the two sets of middle spars 7, so that the connection stability between the two sets of middle spars 7 can be further improved, and the strength of the main wing 4 can be further improved.

Referring to fig. 3, the vtol fixed-wing drone further includes an outer wing 11, a rotor wing arm 12, a tail pipe 13, and a tail wing 14, the main wing 4 is detachably connected to the outer wing 11 through a shape-preserving connector 15, the rotor wing arm 12 is fixedly connected to the shape-preserving connector 15, an inner insertion groove 16 is integrally formed at one end of the main wing 4 away from the main body 1, the inner insertion groove 16 is cylindrical, the shape-preserving connector 15 has a cross section identical to that of the main wing 4 away from the main body 1, and one end of the shape-preserving connector 15 close to the main wing 4 is fixedly connected to an inner insertion connector 17, in this embodiment, the inner insertion connector 17 is a reinforced carbon rod, and the inner insertion connector 17 is in interference fit with the inner insertion groove 16, so as to achieve detachable fixed connection between the main wing 4 and the shape-preserving connector 15.

Referring to fig. 3 and 4, an outer insertion groove 18 is integrally formed at one end of the shape-retaining connector 15 far away from the main wing 4, and an outer insertion piece 19 is fixedly connected at one end of the outer wing 11 near the shape-retaining connector 15, in this embodiment, the outer insertion piece 19 is a reinforced carbon rod, and the outer insertion piece 19 is in interference fit with the outer insertion groove 18, so that the detachable connection between the outer wing 11 and the shape-retaining connector 15 can be realized.

Simultaneously, 1 afterbody integrated into one piece of fuselage has the tube seat, and the tube seat is cylindrically, and 13 one ends of tail pipe insert the tube seat in, and tail pipe 13 and tube seat interference fit, so set up, can realize the detachable fixed connection between fuselage 1 and the tail pipe 13. The tail pipe 13 is fixedly connected with a horizontal tail 20 at one end far away from the fuselage 1.

Referring to fig. 5 and 6, when the unmanned aerial vehicle needs to operate depending on the flight characteristics of the rotary wing type unmanned aerial vehicle, the outer wing 11 is detached from the shape-retaining connector 15, and the tail pipe 13 is detached from the tail of the fuselage 1, so that the fixed wing type unmanned aerial vehicle is converted into the rotary wing type unmanned aerial vehicle; when the flight characteristics that rely on fixed wing unmanned aerial vehicle to carry out work as needs, couple together outer wing 11 and guarantor type connecting piece 15 to be fixed in fuselage 1 afterbody with tail pipe 13, thereby change rotor type unmanned aerial vehicle into fixed wing unmanned aerial vehicle.

Referring to fig. 1, when the flight characteristics that need rely on compound wing unmanned aerial vehicle come the during operation, on fixed wing unmanned aerial vehicle's basis, will be protected type connecting piece 15 and be fixed in between main wing 4 and the outer wing 11 to can realize the conversion between the unmanned aerial vehicle of three kinds of rotor type unmanned aerial vehicle, fixed wing unmanned aerial vehicle and compound wing unmanned aerial vehicle.

Referring to fig. 4, the outer wing 11 is integrally formed, and in order to improve the strength of the outer wing 11, the outer wing 11 includes a side wing spar 21 and a hard shell skin 22, the side wing spar 21 is used as a main supporting member, the hard shell skin 22 is wrapped on the outer side of the side wing spar 21, and the hard shell skin 22 can bear main stress. The high-brightness navigation light, the control surface hinge and the servo installation groove 5 are embedded between the side wing beam 21 and the hard shell skin 22.

Referring to fig. 7, further, rear insertion grooves 23 are integrally formed on two sides of the front end portion of the horizontal tail 20, and a rear insertion part 24 is fixedly connected to the end portion of the tail fin 14, in this embodiment, the rear insertion part 24 is a reinforced carbon rod, and the rear insertion part 24 and the rear insertion groove 23 are in interference fit, so that the detachable fixed connection between the tail fin 14 and the horizontal tail 20 can be realized, and the installation and the detachment of the tail fin 14 are facilitated.

The implementation principle of the vertical take-off and landing fixed wing unmanned aerial vehicle provided by the embodiment of the application is as follows: when the rotor wing type unmanned aerial vehicle needs to work by depending on the flight characteristics of the rotor wing type unmanned aerial vehicle, the outer wing 11 is detached from the shape-preserving connecting piece 15, and the tail pipe 13 is detached from the tail part of the body 1, so that the fixed wing type unmanned aerial vehicle is converted into the rotor wing type unmanned aerial vehicle; when the fixed wing unmanned aerial vehicle needs to work by depending on the flight characteristics of the fixed wing unmanned aerial vehicle, the outer wing 11 is connected with the shape-preserving connecting piece 15, and the tail pipe 13 is fixed at the tail part of the body 1, so that the rotary wing unmanned aerial vehicle is changed into the fixed wing unmanned aerial vehicle; when the flight characteristics that need rely on compound wing unmanned aerial vehicle come the during operation, on fixed wing unmanned aerial vehicle's basis, will protect type connecting piece 15 to be fixed in between main wing 4 and the outer wing 11 to can realize the conversion between the unmanned aerial vehicle of three kinds of rotor type unmanned aerial vehicle, fixed wing unmanned aerial vehicle and compound wing unmanned aerial vehicle.

The above embodiments are preferred embodiments of the present application, and the protection scope of the present application is not limited by the above embodiments, so: all equivalent changes made according to the structure, shape and principle of the present application shall be covered by the protection scope of the present application.

Claims

1. VTOL fixed wing unmanned aerial vehicle, including fuselage (1), set up in aircraft nose (2) of fuselage (1) head, its characterized in that: still including set up in main wing (4) on fuselage (1), set up in outer wing (11) of fuselage (1) one end are kept away from in main wing (4), set up in rotor horn (12) between main wing (4) and outer wing (11), set up in tail pipe (13) of fuselage (1) afterbody and set up in fin (14) of tail pipe (13), detachable connection between main wing (4) and outer wing (11), rotor horn (12) are connected with main wing (4) and outer wing (11) are detachable through shape-preserving connecting piece (15), tail pipe (13) one end is pegged graft in fuselage (1) afterbody.

2. The vtol fixed wing drone of claim 1, wherein: the aircraft is characterized in that one end, far away from the aircraft body (1), of the main wing (4) is provided with an inner insertion groove (16), one end of the shape-preserving connecting piece (15) is provided with an inner insertion piece (17) in interference fit with the inner insertion groove (16), one end of the shape-preserving connecting piece (15) is provided with an outer insertion groove (18), and one end of the outer wing (11) is provided with an outer insertion piece (19) in interference fit with the outer insertion groove (18).

3. The vtol fixed wing drone of claim 1, wherein: mounting groove (5) have been seted up at fuselage (1) top, the position that main wing (4) are close to fuselage (1) is provided with installing frame (6), through fixed screw connection between installing frame (6) and mounting groove (5).

4. The vtol fixed wing drone of claim 1, wherein: the tail pipe is characterized in that a horizontal tail (20) is arranged at one end of the tail pipe (13), a rear insertion groove (23) is formed in the end portion of the horizontal tail (20), and a rear insertion piece (24) in interference fit with the rear insertion groove (23) is arranged at the end portion of the tail fin (14).

5. The vtol fixed wing drone of claim 1, wherein: the outer wing (11) comprises a side wing beam (21) and a hard shell skin (22) arranged outside the side wing beam (21).

6. The vtol fixed wing drone of claim 1, wherein: the main wing (4) and the mounting frame (6) are internally provided with two groups of middle wing beams (7) together, the bottom of each middle wing beam (7) is provided with a beam seat (8), and the beam seats (8) are provided with a plurality of seat cushions (9) in a penetrating mode.

7. The VTOL fixed wing drone of claim 6, wherein: a connecting beam (10) is arranged between the two middle wing beams (7).

8. The vtol fixed wing drone of claim 1, wherein: the bottom of the machine body (1) is provided with a support frame (3).