CN106741932B

CN106741932B - Nine unmanned aerial vehicle of mixed type based on VTOL

Info

Publication number: CN106741932B
Application number: CN201611028137.3A
Authority: CN
Inventors: 罗娟
Original assignee: Sichuan Shanghang Intelligence Technology Co ltd
Current assignee: Sichuan Shanghang Intelligence Technology Co ltd
Priority date: 2016-11-22
Filing date: 2016-11-22
Publication date: 2020-11-03
Anticipated expiration: 2036-11-22
Also published as: CN106741932A

Abstract

The invention discloses a hybrid nine-axis unmanned aerial vehicle based on vertical take-off and landing, which comprises a fixed wing mechanism and a multi-rotor mechanism, the multi-rotor wing structure is fixedly arranged on the fixed wing structure, the fixed wing structure is composed of a front wing, two safety side bands, a tail wing and a body bin, one end of each safety side band is fixedly arranged on the surfaces of the left side and the right side of the front wing and is parallel to each other, the other end of each safety side band is fixedly connected with the other end of each safety side band and is parallel to the front wing, and the two ends of each body bin are fixedly connected with the middle positions of the front wing and the tail wing respectively, the multi-rotor mechanism is composed of two groups of horizontal rotor mechanisms which are respectively and fixedly arranged at two sides of the fuselage bin and a vertical rotor mechanism which is fixedly arranged at the center of the tail wing, the middle bottom surface of the machine body cabin is provided with a square machine body cabin mounting opening, the tail part of the machine body cabin is provided with a round hole, and the two ends below the front wing and the machine body cabin are fixedly provided with roller wheel supports. The invention has the advantages of being capable of adapting to more environments, enabling the flight time range of the airplane body to be longer and saving a large amount of resources.

Description

Nine unmanned aerial vehicle of mixed type based on VTOL

Technical Field

The invention relates to an unmanned aerial vehicle, in particular to a hybrid nine-axis unmanned aerial vehicle based on vertical take-off and landing.

Background

The rotary wing type unmanned aerial vehicle has the advantages of flexible control, vertical take-off and landing, small size and the like, is not limited by a field, and is widely applied to the aspects of aerial photography, surveying and the like. Fixed wing formula unmanned aerial vehicle has duration, and the range is far away, can be used for long-distance task.

Disclosure of Invention

The invention aims to solve the problems and designs a hybrid nine-axis unmanned aerial vehicle based on vertical take-off and landing.

The hybrid nine-axis unmanned aerial vehicle based on vertical take-off and landing comprises a fixed wing mechanism and a multi-rotor mechanism, wherein the multi-rotor mechanism is fixedly arranged on the fixed wing structure, the fixed wing structure is composed of a front wing, two safety side bands, an empennage and a fuselage bin, one end of each safety side band is fixedly arranged on the surfaces of the left side and the right side of the front wing and is parallel to the other end of the front wing, the fuselage bin is fixedly connected with the other end of each safety side band and is parallel to the front wing, and two ends of each fuselage bin are fixedly connected with the middle positions of the front wing and the empennage respectively, the multi-rotor mechanism is composed of two groups of horizontal rotor mechanisms and a vertical rotor mechanism, the two groups of horizontal rotor mechanisms are fixedly arranged on the two sides of the fuselage bin respectively, the horizontal rotor mechanisms are composed of horizontal rotor supports, two ends of the horizontal rotor supports are fixedly, Two sets of horizontal rotor of fixed mounting on the horizontal rotor support constitute jointly, vertical rotor mechanism by fixed mounting at the vertical driving motor of tail wing center department with vertical driving motor rotation end fixed connection's a vertical thrust paddle constitute jointly, open bottom surface in the middle of the fuselage storehouse has square fuselage storehouse carry mouth and afterbody to open there is the round hole, the equal fixed mounting in both ends has gyro wheel support in wing and fuselage storehouse below before the aircraft.

The horizontal rotor is a rotor device which is provided with two horizontal driving motors and a horizontal blade fixedly connected with the rotating end of each horizontal driving motor.

The front wing of the airplane is an n-shaped integrated wing.

The shapes of the front wing and the tail wing are both in a flat streamline shape.

And each horizontal driving motor and each vertical driving motor are internally provided with a blade coupling.

And an elevator is arranged on the tail wing.

And a rudder is arranged on the vertical rotor wing bracket.

And a battery or a loaded heavy object can be arranged in the square body cabin loading port.

The round hole can be internally provided with a navigation device.

And the roller bracket is provided with a roller.

The hybrid nine-axis unmanned aerial vehicle based on vertical take-off and landing, which is manufactured by the technical scheme of the invention, has the advantages of simple and compact structure, innovation, attractiveness, no limitation of the take-off and landing of the body by terrain, capability of adapting to more environments, longer flight time range of the body, saving of a large number of resources, capability of meeting more task requirements, strong practicability and wide applicability.

Drawings

Fig. 1 is a schematic structural diagram of a hybrid nine-axis unmanned aerial vehicle based on vertical take-off and landing according to the present invention;

FIG. 2 is a top view of a hybrid nine-axis VTOL based unmanned aerial vehicle of the present invention;

fig. 3 is a front view of a hybrid nine-axis drone based on vertical take-off and landing according to the present invention;

FIG. 4 is a left side view of a hybrid nine-axis VTOL based unmanned aerial vehicle of the present invention;

in the figure, 1, a front wing; 2. a safety sideband; 3. an aircraft tail wing; 4. a fuselage bin; 5. a horizontal rotor support; 6. a horizontal rotary wing; 7. a vertical drive motor; 8. vertically pushing the paddle; 9. a square fuselage bin mounting port; 10. a circular hole; 11. a roller bracket; 12. a horizontal driving motor; 13. a horizontal paddle; 14. blade coupling; 15. an elevator; 16. a vertical rotor support; 17. a rudder; 18. and a roller.

Detailed Description

The invention is described in detail below with reference to the accompanying drawings, and as shown in fig. 1-4, a hybrid nine-axis unmanned aerial vehicle based on vertical take-off and landing comprises a fixed wing mechanism and a multi-rotor mechanism, wherein the multi-rotor structure is fixedly mounted on the fixed wing structure, the fixed wing structure comprises a front wing (1), two safety sidebands (2) with one ends fixedly mounted on the surfaces of the left and right sides of the front wing (1) and parallel to each other, a rear wing (3) fixedly connected with the other ends of the two safety sidebands (2) and parallel to the front wing (1), and a fuselage bin (4) with two ends fixedly connected with the middle positions of the front wing (1) and the rear wing (3) respectively, the multi-rotor mechanism comprises two groups of horizontal rotor mechanisms fixedly mounted on the two sides of the fuselage bin (4) respectively and a vertical rotor mechanism fixedly mounted at the center of the fuselage bin (3), the horizontal rotor wing mechanism is composed of a horizontal rotor wing bracket (5) and two groups of horizontal rotor wings (6), wherein the two ends of the horizontal rotor wing bracket (5) are fixedly installed on a front wing (1) and a tail wing (3) respectively, the two groups of horizontal rotor wings (6) are fixedly installed on the horizontal rotor wing bracket (5) together, the vertical rotor wing mechanism is composed of a vertical driving motor (7) fixedly installed at the center of the tail wing (3) and a vertical pushing paddle (8) fixedly connected with the rotating end of the vertical driving motor (7) together, a square fuselage cabin mounting opening (9) is formed in the middle bottom surface of the fuselage cabin (4) and a round hole (10) is formed in the tail part of the fuselage cabin, and roller wheel brackets (11) are fixedly installed at the two ends below the front wing (1); the horizontal rotary wing (6) is a rotary wing device provided with two horizontal driving motors (12) and one horizontal blade (13) fixedly connected with the rotating end of each horizontal driving motor (12); the front wing (1) is an n-shaped integrated wing; the shapes of the front wing (1) and the tail wing (3) are both in a flat streamline shape; a blade coupling (14) is arranged in each horizontal driving motor (12) and each vertical driving motor (7); an elevator (15) is arranged on the empennage (3); a rudder (17) is arranged on the vertical rotor wing bracket (16); a battery or a loading heavy object can be installed in the square machine body cabin loading port (9); a navigation device can be arranged in the round hole (10); and the roller bracket (11) is provided with a roller (18).

The multi-rotor mechanism is characterized by comprising a fixed wing mechanism and a multi-rotor mechanism, wherein the multi-rotor mechanism is fixedly arranged on the fixed wing structure, the fixed wing structure is composed of a front wing, two safety side bands with one ends fixedly arranged on the surfaces of the left side and the right side of the front wing and parallel to each other, a tail wing fixedly connected with the other ends of the two safety side bands and parallel to the front wing, and a fuselage bin with two ends respectively fixedly connected with the middle positions of the front wing and the tail wing, the multi-rotor mechanism is composed of two groups of horizontal rotor mechanisms respectively and fixedly arranged on the two sides of the fuselage bin and a vertical rotor mechanism fixedly arranged at the center of the tail wing, the horizontal rotor mechanism is composed of a horizontal rotor bracket with two ends respectively and fixedly arranged on the front wing and the tail wing, and two groups of horizontal rotors fixedly arranged on the horizontal rotor bracket, and the vertical rotor mechanism is composed of a vertical driving motor fixedly arranged at the center and a rotary connecting end fixedly connected with the The perpendicular promotion paddle that connects constitutes jointly, the bottom surface is opened in the middle of the fuselage storehouse has square fuselage storehouse carry mouthful and the afterbody is opened there is the round hole, the equal fixed mounting in wing and fuselage storehouse below both ends has the gyro wheel support before the aircraft, moreover, the steam generator is simple and compact in structure, the innovation is pleasing to the eye, the unmanned aerial vehicle structure of mixed type, let the take-off and landing of organism not restricted by the relief, can adapt to more environment, let the voyage distance of organism farther during voyage, save a large amount of resources, satisfy more task demands, therefore, the clothes hanger is strong in practicability, and wide.

In the embodiment, when a user starts the device, the vertical driving motor fixedly arranged at the center of the empennage can be started through remote control, the vertical driving motor is started to drive the vertical pushing paddle fixedly connected with the rotating end of the vertical driving motor to start rotating so as to provide propulsion power for the operation of the device, the elevator arranged at the empennage can adjust the elevation amplitude during taking off, flat flying, landing and other actions, can assist the body to fly under different modes and improve the flight performance, when the device is started and operated, the paddle coupling in the vertical driving motor transmits information to the paddle coupling in each horizontal driving motor to start the horizontal driving motor on the horizontal rotor support, the horizontal driving motor is started to drive the horizontal paddle fixedly connected with the rotating end of the horizontal driving motor to start rotating, and the two ends of the horizontal rotor support are respectively fixedly arranged on the front wing and the empennage, and install horizontal rotor support respectively in fuselage storehouse both sides, when two sets of horizontal rotors on horizontal rotor support start, vertical take-off and landing and attitude control are realized to horizontal rotor, the lift control and the stability of organism have been improved, install the rudder on the vertical rotor support, the rudder can cooperate horizontal rotor to do course regulation, can change the angle of rudder, control is nimble, can assist the organism direction to change well, mountable battery or load heavy object in the square fuselage storehouse carry mouth of fuselage storehouse middle bottom surface, mountable navigation head in the round hole of fuselage storehouse afterbody.

In this embodiment, the front wing, the fuselage bin and the tail wing of the main body form a fixed wing structure through the safety side bands on two sides of the main body, when flying at high speed, the lifting force provided by the front wing and the tail wing can greatly improve the flight performance, the safety side bands can play a role in protecting the device, the main body is formed by using a composite material, is hard and hollow, and is designed by adopting the aerodynamic characteristics of a fixed wing type, and the shapes of the front wing and the tail wing are both flat and streamlined, so that the aerodynamic resistance can be reduced and partial lifting force can be provided when the device operates. The roller wheel supports arranged on the bottom surfaces of the two sides of the front wing and the bottom surface of the middle part of the tail wing can be used for supporting the main machine body on the ground, and the roller wheels on the roller wheel supports facilitate the movement of the main machine body on the ground.

The technical solutions described above only represent the preferred technical solutions of the present invention, and some possible modifications to some parts of the technical solutions by those skilled in the art all represent the principles of the present invention, and fall within the protection scope of the present invention.

Claims

1. The utility model provides a nine unmanned aerial vehicle of mixed type based on VTOL, a serial communication port, including fixed wing mechanism and many rotor mechanism, many rotor structure fixed mounting are structural at the fixed wing, the fixed wing structure by the aircraft front wing (1), one end fixed mounting aircraft front wing (1) left and right sides on the surface and two safety sideband (2) that are parallel to each other, with two safety sideband (2) other end fixed connection and with aircraft front wing (1) aircraft tail wing (3) that are parallel to each other, both ends constitute jointly with aircraft front wing (1) and aircraft tail wing (3)'s intermediate position fixed connection's fuselage storehouse (4) respectively, many rotor mechanism constitute jointly by two sets of horizontal rotor mechanism of fixed mounting respectively in fuselage storehouse (4) both sides and the vertical rotor mechanism of fixed mounting in aircraft tail wing (3) center department, horizontal rotor mechanism is by its both ends difference fixed mounting horizontal rotor support (5) on aircraft front wing (1) and aircraft tail wing (3) ) Two sets of horizontal rotors (6) of fixed mounting on horizontal rotor support (5) constitute jointly, vertical rotor mechanism by fixed mounting at the vertical drive motor (7) of tail wing (3) center department and with vertical drive motor (7) rotatory end fixed connection's a vertical push paddle (8) constitute jointly, open bottom surface has square fuselage storehouse carry mouth (9) and afterbody to open in the middle of fuselage storehouse (4) and has round hole (10), the equal fixed mounting in fuselage front wing (1) and fuselage storehouse (4) below both ends has gyro wheel support (11), horizontal rotor (6) are for having two horizontal drive motor (12) and the rotor device with a horizontal paddle (13) of every horizontal drive motor (12) rotatory end fixed connection, aircraft front wing (1) are n type integrative wing, the shape of aircraft front wing (1) and tail wing (3) is flat streamline, all be equipped with paddle coupling (14) in every horizontal drive motor (12) and vertical drive motor (7), be equipped with elevator (15) on empennage (3), be equipped with rudder (17) on vertical rotor support (16).

2. The hybrid nine-axis unmanned aerial vehicle based on VTOL of claim 1, wherein the square fuselage cabin carrying port (9) can be internally provided with batteries or carrying heavy objects.

3. The hybrid nine-axis unmanned aerial vehicle based on VTOL of claim 1, wherein the round hole (10) is installed with a navigation device.

4. The hybrid nine-axis unmanned aerial vehicle based on VTOL of claim 1, wherein the roller bracket (11) is mounted with rollers (18).