CN210555573U

CN210555573U - Vertical take-off and landing fixed wing unmanned aerial vehicle

Info

Publication number: CN210555573U
Application number: CN201920553363.6U
Authority: CN
Inventors: 程欣; 王迪鑫
Original assignee: Individual
Current assignee: Individual
Priority date: 2019-04-22
Filing date: 2019-04-22
Publication date: 2020-05-19
Anticipated expiration: 2029-04-22

Abstract

The utility model discloses a VTOL fixed wing unmanned aerial vehicle relates to unmanned air vehicle technique field. The aircraft comprises an airframe, wings, a tilting structure and a power system. The fuselage is provided with a wing middle section limiting hole, a first limiting hole of a tilting structure and a second limiting hole; the wings are of a detachable three-section structure, and the middle wings are fixed on the fuselage through limiting holes in the fuselage; the tilting structure is in a symmetrical structure with a vertical take-off and landing fixed wing unmanned aerial vehicle central axis, and two symmetrical parts are connected through a first connecting rod and a second connecting rod, so that the conversion of take-off and landing and flying modes is realized, wherein the tilting structure is provided with a limit hole of a middle section wing, the first end of the middle section wing passes through the limit hole of the first end of the tilting structure, and the second end of the middle section wing passes through the limit hole of the second end of the tilting structure. The utility model has the advantages that: the vertical landing of the unmanned aerial vehicle is realized, the requirement of the unmanned aerial vehicle with the fixed wing structure on the field in the process of taking off and landing is reduced, the cost is reduced, and the efficiency is improved.

Description

Vertical take-off and landing fixed wing unmanned aerial vehicle

Technical Field

The utility model relates to an unmanned aerial vehicle field, in particular to VTOL fixed wing unmanned aerial vehicle.

Background

A drone is an unmanned aircraft that is operated by a radio remote control device and a self-contained program control device. Unmanned aerial vehicle possesses the huge advantages such as adapt to abominable complicated environment, need not personnel and drive, loss less, has obtained more and more extensive concern and application. Unmanned aerial vehicle technology is increasingly applied in the fields of aerial photography, surveying and mapping, environmental reconnaissance and the like. Along with the maturity of unmanned aerial vehicle technique and the increase of unmanned aerial vehicle technique application, the kind of unmanned aerial vehicle also tends to diversification gradually. Compared with manned aircraft, the unmanned aerial vehicle has the characteristics of small volume, low manufacturing cost, convenience in carrying and strong adaptability to various flight environments, and can be widely applied to aerial survey remote sensing, meteorological monitoring, agricultural plant protection and other works. Compared with a multi-rotor unmanned aerial vehicle, the fixed-wing unmanned aerial vehicle has long endurance time but has higher requirements on the take-off and landing site, and the vertical take-off and landing fixed-wing unmanned aerial vehicle has the advantages of the multi-rotor unmanned aerial vehicle and the fixed-wing unmanned aerial vehicle, has long endurance time and is not limited by the site.

SUMMERY OF THE UTILITY MODEL

The utility model provides a VTOL fixed wing has solved unmanned aerial vehicle's among the prior art problem. The technical scheme is as follows:

a vertical take-off and landing fixed wing unmanned aerial vehicle comprises a fuselage, wings and a tilting rotor system (comprising a tilting structure and a power system).

Further, the wingspan of the VTOL fixed wing UAV is 1600 mm.

Furthermore, the fuselage of the vertical take-off and landing fixed-wing unmanned aerial vehicle is provided with a vertical tail wing and a horizontal tail wing which are fixedly installed.

Further, the main body of the tilting structure is formed by fixedly connecting a wooden box-shaped structure arm and a carbon transverse rod, the two ends of the structure arm are fixed with the motor mounting platform through screws, and the motor mounting platform is embedded into the structure arm

Further, the power system and the tilting structure are fixedly connected through a screw.

Further, a flight control module is arranged inside the fuselage.

The utility model discloses, the wing is for dismantling syllogic structure, simple structure, and is with low costs, small, portable, easily installation and maintenance, and duration is strong, can adapt to the operation environment of various abominable complicacies.

Drawings

In order to more clearly illustrate the technical solution of the present invention, the drawings required for the present invention will be briefly described below.

Fig. 1 is the utility model discloses a VTOL unmanned aerial vehicle's overall structure schematic diagram.

Fig. 2 is the utility model discloses a VTOL unmanned aerial vehicle's rotor system that verts schematic diagram.

Fig. 3 is a schematic view of the motor mounting platform of the present invention.

Fig. 4 is the utility model discloses a VTOL unmanned aerial vehicle's action of taking off and land schematic diagram.

Fig. 5 is the horizontal flight action schematic diagram of the vertical take-off and landing unmanned aerial vehicle of the utility model.

In the figure, 1, a middle wing section; 2. a limiting hole; 3. a body; 4. a structural arm; 5. a cross bar; 6. an outboard section of the wing; 7. a wing seam; 8. a motor mounting platform; 9. a screw; 10. a motion driver; 11. three connecting rods; 12. a horizontal tail fin stabilizer; 13. a vertical tail fin stabilizer; 14. a horizontal tail control surface; 15. a vertical tail control surface; 16. a flight control system; 17. electrically adjusting; 18. a motor; 19. a rotor wing.

Detailed Description

The present invention will be described in further detail with reference to the accompanying drawings and specific embodiments.

As shown in fig. 1-5, a vertical take-off and landing fixed wing aircraft comprises a wing middle section 1; the middle section of the wing penetrates through the limiting hole 2 and is nested in the fuselage 3; structural arms 4 on two sides of the fuselage 3 are nested in the middle section 1 of the wing in the same way; the two cross rods 5 penetrate through the machine body 3 and are fixed at the front end and the rear end of the structural arm 4; the outer wing section 6 is connected with the middle wing section 1 through a wing joint 7; the motor mounting platform 8 is connected through a screw 9; the motion drivers 10 are embedded at the front end and the rear end of the structural arm 4; the motion driver 10 drives the motor mounting platform 8 to move through the three connecting rods 11; the motor provided with the rotor wing 19 is fixed on the motor mounting platform 8 through a bolt; the horizontal tail fin stabilizer 12 is positioned at the rear part of the machine body 2 and is fixedly embedded in the rear part of the machine body; the vertical tail fin stabilizer 13 is positioned at the rear part of the machine body 2 and is fixedly embedded; the horizontal tail control surface 14 is connected to the horizontal tail stabilizing surface 12 by a hinge; the vertical tail control surface 15 is connected to the vertical tail stabilizing surface 13 by a hinge; the flight control system 16 is fixed inside the fuselage 2; the flight control system 16 is fixed on the upper side of the wing middle section 1. The electric regulator 17 is positioned inside the box-type structures at the two ends of the structure arm 4; the motor 18 is connected with the electric regulator 17 and fixed on the motor mounting platform 8; the rotor 19 is fixed on the upper part of the motor 18.

The utility model discloses when using, at first on this unmanned aerial vehicle arranges the horizontal stand in, the motion driver 10 at both ends makes 8 vertical upwards of two motor mounting platforms in front side through 11 driving motor mounting platform 8 of three-bar linkage around two structure arms 4, makes 8 vertical downwards of two motor mounting platforms in rear side. Starting unmanned aerial vehicle at this moment, two rotors of front side 19 provide the pull-up force, and two rotors of rear side 19 provide thrust down, wholly provide lift upwards, and 19 torsions of each rotor offset each other.

When unmanned aerial vehicle rises to a take the altitude, the motion driver 10 at both ends passes through three connecting rods 11 driving motor mounting platforms 8 around two structure arms 4, makes two motor mounting platforms 8 of front side upwards slowly vert to the level forward by vertical, makes two motor mounting platforms 8 of rear side slowly vert to the level backward by vertical downwards. Unmanned aerial vehicle, two rotors 19 of front side provide pulling force forward at this moment, and two rotors 19 of rear side provide thrust backward, wholly provide pulling force forward, and 19 torsions of each rotor offset each other. In the process that the unmanned aerial vehicle slowly tilts by the four-motion driver 10 through the three-connecting-rod 11 to drive the four-motor mounting platform 8, the lift force source is gradually provided by the four rotors 19 and transits to the power provided by the organic wings. During tilting, and during flight, stability is provided by flight control system 16.

After the four rotors 19 are in a state of completely providing forward pulling force, the horizontal tail control surface 14 connected to the horizontal tail stabilizing surface 12 moves around the hinge, and the pitching and climbing actions of the unmanned aerial vehicle can be realized. The vertical tail control surface 15 connected to the vertical tail stabilizing surface 13 moves around the hinge, so that the steering action of the unmanned aerial vehicle can be realized. The motion driver 10 at both ends passes through 11 driving motor mounting platform 8 of three connecting rods around the left side structure arm 4, make two motor mounting platform 8 of front side forward by the level downwards or upwards vert certain angle, two motor mounting platform 8 of rear side backward by the level upwards or downwards certain angle verts, the motion driver 10 at both ends passes through 11 driving motor mounting platform 8 of three connecting rods around the left side structure arm 4, make two motor mounting platform 8 of front side forward by the level upwards or downwards vert certain angle, two motor mounting platform 8 of rear side turn to down or upwards certain angle by the level backward tilting, realize that unmanned aerial vehicle rolls over on the right side left side.

When unmanned aerial vehicle need descend, the motion driver 10 at both ends passes through three connecting rods 11 driving motor mounting platforms 8 around two structure arms 4, makes two motor mounting platforms 8 of front side slowly vert forward by the level to vertical upwards, makes two motor mounting platforms 8 of rear side slowly vert backward by the level to vertical downwards. Unmanned aerial vehicle at this moment, two rotors 19 of front side provide the pull-up force, and two rotors 19 of rear side provide thrust down, wholly provide the pull-up force, and 19 torsions of each rotor offset each other. The four rotors of unmanned aerial vehicle flight control system 16 control provide the pulling force and reduce, realize that unmanned aerial vehicle height descends slowly, and the position is predetermine on ground to final descending.

The utility model discloses well flight control system 16, electricity are conventional public part such as 17, installation and inside for regulate and control motor 18, its concrete structure need not to show in the drawing, and the skilled person in the art clearly understands what kind of concrete structure of selection and motor 18 and carries out the adaptation etc..

The utility model discloses in flight control system 16, flight control module, electricity are transferred 17, motor 18 and power etc. are the technical means that conventional in this field was disclosed, and for the necessary electron device of conventional unmanned aerial vehicle etc. need not to be repeated here, and the concrete structure of part device also need not to show in the drawing, and the technical staff in the art can clearly understand its concrete structure, how to install, control logic and specific control circuit etc. can realize complete technical scheme.

Claims

1. The utility model provides a VTOL fixed wing unmanned aerial vehicle which characterized in that: the aircraft comprises a fuselage, wings, a tilting structure and a power system; the fuselage is provided with a wing middle section limiting hole, a first limiting hole of a tilting structure and a second limiting hole; the wings comprise three sections, namely a first section of wings, a middle section of wings and a third section of wings from right to left; the middle section wing is fixed on the machine body, and the tilting structure is fixed on the machine body; each section of wing is provided with a first end part and a second end part, the second end part of the first section of wing is connected with the first end part of the middle section of wing in a bonding mode, and the first end part of the third section of wing is connected with the second end part of the middle section of wing in a bonding mode; the tilting structure comprises a first connecting rod, a second connecting rod, a first structure arm and a second structure arm; the power system comprises a plurality of motors and a plurality of electric adjusters, and the first end parts and the second end parts of the first structural arms and the second structural arms are in one-to-one correspondence with the motor electric adjusters.

2. A vtol fixed wing drone according to claim 1, characterized in that: the wing is a detachable three-section structure.

3. A vtol fixed wing drone according to claim 1, characterized in that: the middle section wing passes through the position of the wing middle section limiting hole of the fuselage, the central axis is superposed with the central axis of the fuselage, and the middle section wing and the fuselage are fixed in an adhesive mode.

4. A vtol fixed wing drone according to claim 1, characterized in that: the tilting structure uses the central axis of the machine body as a symmetrical line structure, the first connecting rod of the tilting structure penetrates through a first limiting hole of the machine body to be connected with the tilting structure, and the second connecting rod of the tilting structure penetrates through a second limiting hole of the machine body to be connected with the tilting structure.

5. A vtol fixed wing drone according to claim 1, characterized in that: the power system comprises a plurality of motors, a plurality of electric regulators and a plurality of rotors.

6. A VTOL fixed-wing drone according to claim 5, characterized in that: power system is through the motor mounting platform that corresponds and vert structure fixed connection, the structure that verts drives power system is at the flat angle of verting of flying mode conversion in-process of taking off and landing mode, thereby realizes VTOL fixed wing unmanned aerial vehicle's quick take off and land and fly.

7. A vtol fixed wing drone according to claim 6, characterized in that: the motor mounting platform is connected with a first structure arm and a second structure arm of the tilting structure through the screw rod, and the motor mounting platform is tilted by an angle around the screw rod in the working process of the tilting structure.