CN215361831U - Miniature fixed wing unmanned aerial vehicle - Google Patents

Abstract

The utility model relates to a micro fixed wing unmanned aerial vehicle, which comprises a machine head and a machine body, wherein the machine body is formed by splicing a main longitudinal beam, a cross beam arranged at the front end of the main longitudinal beam and a tail beam arranged at the rear end of the main longitudinal beam; taking the main longitudinal beam as a symmetry axis, and symmetrically arranging and fixedly connecting at least two pairs of rib plates on the cross beam, wherein the rib plate close to the main longitudinal beam is marked as a first rib plate, and the rib plate close to the end part of the cross beam is marked as a second rib plate; two horizontal tail wings are mounted at the tail of the machine body, and side wings are arranged on the second rib plates; the machine head is arranged between the two first ribbed plates and is fixedly connected with the first ribbed plates; the beam is provided with a hook plate, and the hook plate is provided with an ejection hook matched with the ejection launching device. The utility model has the advantages of low cost, capability of carrying a certain weight and capability of accurately positioning.

Description

Miniature fixed wing unmanned aerial vehicle

Technical Field

The utility model relates to a micro fixed-wing unmanned aerial vehicle, and belongs to the technical field of unmanned aerial vehicles.

Background

Unmanned aerial vehicles are classified according to the configuration of a flight platform, and are generally divided into fixed-wing unmanned aerial vehicles and rotor wing unmanned aerial vehicles. At present, in the field of subminiature unmanned aerial vehicles, only rotor subminiature unmanned aerial vehicles exist in the industry, the rotor generates lifting force, the unmanned aerial vehicles can vertically take off, land and hover, the technology is mature relatively, and the unmanned aerial vehicles have a large market.

However, in some fields, for example, fire extinguishing is performed by carrying fire extinguishing bomb to hit a fire catching part during fire extinguishing, because the rotor type unmanned aerial vehicle has one or more rotors, the size of the rotor type unmanned aerial vehicle is limited, the cost is high, and the rotor type unmanned aerial vehicle can fail under a high-temperature condition and cannot accurately complete positioning, so that the use of the rotor type unmanned aerial vehicle is limited; when the size of the fixed-wing unmanned aerial vehicle is small, the total lift force provided by the fixed-wing unmanned aerial vehicle is small, so that the problem that the lift force is insufficient commonly exists in the ultra-miniature fixed-wing unmanned aerial vehicle, fire extinguishing bombs cannot be carried, and the fixed-wing unmanned aerial vehicle does not have practical value.

In addition, the traditional ultramicro-miniature unmanned aerial vehicle generally uses balsa wood or foam to form a truss-type fuselage, cannot be impacted for many times, maintains the pneumatic appearance, and has great loss in practicability and flexibility.

Therefore, how to provide an unmanned aerial vehicle that has a lower cost, can carry certain weight and can pinpoint becomes the problem that awaits a urgent need to be solved.

Disclosure of Invention

The technical problem to be solved by the utility model is as follows: the unmanned aerial vehicle is lower in cost, can carry certain weight and can pinpoint.

In order to solve the technical problems, the technical scheme provided by the utility model is as follows: a micro fixed wing unmanned aerial vehicle comprises a machine head and a machine body, wherein the machine body is formed by splicing a main longitudinal beam, a cross beam arranged at the front end of the main longitudinal beam and a tail beam arranged at the rear end of the main longitudinal beam, and a skin covers the machine body; taking the main longitudinal beam as a symmetry axis, and symmetrically arranging and fixedly connecting at least two pairs of rib plates on the cross beam, wherein the rib plate close to the main longitudinal beam is marked as a first rib plate, and the rib plate close to the end part of the cross beam is marked as a second rib plate; the tail parts of the first rib plate and the second rib plate are fixedly connected with a tail beam, two horizontal tail wings are mounted at the tail part of the machine body, and the two horizontal tail wings are symmetrically arranged by taking the main longitudinal beam as a symmetry axis; the second rib plates are provided with side wings, and the two side wings are also symmetrically arranged by taking the main longitudinal beam as a symmetry axis; the machine head is arranged between the two first ribbed plates and is fixedly connected with the first ribbed plates; the beam is provided with a hook plate, and the hook plate is provided with an ejection hook matched with the ejection launching device. Preferably, the rib plate is arranged in parallel with the main longitudinal beam.

This practicality adopts hollow frame construction to omit power structures such as engine, reduced the space and taken (reduced the volume), reduced weight, the cost is reduced makes and carries fire extinguishing bomb etc. through the aircraft nose, is used for practical application such as fire control fire fighting to become possible.

The utility model carries out ejection and launching through the ejection rack, thereby not only saving the cost of providing power, solving the problem of insufficient lift force commonly existing in the ultra-miniature fixed wing unmanned aerial vehicle, but also reducing the weight of the unmanned aerial vehicle, and controlling the ejection and launching device to obtain an accurate running track through the calculation in advance, thereby realizing accurate positioning. In addition, the ejection hook shape of the hook plate has strong adaptability, and the structural requirement of the launcher for launching can be simplified.

In order to further accurately position, the technical scheme is further improved as follows: the empennage with the organism pin joint, be equipped with the steering wheel on the first floor, the rigid coupling has the rudder foot on the empennage, the steering wheel passes through the pull rod steel wire and is connected with the rudder foot.

In order to strengthen the strength of the skin fuselage, the technical scheme is further improved as follows: the skin adopts the thin shell structure that carbon fiber made, and the thin shell structure of carbon fiber accessible 3D prints and accomplishes, and the skin fuselage can bear the pneumatic appearance of self maintaining when assaulting many times.

In order to further reduce the weight of the fuselage, it is preferable that the main longitudinal beams, the cross beams, the tail beams and the rib plates are all provided with lightening holes, and the tail wings and the side uniform wings are of hollow structures.

In order to further improve the power of the unmanned aerial vehicle, it is preferable that a motor and a propeller driven by the motor are arranged on the main longitudinal beam.

Preferably, a camera is arranged on the machine head.

Drawings

The utility model will be further explained with reference to the drawings.

Fig. 1 is a schematic structural diagram of an embodiment of the present invention.

Fig. 2 is a schematic structural view of the body in the embodiment of the present invention.

Fig. 3 is a schematic diagram of a steering engine and a rudder foot in the embodiment of the utility model.

Fig. 4 is a schematic view of the installation of the camera in the embodiment of the present invention.

Reference numerals: 1. a cross beam; 2. a main stringer; 3. an upper housing; 4. a machine head; 5. a camera; 6. a side wing; 7. a tail wing; 8. a motor; 9. a first rib plate; 10. a third rib plate; 11. a second rib plate; 12. a tail boom; 13. a leading edge panel; 14. a hook plate; 15. a hook plate beam; 16. a steering engine; 17. a rudder horn; 18. a pull rod steel wire; 19. a rudder foot; 20. a lower housing; 21. a pivot shaft.

Detailed Description

Examples

The miniature fixed wing unmanned aerial vehicle of this embodiment, as shown in fig. 1, including aircraft nose 4 and organism, the organism is formed by main longitudinal beam 2, the crossbeam 1 that sets up at 2 front ends of main longitudinal beam and the tail boom 12 concatenation that sets up at 2 rear ends of main longitudinal beam, the organism coats outward and has the covering (not shown in the figure). As shown in fig. 1 and 4, the top of the head 4 is provided with an upper housing 3, and the bottom of the head 4 is provided with a lower housing 20.

As shown in fig. 1 and 2, the main longitudinal beam 2 is taken as a symmetry axis, and at least two pairs of rib plates are symmetrically arranged and fixedly connected on the cross beam 1, wherein the rib plate close to the main longitudinal beam 2 is taken as a first rib plate 9, and the rib plate close to the end of the cross beam 1 is taken as a second rib plate 11; the tail parts of the first rib plate 9 and the second rib plate 11 are fixedly connected with the tail beam 7, and the head parts of the first rib plate and the second rib plate are fixedly connected through a front edge plate 13. In this embodiment there are three pairs of ribs, i.e. a third rib 10 is provided between the first 9 and second 11 ribs. Preferably, the rib is arranged parallel to the main longitudinal beam 2. In order to facilitate installation and disassembly, the novel middle rib plate and the machine body and all parts of the machine body are installed in an inserting mode.

Two horizontal tail wings 7 are installed at the tail part of the machine body, and the two horizontal tail wings 7 are symmetrically arranged by taking the main longitudinal beam 2 as a symmetry axis. And the second rib plates 11 are provided with side wings 6, and the two side wings 6 are also symmetrically arranged by taking the main longitudinal beam 2 as a symmetry axis.

The machine head 4 is arranged between the two first ribbed plates 9, and the machine head 4 is fixedly connected with the first ribbed plates 9; the beam 1 is provided with a hook plate 14, and the hook plate 14 is provided with an ejection hook matched with the ejection launching device. Hook plate 14 is through fixing the hook plate roof beam 15 improvement intensity on the floor, and hook plate 14 and the combination of hook plate roof beam 15 form and launch the frame, and this embodiment is through setting up the ejection hook, can make unmanned aerial vehicle launch the transmission.

In order to facilitate positioning and ejection launching, the weight of the nose accounts for 30-40% of the total weight of the unmanned aerial vehicle, and the effect is optimal. In this embodiment, the arrangement of the airframe, the empennage, the side wings and the skin should conform to the aerodynamic principle, which is common knowledge and is not described again, and the utility model is just an improvement on the existing unmanned aerial vehicle on the basis of conforming to the aerodynamic principle.

The embodiment can be further modified as follows:

1) for further accurate positioning, as shown in fig. 3, the tail fin 7 is pivotally connected to the body (the first rib plates 9 extend from the cross beam 1 to the tail beam 12 and extend out of the tail beam 12, and the pivot shafts 21 are installed on the two first rib plates 9), a steering engine 16 is arranged on the first rib plates 9, a steering foot 19 is fixedly connected to the tail fin 7, and a rudder arm 17 is arranged on the steering engine 16 and connected to the steering foot 19 through a pull rod steel wire 18. When the unmanned aerial vehicle is used, the track of the unmanned aerial vehicle can be known according to monitoring or a camera and the like, the up-down turning amplitude of the tail wing is controlled through the steering engine during track yaw, so that the track is adjusted, and control signals can be manually sent to the steering engine through a remote controller and the like. The steering engine is an executing component for controlling the rotation of a control surface (control surface) of an airplane in an autopilot, and related documents can be referred to for the prior art, so that the details are not repeated.

2) In order to strengthen the strength of the skin fuselage, the skin adopts a thin-shell structure made of carbon fibers, the carbon fiber thin-shell structure can be completed through 3D printing, and the skin fuselage can bear multiple impacts and maintain the aerodynamic shape of the skin fuselage.

3) In order to further reduce the weight of the fuselage, lightening holes are formed in the main longitudinal beam, the cross beam, the tail beam and the rib plates, and the tail wing and the side wing are of hollow structures.

4) As shown in fig. 1, in order to further improve the power of the unmanned aerial vehicle, a motor 8 and a propeller driven by the motor 8 are arranged on the main longitudinal beam 2, and the propeller is only used for driving the unmanned aerial vehicle to advance, and is different from the propeller of the rotor unmanned aerial vehicle in nature.

5) As shown in fig. 4, the camera 5 is arranged on the machine head 4, so that the flight path can be observed more accurately through the camera 5, and more accurate control is facilitated.

The present invention is not limited to the specific technical solutions described in the above embodiments, and other embodiments may be made in the present invention in addition to the above embodiments. It will be understood by those skilled in the art that various changes, substitutions of equivalents, and alterations can be made without departing from the spirit and scope of the utility model.

Claims (7)

1. A micro fixed wing unmanned aerial vehicle comprises a machine head and a machine body, wherein the machine body is formed by splicing a main longitudinal beam, a cross beam arranged at the front end of the main longitudinal beam and a tail beam arranged at the rear end of the main longitudinal beam, and a skin covers the machine body; the method is characterized in that: taking the main longitudinal beam as a symmetry axis, and symmetrically arranging and fixedly connecting at least two pairs of rib plates on the cross beam, wherein the rib plate close to the main longitudinal beam is marked as a first rib plate, and the rib plate close to the end part of the cross beam is marked as a second rib plate;

the tail parts of the first rib plate and the second rib plate are fixedly connected with a tail beam, two horizontal tail wings are mounted at the tail part of the machine body, and the two horizontal tail wings are symmetrically arranged by taking the main longitudinal beam as a symmetry axis;

the second rib plates are provided with side wings, and the two side wings are also symmetrically arranged by taking the main longitudinal beam as a symmetry axis;

the machine head is arranged between the two first ribbed plates and is fixedly connected with the first ribbed plates;

the beam is provided with a hook plate, and the hook plate is provided with an ejection hook matched with the ejection launching device.

2. The micro fixed-wing drone of claim 1, wherein: the empennage with the organism pin joint, be equipped with the steering wheel on the first floor, the rigid coupling has the rudder foot on the empennage, the steering wheel passes through the pull rod steel wire and is connected with the rudder foot.

3. The micro fixed-wing drone of claim 1 or 2, wherein: the rib plates are arranged in parallel with the main longitudinal beam.

4. The micro fixed-wing drone of claim 1 or 2, wherein: the skin is of a thin shell structure made of carbon fibers.

5. The micro fixed-wing drone of claim 1 or 2, wherein: lightening holes are formed in the main longitudinal beam, the cross beam, the tail beam and the rib plate, and the tail wing and the side wing are of hollow structures.

6. The micro fixed-wing drone of claim 1 or 2, wherein: the head is provided with a camera.

7. The micro fixed-wing drone of claim 1 or 2, wherein: and the main longitudinal beam is provided with a motor and a propeller driven by the motor.

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