CN218022153U

CN218022153U - Unmanned plane

Info

Publication number: CN218022153U
Application number: CN202222523873.3U
Authority: CN
Inventors: 胡华智; 李海恩
Original assignee: Ehang Intelligent Equipment Guangzhou Co Ltd
Current assignee: Ehang Intelligent Equipment Guangzhou Co Ltd
Priority date: 2022-09-23
Filing date: 2022-09-23
Publication date: 2022-12-13
Anticipated expiration: 2032-09-23

Abstract

The utility model discloses an unmanned aerial vehicle, the top detachably of central wing box installs in the bottom of fuselage, and the cavity of acceping in the central wing box can load unmanned aerial vehicle's avionics equipment to central wing box and avionics equipment invade unmanned aerial vehicle's freight space, and based on this structure, unmanned aerial vehicle's storehouse can set up and be being close to the centrobaric position of fuselage more, and this has not only increased unmanned aerial vehicle's maximum load capacity, has still improved unmanned aerial vehicle's flight stability.

Description

Unmanned plane

Technical Field

The utility model relates to a fixed wing airborne vehicle technical field especially relates to an unmanned aerial vehicle.

Background

At present, a fixed-wing freight unmanned aerial vehicle in the market adopts an upper single-wing or middle single-wing configuration, wings of the unmanned aerial vehicle in the upper single-wing configuration are arranged at the top of a fuselage, a cargo bin of the unmanned aerial vehicle is usually arranged at the head or the tail of the fuselage, so that the actual loading capacity of cargoes has a large influence on the gravity center of the fuselage, and wings of the unmanned aerial vehicle in the middle single-wing configuration are arranged in the middle of the fuselage, namely a central wing box of the unmanned aerial vehicle encroaches on the inner space of the fuselage, so that the maximum loading capacity of the unmanned aerial vehicle is greatly influenced.

SUMMERY OF THE UTILITY MODEL

In order to overcome the not enough of prior art, the utility model aims to provide an unmanned aerial vehicle to solve current fixed wing unmanned aerial vehicle and influence maximum load capacity and the centrobaric problem of unmanned aerial vehicle because of wing layout design.

The purpose of the utility model is realized by adopting the following technical scheme:

an unmanned aerial vehicle comprising a fuselage and wings;

the wing comprises a central wing box and two outer wing boxes, the two outer wing boxes are respectively connected to two sides of the central wing box, and the top of the central wing box is detachably connected to the bottom of the fuselage;

the central wing box is internally provided with a containing cavity, and avionic equipment is arranged in the containing cavity.

In some optional embodiments, the top or the bottom of the central wing box is provided with an access opening communicated with the accommodating cavity, and the access opening is detachably covered with an access cover.

In some optional embodiments, a first data plug is arranged at the top of the central wing box, a second data plug is arranged at the bottom of the body, and the first data plug and the second data plug are connected.

In some optional embodiments, a heat dissipation port communicated with the accommodating cavity is formed in the top of the central wing box, a heat dissipation fan is arranged on the heat dissipation port, a first through hole communicated with the inner space of the body is formed in the bottom of the body, and the first through hole is opposite to the heat dissipation fan.

In some optional embodiments, the top of the central wing box is provided with an air inlet communicated with the accommodating cavity, the bottom of the fuselage is provided with a second through hole communicated with the inner space of the fuselage, and the second through hole and the air inlet are oppositely arranged and communicated.

In some optional embodiments, a filter screen is arranged on the air inlet hole.

In certain optional embodiments, the avionics equipment comprises a flight control system, an image transmission device or a signal receiving device.

In some optional embodiments, the aircraft further comprises a connecting piece, the bottom of the aircraft body is provided with a first connecting structure, the top of the central wing box is provided with a second connecting structure, and two ends of the connecting piece are respectively detachably connected to the first connecting structure and the second connecting structure.

In some optional embodiments, the wing further comprises a first spar, a second spar, a first rib and a second rib, the first spar and the second spar are arranged in parallel, the first rib and the second rib are arranged in parallel, two ends of the first rib are respectively connected to the middle of the first spar and the middle of the second spar, two ends of the second rib are respectively connected to the middle of the first spar and the middle of the second spar, the middle of the first rib, the second rib, the first spar and the middle of the second spar form the central box, one end of the first rib, the first spar and one end of the second spar form one of the outer boxes, and the other end of the second rib, the first spar and the other end of the second spar form the other outer box; the first wing rib is provided with a first connecting hole, and the second wing rib is provided with a second connecting hole.

In some optional embodiments, a positioning groove is formed in the top of the central wing box, and a positioning protrusion is arranged at the bottom of the fuselage, and is embedded in the positioning groove.

Compared with the prior art, the beneficial effects of the utility model reside in that:

the top detachably of central authorities 'wing box installs in the bottom of fuselage, and accommodating cavity in the central authorities' wing box can load unmanned aerial vehicle's avionics equipment to central authorities' wing box and avionics equipment encroach on unmanned aerial vehicle's freight transportation space, and based on this structure, unmanned aerial vehicle's storehouse can set up and be being close to the centrobaric position of fuselage more, and this has not only increased unmanned aerial vehicle's maximum loading capacity, has still improved unmanned aerial vehicle's flight stability.

Drawings

Fig. 1 is a schematic view of the overall structure of the utility model of the unmanned aerial vehicle;

fig. 2 is an exploded view of the wings and fuselage of the utility model of the unmanned aerial vehicle;

fig. 3 is an exploded schematic view of the central wing box of the utility model unmanned aerial vehicle;

fig. 4 is a schematic view of the bottom of the body of the utility model unmanned aerial vehicle;

fig. 5 is a schematic view of the internal structure of the wing of the unmanned aerial vehicle of the utility model;

FIG. 6 is an enlarged schematic view at A in FIG. 2;

in the figure: 10. a body; 11. a second data jack; 12. a first through hole; 13. a second through hole; 14. a first connecting structure; 15. positioning the bump; 20. a center wing box; 21. a housing cavity; 22. an access hole; 23. a first data jack; 24. a heat dissipation port; 25. a heat radiation fan; 26. an air inlet; 27. a filter screen; 28. a second connecting structure; 29. a positioning groove; 30. an outboard wing box; 40. an access cover; 50. a first spar; 60. a second spar; 70. a first rib; 71. a first connection hole; 80. a second rib; 81. And a second connection hole.

Detailed Description

In order to facilitate understanding of the present invention, the present invention will be described more fully hereinafter with reference to the accompanying drawings. Preferred embodiments of the present invention are shown in the drawings. The invention may, however, be embodied in many different forms and should not be construed as limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete.

It will be understood that when an element is referred to as being "secured to" another element, it can be directly on the other element or intervening elements may also be present. When an element is referred to as being "connected" to another element, it can be directly connected to the other element or intervening elements may also be present. The terms "vertical," "horizontal," "left," "right," and the like are used herein for purposes of illustration only.

Unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs. The terminology used in the description of the invention herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. As used herein, the term "and/or" includes any and all combinations of one or more of the associated listed items.

Referring to fig. 1 to 6, the unmanned aerial vehicle of the present invention is schematically shown, which includes a fuselage 10 and wings.

The wing comprises a central wing box 20 and two outer wing boxes 30, the number of the outer wing boxes 30 is two, and the two outer wing boxes 30 are respectively connected to two sides of the central wing box 20. The top of the central wing box 20 is detachably connected to the bottom of the fuselage 10 to constitute the lower monowing layout of the drone. The detachable wing design facilitates transportation of the drone, but also facilitates quick maintenance or replacement of the fuselage 10 or wings.

The central wing box 20 has a receiving cavity 21 therein, and an avionic device is arranged in the receiving cavity 21, and the avionic device includes but is not limited to a flight control system, an image transmission device and a signal receiving device, and of course, the avionic device may be one of the flight control system, the image transmission device or the signal receiving device. With avionics equipment setting in central wing box 20, can avoid avionics equipment to encroach on the freight transportation space of fuselage 10, and based on the single wing overall arrangement down for avionics equipment is closer to unmanned aerial vehicle's bottom, is favorable to reducing unmanned aerial vehicle's focus.

Referring to fig. 3 and 6, in the present embodiment, an access opening 22 communicating with the accommodating cavity 21 is formed at the top of the central wing box 20, an access cover 40 is detachably covered on the access opening 22, and the avionics equipment in the central wing box 20 can be accessed or maintained through the access opening 22 by uncovering the access cover 40. The access cover 40 may be hinged to one side of the access opening 22, or the access cover 40 may be detachably attached to the edge of the access opening 22 by a screw or bolt. In other alternative embodiments, the access opening 22 may also be provided at the bottom of the centre wing box 20.

Specifically, the top of central wing box 20 is equipped with foretell access hole 22, is equipped with first data bayonet joint 23 on the access cover 40, and the bottom of fuselage 10 is equipped with second data bayonet joint 11, and first data bayonet joint 23 is connected with second data bayonet joint 11, and first data bayonet joint 23 and second data bayonet joint 11 can be used to transmit unmanned aerial vehicle's control signal, sensing signal and electric energy. In this embodiment, a plurality of batteries of unmanned aerial vehicle set up both ends around fuselage 10 respectively, and the electric energy of battery can transmit flight control system, image transmission device and the signal receiving device in central wing box 20 through first data bayonet joint 23 and second data bayonet joint 11. Of course, the flight control system may also acquire the working state of the battery through the first data plug 23 and the second data plug 11, specifically, the battery is provided with a battery management system, and the flight control system acquires the battery working state parameters generated by the battery management system through the first data plug 23 and the second data plug 11.

The access cover 40 is further provided with a heat dissipation port 24 and an air inlet 26 which are both communicated with the accommodating cavity 21, the heat dissipation port 24 is provided with a heat dissipation fan 25, the bottom of the body 10 is provided with a first through hole 12 communicated with the internal space of the body, the first through hole 12 is arranged opposite to the heat dissipation fan 25, when the heat dissipation fan 25 operates, hot air in the accommodating cavity 21 of the central wing box 20 can be discharged into the body 10 through the heat dissipation port 24 and the first through hole 12, and the existing heat dissipation structure of the body 10 discharges the hot air in the body 10 out of the body 10. Furthermore, a second through hole 13 is formed in the bottom of the body 10 and is communicated with the internal space of the body, the second through hole 13 and the air inlet 26 are oppositely arranged and are communicated, and cold air in the body 10 can enter the accommodating cavity 21 of the central wing box 20 through the second through hole 13 and the air inlet 26 to cool the avionic device. In order to prevent dust from entering the receiving cavity 21 of the central wing box 20, a filter screen 27 is provided on the air inlet 26.

When the heat dissipation fan 25 is running, the heat dissipation fan 25 will generate negative pressure in the housing cavity 21 of the central wing box 20, and the negative pressure will force the cold air in the fuselage 10 to enter the housing cavity 21 of the central wing box 20 through the second through hole 13 and the air inlet 26.

The utility model discloses an unmanned aerial vehicle still includes the connecting piece, the bottom of fuselage 10 is equipped with first connection structure 14, and the top of central authorities' wing box 20 is equipped with second connection structure 28, and the both ends of connecting piece are detachably connected in first connection structure 14 and second connection structure 28 respectively, and wherein, first connection structure 14 is the through-hole, and second connection structure 28 is the screw, and the connecting piece is preferred to be the bolt, and the connecting piece passes first connection structure 14 and passes through screw thread fixed connection in second connection structure 28.

Referring to fig. 3 and 4, in order to realize the positioning of the wing and the fuselage 10, the top of the central wing box 20 is provided with four positioning grooves 29, the bottom of the fuselage 10 is provided with four positioning protrusions 15, and the positioning protrusions 15 are embedded in the positioning grooves 29, in this embodiment, the number of the positioning grooves 29 is four, the number of the positioning protrusions 15 is also four, and each positioning groove 29 corresponds to one positioning protrusion 15, so that the stable connection between the wing and the fuselage 10 is realized, and the abnormal swinging of the wing relative to the fuselage 10 is avoided.

As shown in fig. 5, the wing further includes a first wing beam 50, a second wing beam 60, a first rib 70 and a second rib 80, the first wing beam 50 and the second wing beam 60 are arranged in parallel, the first rib 70 and the second rib 80 are arranged in parallel, two ends of the first rib 70 are respectively connected to the middle of the first wing beam 50 and the middle of the second wing beam 60, and two ends of the second rib 80 are respectively connected to the middle of the first wing beam 50 and the middle of the second wing beam 60. The first rib 70, the second rib 80, the middle part of the first wing beam 50 and the middle part of the second wing beam 60 form a central wing box 20, one end of the first rib 70, the first wing beam 50 and one end of the second wing beam 60 form one of the outer wing boxes 30, the second rib 80, the other end of the first wing beam 50 and the other end of the second wing beam 60 form the other outer wing box 30, and it can be seen that the central wing box 20 and the two outer wing boxes 30 share the first wing beam 50 and the second wing beam 60, and the integrated structure can effectively improve the rigidity and the strength of the wing. The first connection hole 71 is formed in the first rib 70, the second connection hole 81 is formed in the second rib 80, and the first connection hole 71 and the second connection hole 81 can be used for lightening and communicating the inner spaces of the central wing box 20 and the outer wing box 30, so that the outer wing box 30 also has a condition for accommodating avionics equipment.

To sum up, the top detachably of central authorities 'wing box 20 installs in the bottom of fuselage 10, and the accommodating cavity 21 in the central authorities' wing box 20 can load unmanned aerial vehicle's avionics equipment to central authorities' wing box 20 and avionics equipment encroach unmanned aerial vehicle's freight transportation space, and based on this structure, unmanned aerial vehicle's storehouse can set up and be being close to the centrobaric position of fuselage 10 more, and this has not only increased unmanned aerial vehicle's maximum load capacity, has still improved unmanned aerial vehicle's flight stability.

The above only is the embodiment of the present invention, not limiting the patent scope of the present invention, all the equivalent structures or equivalent processes that are used in the specification and the attached drawings or directly or indirectly applied to other related technical fields are included in the patent protection scope of the present invention.

Claims

1. An unmanned aerial vehicle, comprising a fuselage and wings;

an accommodating cavity is formed in the central wing box, and avionic equipment is arranged in the accommodating cavity.

2. The unmanned aerial vehicle of claim 1, wherein the top or bottom of the central wing box is provided with an access opening communicated with the accommodating cavity, and an access cover is detachably covered on the access opening.

3. An unmanned aerial vehicle as defined in claim 1, wherein a first data plug is disposed at a top of the central wing box, and a second data plug is disposed at a bottom of the fuselage, and the first data plug and the second data plug are connected.

4. The unmanned aerial vehicle of claim 1, wherein a heat dissipation opening communicated with the accommodating cavity is formed in the top of the central wing box, a heat dissipation fan is arranged on the heat dissipation opening, a first through hole communicated with the inner space of the fuselage is formed in the bottom of the fuselage, and the first through hole is opposite to the heat dissipation fan.

5. The unmanned aerial vehicle of claim 1, wherein the top of the central wing box is provided with an air inlet communicated with the accommodating cavity, the bottom of the fuselage is provided with a second through hole communicated with the inner space of the fuselage, and the second through hole and the air inlet are oppositely arranged and communicated.

6. An unmanned aerial vehicle as claimed in claim 5, wherein the air inlet is provided with a filter screen.

7. The drone of claim 1, wherein the avionics equipment comprises a flight control system, an image transmission device, or a signal receiving device.

8. The unmanned aerial vehicle of claim 1, further comprising a connecting piece, wherein a first connecting structure is arranged at the bottom of the fuselage, a second connecting structure is arranged at the top of the central wing box, and two ends of the connecting piece are respectively detachably connected to the first connecting structure and the second connecting structure.

9. An unmanned aerial vehicle according to claim 1, wherein the wing further comprises a first spar, a second spar, a first rib and a second rib, the first spar and the second spar being arranged in parallel, the first rib and the second rib being arranged in parallel, the first rib being connected at each end to a central portion of the first spar and a central portion of the second spar, the second rib being connected at each end to a central portion of the first spar and a central portion of the second spar, the first rib, the second rib, the central portions of the first spar and the central portions of the second spar forming the central box, one of the ends of the first rib, the first spar and one of the ends of the second spar forming one of the outer side boxes, the other of the second rib, the first spar and the other of the ends of the second spar forming the other of the outer side boxes; the first wing rib is provided with a first connecting hole, and the second wing rib is provided with a second connecting hole.

10. The unmanned aerial vehicle of claim 1, wherein a positioning groove is formed in the top of the central wing box, and a positioning bump is arranged at the bottom of the fuselage and embedded in the positioning groove.