CN112478157B

CN112478157B - Freight unmanned aerial vehicle

Info

Publication number: CN112478157B
Application number: CN201910862629.XA
Authority: CN
Inventors: 郜奥林; 孙勇; 董文辉; 周维
Original assignee: Beijing Jingdong Century Trading Co Ltd; Beijing Jingdong Shangke Information Technology Co Ltd
Current assignee: Beijing Jingdong Century Trading Co Ltd; Beijing Jingdong Shangke Information Technology Co Ltd
Priority date: 2019-09-11
Filing date: 2019-09-11
Publication date: 2023-09-05
Anticipated expiration: 2039-09-11
Also published as: CN112478157A

Abstract

The present disclosure provides a cargo unmanned aerial vehicle, comprising: a body; a nose configured to be rotatable to one side with respect to the body, a cargo space of the body being communicated with the outside in a case where the nose turns to one side; and the wing comprises two front wings, the two front wings are respectively connected to two sides of the machine body, and the two front wings are positioned close to the nose.

Description

Freight unmanned aerial vehicle

Technical Field

The present disclosure relates to the field of logistics, and more particularly, to a cargo drone.

Background

With the development of science and technology, unmanned aerial vehicles are becoming more and more popular, and cargo unmanned aerial vehicles for cargo transportation play an important role in the field of logistics.

In the process of implementing the disclosed concept, the inventor finds that at least the following problems exist in the prior art:

in the prior art, the load-bearing gravity center of a freight aircraft is near a main wing, and goods are required to be placed near the load-bearing gravity center, if the goods are arranged at the front end of a fuselage, the front end has heavy weight, and the front end of the aircraft is easy to sink. Therefore, the cargo space available for the existing cargo aircraft is small, and the existing cargo unmanned aerial vehicle structure cannot conveniently load and unload large-sized cargo.

Disclosure of Invention

In view of this, the present disclosure provides a cargo unmanned aerial vehicle, comprising: a body; a nose configured to be rotatable to one side with respect to the body, a cargo space of the body being communicated with the outside in a case where the nose turns to one side; and the wing comprises two front wings, the two front wings are respectively connected to two sides of the machine body, and the two front wings are positioned close to the nose.

According to an embodiment of the present disclosure, the wing further comprises two main wings and an empennage; the two main wings are respectively arranged at two sides of the machine body, tail supports are arranged on the two main wings, and the tail supports extend to the rear of the machine body relative to the main wings; and the tail fin comprises a horizontal tail fin and two vertical tail fins, wherein the lower ends of the two vertical tail fins are respectively connected with a tail support positioned on the same side of the machine body, and the upper ends of the two vertical tail fins are connected with the horizontal tail fin.

According to an embodiment of the present disclosure, at least one of the front wing and the main wing is connected to an upper half of the fuselage.

According to an embodiment of the present disclosure, the front wing has a dihedral angle with respect to the main wing.

According to an embodiment of the present disclosure, the unmanned aerial vehicle further comprises a power device, wherein: the power device comprises an engine and a propeller; the power device is arranged at the tail part of the machine body and provides rear thrust for the unmanned aerial vehicle.

According to an embodiment of the disclosure, the fuselage comprises a straight section and a tapered section that tapers from a straight section cross section to a tail end face; the inner space of the straight section is the cargo space, and the gradually-retracted section is used for accommodating and installing the power device.

According to an embodiment of the present disclosure, the handpiece is configured to be capable of being turned up by a preset angle with respect to the fuselage; the preset angle is not smaller than 90 degrees.

According to an embodiment of the present disclosure, the handpiece has a closed state and an open state; in a closed state, the rear end of the machine head is attached to the front end of the machine body; in the open state, the rear end of the machine head is separated from the front end of the machine body, and the machine head is turned upwards by a preset angle relative to the machine body.

According to the embodiment of the disclosure, the top of the machine head is connected with the top of the machine body through a rotating shaft; a folding bracket is arranged on the machine head or the machine body; in the open state, the folding bracket is unfolded and supported between the nose and the body.

According to an embodiment of the disclosure, a first fixing piece is arranged at the bottom and/or the side part of the machine head, and a second fixing piece is arranged on the machine body at a position corresponding to the first fixing piece; in the closed state, the first fixing piece is locked with the second fixing piece.

According to the embodiment of the present disclosure, the problem that the cargo space available in the freight machine in the prior art is small and large-sized freight cannot be conveniently loaded and unloaded can be at least partially solved, and thus the technical effects of expanding the cargo space and conveniently and stably loading and unloading and transporting large-sized freight can be achieved.

Drawings

The above and other objects, features and advantages of the present disclosure will become more apparent from the following description of embodiments thereof with reference to the accompanying drawings in which:

fig. 1 schematically illustrates an exemplary application scenario of a cargo drone according to an embodiment of the present disclosure;

fig. 2A schematically illustrates a structural schematic of a cargo drone according to an embodiment of the present disclosure;

fig. 2B schematically illustrates a top view block diagram of a cargo drone according to an embodiment of the present disclosure;

fig. 2C schematically illustrates a right-view structural view of a cargo drone according to an embodiment of the present disclosure;

fig. 3A-3C schematically illustrate a schematic diagram of a nose rotation process of a cargo drone according to an embodiment of the present disclosure;

fig. 4 schematically illustrates a loading and unloading schematic of a cargo drone according to an embodiment of the present disclosure;

fig. 5 schematically illustrates a structural schematic of a cargo drone according to another embodiment of the present disclosure;

fig. 6 schematically illustrates a front view structural schematic of a cargo drone according to another embodiment of the present disclosure; and

fig. 7 schematically illustrates a right-view structural schematic of a cargo drone according to another embodiment of the present disclosure.

Detailed Description

Hereinafter, embodiments of the present disclosure will be described with reference to the accompanying drawings. It should be understood that the description is only exemplary and is not intended to limit the scope of the present disclosure. In the following detailed description, for purposes of explanation, numerous specific details are set forth in order to provide a thorough understanding of the embodiments of the present disclosure. It may be evident, however, that one or more embodiments may be practiced without these specific details. In addition, in the following description, descriptions of well-known structures and techniques are omitted so as not to unnecessarily obscure the concepts of the present disclosure.

The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the disclosure. The terms "comprises," "comprising," and the like, as used herein, specify the presence of stated features, operations, and/or components, but do not preclude the presence or addition of one or more other features, operations, or components.

All terms (including technical and scientific terms) used herein have the same meaning as commonly understood by one of ordinary skill in the art unless otherwise defined. It should be noted that the terms used herein should be construed to have meanings consistent with the context of the present specification and should not be construed in an idealized or overly formal manner.

Where expressions like at least one of "A, B and C, etc. are used, the expressions should generally be interpreted in accordance with the meaning as commonly understood by those skilled in the art (e.g.," means having at least one of A, B and C "shall include, but not be limited to, means having a alone, B alone, C alone, a and B together, a and C together, B and C together, and/or A, B, C together, etc.). Where a convention analogous to "at least one of A, B or C, etc." is used, in general such a convention should be used in the sense one having skill in the art would understand the convention (e.g., "a device having at least one of A, B or C" would include but not be limited to devices having a alone, B alone, C alone, a and B together, a and C together, B and C together, and/or A, B, C together, etc.).

It should also be appreciated by those skilled in the art that virtually any disjunctive word and/or phrase presenting two or more alternative items, whether in the description, claims, or drawings, should be understood to contemplate the possibilities of including one of the items, either of the items, or both. For example, the phrase "a or B" should be understood to include the possibility of "a" or "B", or "a and B".

Embodiments of the present disclosure provide a cargo drone including a fuselage, a nose, and wings. The nose is configured to be rotatable to one side with respect to the body, and in a case where the nose turns to one side, a cargo space of the body communicates with the outside. The wing comprises two front wings which are respectively connected to two sides of the machine body, and the two front wings are positioned close to the machine head.

According to the embodiment of the disclosure, the front wing is arranged on the freight unmanned aerial vehicle, the pneumatic focus of the whole aircraft is moved forward by the added front wing, and then the bearing gravity center range of the whole aircraft is also moved forward to provide lifting force for the front side of the unmanned aerial vehicle, so that the cargo space can be expanded to the vicinity of a nose in front, and then the nose is opened, so that large-scale cargoes can be conveniently and stably loaded and unloaded.

Fig. 1 schematically illustrates an exemplary application scenario of a cargo drone according to an embodiment of the present disclosure. It should be noted that fig. 1 illustrates only an example of an application scenario in which the embodiments of the present disclosure may be applied to help those skilled in the art understand the technical content of the present disclosure, but it does not mean that the embodiments of the present disclosure may not be applied to other devices, systems, environments, or scenarios.

As shown in fig. 1, the cargo drone 110 of the disclosed embodiments may be used for spur transportation, which complements the transportation between the trunk and the ship-receiving location, with the capacity between the large transporter 120 and the rotary unmanned aerial vehicle 130, primarily assuming the transportation tasks from suppliers to collection points on the trunk and from collection points on the trunk to distribution stations in the transportation supply chain. The cargo unmanned aerial vehicle 110 can transport cargoes with the weight of more than two hundred kilograms, and is flexible in lifting and good in economy.

In the process of delivering the goods, the large-scale transporter 120 may be used for transporting the goods from the suppliers to the collection points on the trunk, then the freight unmanned aerial vehicle 110 is used for transporting the goods from the collection points on the trunk to the delivery station, and then the rotary unmanned aerial vehicle 130 is used for transporting the goods from the delivery station to the receiving location.

It will be appreciated that the application scenario in fig. 1 is only an example, and that the cargo drone may be used in other transportation scenarios in addition to being applied to spur transportation.

Fig. 2A schematically illustrates a structural schematic of a cargo drone 200 according to an embodiment of the present disclosure.

Fig. 2B schematically illustrates a top view block diagram of a cargo drone 200 according to an embodiment of the present disclosure.

Fig. 2C schematically illustrates a right-view block diagram of the cargo drone 200 according to an embodiment of the present disclosure.

As shown in fig. 2A to 2C, a cargo unmanned aerial vehicle 200 of the embodiment of the present disclosure includes:

a body 210;

a head 220 configured to be rotatable to one side with respect to the body 210, and a cargo space of the body 210 communicates with the outside in a case where the head 220 turns to one side; and

the wing includes two front wings 231, the two front wings 231 are respectively connected to two sides of the fuselage 210, and the two front wings 231 are positioned near the nose 210.

In particular, the cargo unmanned aerial vehicle 200 of the disclosed embodiments may be a fixed wing unmanned aerial vehicle.

The wing 230 further includes two main wings 232 and an empennage 233, the two main wings are respectively disposed at two sides of the fuselage 210, and the two front wings 231 are disposed in front of the two main wings 232, that is, the two front wings 231 are closer to the nose 220 than the two main wings 232, and the two front wings 231 can provide positive lift for the cargo unmanned aerial vehicle 200.

The existing fixed wing unmanned aerial vehicle is only provided with a pair of main wings and a normal tail wing, the main wings are in front, the tail wing is behind, the main wings of the unmanned aerial vehicle provide main lifting force, and the tail wing is at the tail part of the unmanned aerial vehicle body and mainly used for unmanned aerial vehicle leveling and attitude control, and corresponding balancing resistance can be generated. In the fixed wing unmanned aerial vehicle with the layout, the bearing gravity center is near the main wing, when goods are loaded, the goods are required to be loaded near the main wing of the unmanned aerial vehicle, the cargo space of the freight unmanned aerial vehicle with the layout is small, and if the goods are loaded at the front end of the body, the front end weight is heavy, so that the front end of the unmanned aerial vehicle is easy to sink due to insufficient lifting force.

After the front wing 231 is arranged on the freight unmanned aerial vehicle 200, positive lifting force can be provided for the front end of the unmanned aerial vehicle, the added front wing 231 enables the pneumatic focus of the whole unmanned aerial vehicle to move forward, and further the bearing gravity center range of the whole unmanned aerial vehicle can also move forward, so that the cargo space can be expanded to the vicinity of a nose in front, and the cargo space is greatly expanded.

A front wing is added near the nose to form a three-wing surface layout, the front wing changes the trimming condition of the whole unmanned aerial vehicle, and the stall prevention function is added for the unmanned aerial vehicle. The stall phenomenon generally occurs when unmanned aerial vehicle flies at a large attack angle, and as the unmanned aerial vehicle flies at an excessive attack angle, the resistance of the unmanned aerial vehicle is too large, and then the unmanned aerial vehicle is decelerated to a position where the flying height cannot be maintained, so that the lift force at the corresponding position is suddenly reduced or even disappears, the stall-most place of the unmanned aerial vehicle with the conventional layout is a main wing, the main wing is used as the most important part for generating the lift force, once the unmanned aerial vehicle stalls, danger can occur, the unmanned aerial vehicle is not easy to recover during non-human intervention, and the flying of the unmanned aerial vehicle under a severe environment is not facilitated. For the cargo unmanned aerial vehicle 200 of the embodiment of the present disclosure, the front wing 231 may generate vortex above the main wing 232 when flying at a large angle of attack, increasing the stall angle of attack. Therefore, the cargo unmanned aerial vehicle 200 of the embodiment of the disclosure can still maintain better flight control under severe conditions, so that the application scene of the cargo unmanned aerial vehicle is expanded, and the attendance rate is improved.

In the case where the front wing 231 expands the cargo space of the cargo drone to the front end of the fuselage, if the side of the fuselage 210 is provided with the door, it is inconvenient to load cargo into the cargo space near the nose 220 through the side door, and the cargo space on the front side of the cargo drone cannot be utilized well. And for larger cargoes, the loading and unloading are not easy.

Thus, the nose 220 of the embodiment of the present disclosure is provided in an openable form, and the cargo space is opened from the front side by opening the nose 220 on the basis that the front wing 231 expands the cargo space at the front side, so that cargo can be loaded and unloaded from the front end of the fuselage 210, and cargo can be stacked at the front end portion of the cargo space, making full use of the cargo space expanded by the front wing 231. The cabin door is opened at the machine head position, so that a cargo loading and unloading path is more reasonable, the unmanned aerial vehicle can conveniently and rapidly load and unload cargoes, the cargo loading and unloading speed is improved, and the operation efficiency is improved. And, the size of the handpiece 220 is large, and the opening of the fuselage 210 is large after the handpiece 220 is opened, so that the whole entry and exit of large goods are facilitated. After loading, under the condition that the cargo is loaded on the front side of the cargo hold, the front wing 231 can be utilized to provide lifting force for the front side of the aircraft body in the flying process of the freight unmanned aerial vehicle, so that the front end of the freight unmanned aerial vehicle is prevented from sinking due to overweight and insufficient lifting force, and the flying process is safer and more flexible. Thus, in the disclosed embodiments, the openable arrangement of the nose and the arrangement of the front wing mounted near the nose complement each other, which together achieve the technical effects of expanding cargo space, rapidly loading and unloading, and improving flight safety.

Fig. 3A-3C schematically illustrate a schematic view of a nose 320 rotation process of a cargo unmanned aerial vehicle 300 according to an embodiment of the present disclosure.

As shown in fig. 3A to 3C, according to an embodiment of the present disclosure, the handpiece 320 is configured to be capable of being turned upward relative to the body 310 by a preset angle, which is not less than 90 degrees.

Specifically, the handpiece 320 is configured to be flipped up with respect to the body 310, and is simple in structure and convenient in operation, and in other embodiments of the present disclosure, the handpiece 320 may be flipped left or right with respect to the body 310.

If the flip angle of the nose 320 is not less than 90 degrees, the cargo opening of the body 310 cannot be completely smoothly communicated with the external environment in the case that the nose 320 is opened, and cargo may interfere with the nose 320 when loading and unloading. In the disclosed embodiment, the predetermined angle may be 110 degrees, and the nose 320 may be opened to provide a cargo space environment for loading and unloading.

Handpiece 320 can be maintained in a closed state and an open state in accordance with embodiments of the present disclosure.

In the state shown in fig. 3A, the nose 320 is in a closed state, the rear end surface of the nose 320 is attached to the front end surface of the body 310, and the cargo space of the body 310 is closed.

According to an embodiment of the present disclosure, as shown in fig. 3C, a first fixing member 341 may be provided at a bottom and/or side of the handpiece 320, and a second fixing member 342 may be provided at a position on the body 310 with respect to the first fixing member 341, and in a closed state, the first fixing member 341 and the second fixing member 342 may be capable of locking the handpiece 320 and the body 310.

For example, the first fixing member 341 and the second fixing member 342 may be connection holes, and the two connection holes may be connected by using a connection member, so as to realize locking of the handpiece 320 and the body 310, and the connection member may be a fastener such as a bolt; alternatively, the first fixing element 341 may be a clamping block disposed on the rear end face of the nose 320, and the second fixing element 342 may be a clamping groove disposed on the front end face of the body 310, where the clamping block may be clamped into the clamping groove when the nose 320 is closed, so as to lock the nose 320 and the body 310; alternatively, the first and second fixing members 341 and 342 may be coupled together by a locking manner.

According to embodiments of the present disclosure, a sensor may be further disposed on a front end surface of the body 310 and/or a rear end surface of the nose 320 to sense whether the front end surface of the body 310 and the rear end surface of the nose 320 are pressed, and during flight, if the sensor senses that the nose is loose, an operator may take corresponding emergency measures.

In the state shown in fig. 3C, the nose 320 is in an opened state, the rear end surface of the nose 320 is separated from the front end surface of the body 310, and the nose 320 is turned upward by a preset angle with respect to the body 310.

According to an embodiment of the present disclosure, the top of the handpiece 320 is coupled to the top of the body 310 through a rotation shaft so that the handpiece 320 can be rotated upward with respect to the body 310 through the rotation shaft.

As shown in fig. 3C, a folding bracket 350 is provided on the handpiece 320 or the body 310, and in an opened state, the folding bracket 350 is unfolded and supported between the handpiece 310 and the body 320.

The head 320 may be opened by a person, for example, after unlocking the fixing members of the head 320 and the body 310, a worker rotates the head 320 to a limit position by a person, and then opens the folding frame 350 such that both ends of the folding frame 350 are supported on the head 320 and the body 310, respectively, to maintain the head 320 in an opened state.

In other embodiments of the present disclosure, the nose 320 may be opened automatically, for example, an automatic expansion bracket may be disposed on the body 310, one end of the automatic expansion bracket is connected to the body 310, in a state that the nose is closed, the automatic expansion bracket is in a retracted state, when the nose 320 needs to be opened, the automatic expansion bracket is controlled to extend, the other end of the automatic expansion bracket abuts against the nose 320, and the nose 320 is pushed away from the body 310, with the increase of the length of the automatic expansion bracket, the nose 320 increases the rotation angle along with the increase of the length of the automatic expansion bracket until the nose rotates to a limit angle, and the automatic expansion bracket stops extending and is supported between the nose 320 and the body 310, so that the nose 320 is kept in the opened state.

In a state where the head 320 is opened, loading and unloading of cargo can be performed.

Fig. 4 schematically illustrates a loading and unloading schematic of a cargo drone 400 according to an embodiment of the present disclosure.

As shown in fig. 4, the loading and unloading platform 450 can be used for loading and unloading cargoes of the cargo unmanned plane 400, and after the machine head is opened upwards, cargoes can be integrally moved in and out of the opening of the machine body without any obstacle. With the cooperation of an automatic assembly line, after the cargo unmanned aerial vehicle 400 is stopped at one side of the cargo loading platform 450, the machine head is opened, the cargo loading platform 450 and the cargo unmanned aerial vehicle 400 are connected together, and then cargoes can automatically enter and exit from the cargo loading platform 450.

In other embodiments of the present disclosure, an own dock may also be provided on the cargo drone 400. When the machine head is closed, the self-contained loading platform is positioned in the cargo space, after the machine head is opened, the self-contained loading platform moves forwards under the action of external force, one part of the self-contained loading platform extends out of the cargo space, a bracket is arranged at the bottom of the loading platform, after the loading platform extends out of the cargo space, the bracket is lowered, the loading platform is supported on the ground by the bracket, and cargo loading and unloading can be carried out through the loading platform.

Fig. 5 schematically illustrates a structural schematic of a cargo drone 500 according to an embodiment of the present disclosure.

As shown in fig. 5, according to an embodiment of the present disclosure, the main wing includes two main wings 5321 and 5322 provided at both sides of the fuselage, on which tail struts 5323 and 5324 are provided, respectively, the tail struts 5323 extending rearward of the fuselage with respect to the main wing 5321, and likewise the tail struts 5324 extending rearward of the fuselage with respect to the main wing 5322.

The tail includes a horizontal tail 5331 and two vertical tails 5332 and 5333, the lower end of the vertical tail 5332 is connected to a tail boom 5323 located on the same side of the fuselage, and the lower end of the vertical tail 5333 is connected to a tail boom 5324 located on the same side of the fuselage. The upper ends of the two vertical tails 5332 and 5333 are connected to the horizontal tail 5331.

According to an embodiment of the present disclosure, the cargo drone 500 also includes a power plant. Wherein:

the power device comprises an engine and a propeller 560, and is arranged at the tail of the machine body to provide rear thrust for the unmanned aerial vehicle. The cargo drone 500 may be a single-shot drone, including an engine and a propeller 560.

Conventional single-shot screw unmanned aerial vehicle adopts the pull-forward screw as main pull-in part, and engine and screw are installed at unmanned aerial vehicle's head, and the high-speed air current of front pull-forward screw will be mostly blown to unmanned aerial vehicle fuselage and wing on, and the heliciform high-speed air current has caused additional resistance to unmanned aerial vehicle fuselage to improve unmanned aerial vehicle's flight energy consumption to the additional lateral force that the air current produced on blowing the fuselage also has caused extra burden for unmanned aerial vehicle's flight manipulation. In addition, since the nose space is occupied by the engine and the tail space is occupied by the tail wing, the cargo space is narrowed.

Engines and propellers 560 in embodiments of the present disclosure are disposed at the tail of the fuselage, minimizing the air flow interference of the unmanned aerial vehicle engines and propellers to the unmanned aerial vehicle body.

The cargo unmanned aerial vehicle 500 of the embodiment of the disclosure adopts a rear propulsion engine, and the tail wing uses the double vertical tails arranged on the tail boom, so that the arrangement avoids the air flow of the propeller from blowing to the surface of the tail wing body, also prevents other bodies from being disturbed by the air flow, and reduces the resistance coefficient of the whole unmanned aerial vehicle and the flight energy consumption. In addition, the rear position of the engine and the screw propeller can give off the space near the machine head, enlarge the space of the cargo hold and facilitate the front side opening.

Fig. 6 schematically illustrates a front view schematic of a cargo drone 600 according to an embodiment of the present disclosure.

As shown in fig. 6, at least one of the front wing 631 and the main wing 632 is connected to the upper half of the fuselage according to an embodiment of the present disclosure.

The front wing 631 and the main wing 632 are both upper single wings, namely, are both single auxiliary wings positioned at the top of the main body, and the main wing 632 moves upwards to the upper half part of the main body, so that the tail stay arranged on the main wing 632 can be prevented from wiping the ground during take-off. When the front wing 631 is positioned downward, the front wing 631 needs to be installed at a relatively forward position, which causes interference between the front wing 631 and the nose, so that the front wing 631 moves upward to the upper half of the fuselage to prevent the nose from interfering with the front wing 631.

According to embodiments of the present disclosure, the front wing 631 has a dihedral angle relative to the main wing 632, i.e., the front wing 631 is tilted downward relative to the main wing 632 such that the airflow passing through the front wing 631 is offset from the main wing 632, which may reduce aerodynamic interference of the front wing 631 with the main wing 632. The dihedral angle may be, for example, 5 degrees.

Fig. 7 schematically illustrates a right-hand schematic view of a cargo drone 700 according to an embodiment of the present disclosure.

As shown in fig. 7, according to an embodiment of the present disclosure, the fuselage includes a straight section 711 and a tapered section 712, the tapered section 712 being connected to the rear of the straight section 711, the tapered section 712 transitioning from the cross section of the straight section 711 to the tail end face.

Specifically, the cross-sectional dimensions of the respective portions of the straight section 711 are not greatly different, and the cross-sectional dimensions may be, for example, 1.5m in width and 1.5m in height. The distance from the nose front end to the tail end face of the tapered section 712 may be, for example, 6m.

The inner space of the straight section 711 is cargo space for accommodating cargo. The tapered section 712 is used for accommodating and mounting a power device, and the engine is disposed in an inner space of the tapered section 712, and extends the output shaft through the tail end face, and the propeller is disposed on the tail end face and connected to the output shaft of the engine.

Those skilled in the art will appreciate that the features recited in the various embodiments of the disclosure and/or in the claims may be combined in various combinations and/or combinations, even if such combinations or combinations are not explicitly recited in the disclosure. In particular, the features recited in the various embodiments of the present disclosure and/or the claims may be variously combined and/or combined without departing from the spirit and teachings of the present disclosure. All such combinations and/or combinations fall within the scope of the present disclosure.

The embodiments of the present disclosure are described above. However, these examples are for illustrative purposes only and are not intended to limit the scope of the present disclosure. Although the embodiments are described above separately, this does not mean that the measures in the embodiments cannot be used advantageously in combination. The scope of the disclosure is defined by the appended claims and equivalents thereof. Various alternatives and modifications can be made by those skilled in the art without departing from the scope of the disclosure, and such alternatives and modifications are intended to fall within the scope of the disclosure.

Claims

1. A cargo drone, comprising:

a body;

a nose configured to be rotatable to one side with respect to the body, a cargo space of the body being communicated with the outside in a case where the nose turns to one side; and

the wing comprises two front wings and two main wings, wherein the two main wings are respectively arranged on two sides of the machine body, the two front wings are respectively connected to two sides of the machine body, the positions of the two front wings are close to the machine head, the main wings and the front wings are both upper single wings, and the front wings have lower dihedral angles relative to the main wings.

2. The unmanned aerial vehicle of claim 1, wherein:

the wing also comprises two tail wings;

tail struts are arranged on the two main wings, and extend to the rear of the machine body relative to the main wings; and

the tail wing comprises a horizontal tail wing and two vertical tail wings, wherein the lower ends of the two vertical tail wings are respectively connected with a tail support positioned on the same side of the machine body, and the upper ends of the two vertical tail wings are connected with the horizontal tail wing.

3. The drone of claim 2, wherein:

at least one of the front wing and the main wing is connected to an upper half of the fuselage.

4. The unmanned aerial vehicle of claim 1, further comprising a power device, wherein:

the power device comprises an engine and a propeller;

the power device is arranged at the tail part of the machine body and provides rear thrust for the unmanned aerial vehicle.

5. The drone of claim 4, wherein:

the machine body comprises a straight section and a gradually-shrinking section, and the gradually-shrinking section gradually-shrinking transition from the section of the straight section to the end face of the tail;

the inner space of the straight section is the cargo space, and the gradually-retracted section is used for accommodating and installing the power device.

6. The unmanned aerial vehicle of claim 1, wherein:

the handpiece is configured to be capable of being folded upwardly relative to the fuselage by a preset angle;

the preset angle is not smaller than 90 degrees.

7. The unmanned aerial vehicle of claim 6, wherein:

the handpiece has a closed state and an open state;

in a closed state, the rear end of the machine head is attached to the front end of the machine body;

in the open state, the rear end of the machine head is separated from the front end of the machine body, and the machine head is turned upwards by a preset angle relative to the machine body.

8. The drone of claim 7, wherein:

the top of the machine head is connected with the top of the machine body through a rotating shaft;

a folding bracket is arranged on the machine head or the machine body;

in the open state, the folding bracket is unfolded and supported between the nose and the body.

9. The drone of claim 7, wherein:

the bottom and/or the side part of the machine head are/is provided with a first fixing piece, and the position on the machine body corresponding to the first fixing piece is provided with a second fixing piece;

in the closed state, the first fixing piece is locked with the second fixing piece.