WO2018103457A1

WO2018103457A1 - Unmanned aerial vehicle

Info

Publication number: WO2018103457A1
Application number: PCT/CN2017/106338
Authority: WO
Inventors: 郑毅; 刘城斌
Original assignee: 北京京东尚科信息技术有限公司; 北京京东世纪贸易有限公司
Priority date: 2016-12-09
Filing date: 2017-10-16
Publication date: 2018-06-14
Also published as: CN108609165A

Abstract

An unmanned aerial vehicle (100) comprises a vehicle body (2), an arm component (4), and rotor mechanisms (6). The arm component is connected to the vehicle body. The rotor mechanisms are arranged via the arm component at the periphery of the vehicle body. The arm component comprises: main arms (41) installed at the vehicle body; two or more carrier arms (42) carrying the rotor mechanisms and protruding along a length direction of the vehicle body and arranged in parallel to each other; and connection arms (44) connecting the main arms and the carrier arms. Each of the connection arms has one end connected to the main arm, and the other end connected to the carrier arm. The connection arm and the main arm protrude along the same direction and have a protrusion direction in perpendicular to that of the carrier arm. The unmanned aerial vehicle is compact in size, facilitating storage, transport, and carrying.

Description

Drone

Technical field

Embodiments of the present invention relate to the field of aircraft technologies, and in particular, to a drone.

Background technique

With the rise in labor costs and the increasing traffic congestion, many courier companies or e-commerce companies are beginning to try to use drones for delivery.

The drone generally includes a body, a arm mounted on the body, and a power mechanism disposed on the arm. Limited by the design and layout of the fuselage, arm and power mechanism, the traditional UAV's own weight is generally large, and the internal space of the UAV is also not conducive to loading large cargo, so the traditional no Man-machines have the drawback of having a small payload and only loading smaller items.

In addition, the conventional drone is not in the working state of the flight or in the idle non-working state, and the mounting position of the arm and the power mechanism relative to the body is not changed due to the change of the working state thereof. The change occurs, so that the drones are all in an extended state, occupying a large space, which is disadvantageous for the storage, transportation and carrying of the drone.

Summary of the invention

In order to solve at least one of the above problems or drawbacks, the present invention proposes a drone.

According to an aspect of the invention, there is provided a drone comprising a fuselage, an arm assembly and a rotor mechanism, the arm assembly being coupled to the fuselage, the rotor mechanism being distributed by the arm assembly Around the fuselage, wherein the arm assembly comprises:

a main arm mounted on the fuselage;

At least two carrying arms on which the rotor mechanisms are carried, each of the carrying arms extending parallel to each other along the length of the fuselage; and

a connecting arm for connecting the main arm and the carrying arm, one end of the connecting arm is connected to the main arm, and the other end of the connecting arm is connected to the carrying arm, the connecting arm and the connecting arm The main arms extend in the same direction, and the extending direction of the connecting arm and the main arm is perpendicular to the extending direction of the carrying arm.

According to some embodiments, the drone includes a plurality of rotor mechanisms, the at least two carrying arms extending parallel to each other are located in the same carrying plane, and a portion of the plurality of rotor mechanisms are disposed above the carrying plane Another portion of the plurality of rotor mechanisms is disposed below the load bearing plane.

According to some embodiments, one end of the connecting arm is connected to the main arm through a first connecting mechanism, the first connection The mechanism has a pivot having an axial direction parallel to a length direction of the fuselage, the first coupling mechanism being configured such that the connecting arm is rotatable relative to the main arm about the pivot .

According to some embodiments, the drone further includes a cargo bin that is mounted to the fuselage by a detachable connection structure.

According to some embodiments, the drone includes two of the carrying arms, one of the carrying arms being located on one side of the fuselage, and the other of the carrying arms being located on the opposite side of the fuselage, and Three of the rotor mechanisms are carried on each of the carrying arms.

According to some embodiments, a rotor mechanism is carried at each of the two ends of each of the carrying arms and at an intermediate position between the ends.

According to some embodiments, the rotor mechanism at the end of the carrying arm is disposed below the carrying plane, the rotor mechanism located at an intermediate position between the ends of the carrying arm is disposed at Above the carrying plane.

According to some embodiments, each of the rotor mechanisms includes a propeller, and an area swept by the propeller above the load-bearing plane and swept by a propeller located below the load-bearing plane during the rotation is at the load There is overlap in the projections in the plane.

According to some embodiments, the first connection mechanism further includes a fixing member for fixedly connecting the connecting arm and the main arm to set the drone to an operating state.

According to some embodiments, the first connection mechanism is configured such that the connecting arm is rotatable about the pivot relative to the main arm toward the body by about 90° to set the drone to Non-working status.

According to some embodiments, the first connection mechanism further includes:

a main arm connecting seat connected to the main arm, the main arm connecting seat having a plurality of main arm flange portions disposed opposite to each other in a radial direction thereof, each of the main arm flange portions Each has a main arm mounting wall, and each of the main arm mounting walls is formed with a main arm through hole, and an extending direction of the main arm through hole is parallel to an axial direction of the pivot; and

a connecting arm connecting seat, the connecting arm connecting seat being connected to the connecting arm, the connecting arm connecting seat having a connecting arm flange portion disposed opposite to each other in a radial direction thereof, each of the connecting arm flange portions having The connecting arm mounting wall is formed with a connecting arm through hole in each of the connecting arm mounting walls, and the connecting arm through hole extends in a direction parallel to an axial direction of the pivot.

According to some embodiments, the outer casing of the cargo compartment mates with the outer casing of the fuselage such that when the cargo bin is mounted on the fuselage, the fuselage and the cargo compartment form an integral component .

According to some embodiments, the outer casing of the integral component consisting of the fuselage and the cargo bin is streamlined.

According to some embodiments, the detachable connection structure includes a plurality of hooks disposed on the body and a plurality of hook points disposed in the magazine, the hooks being engageable with the hook points to The warehouse is mounted to the fuselage; or By

The detachable connection structure includes a plurality of hooks disposed on the cargo compartment and a plurality of hook points disposed in the fuselage, the hooks being engageable with the hook points to mount the cargo bin To the fuselage.

The drone according to the embodiment of the present invention arranges the rotor mechanism on both sides of the fuselage through a substantially "H"-shaped arrangement of the arm assembly, and can effectively reduce the weight of the drone itself and improve the overall structure through a reasonable layout. rigidity. Moreover, the carrying arm and the rotor mechanism carried thereby can be folded toward the inside of the fuselage, so that the volume of the drone when it is in an inoperative state can be reduced. In addition, the flexibility of the drone can be provided by connecting the fuselage and the warehouse with a detachable structure.

DRAWINGS

In order to make the objects, the technical solutions and the advantages of the present invention more comprehensible, the present invention will be further described in detail below with reference to the accompanying drawings.

1 is a perspective view of a drone according to an embodiment of the present invention;

2 is a top plan view of a drone according to an embodiment of the present invention;

3 is a front elevational view of a drone according to an embodiment of the present invention;

4 is a perspective view showing a region swept by a propeller of a rotor mechanism of a drone according to an embodiment of the present invention;

5 is a top plan view showing a region swept by a propeller of a rotor mechanism of a drone according to an embodiment of the present invention;

6 is an enlarged view of a connection mechanism for connecting a main arm and a connecting arm in a drone according to an embodiment of the present invention, wherein the connecting mechanism is in a first state;

7 is an enlarged view of a connection mechanism for connecting a main arm and a connecting arm in a drone according to an embodiment of the present invention, wherein the connecting mechanism is in a second state;

Figure 8 is a view schematically showing a state in which both the carrying arms on both sides and the rotor mechanisms carried thereon are folded;

Figure 9 is a perspective view schematically showing a state in which both the carrying arms on both sides and the wing mechanisms carried thereon are folded;

Figure 10 is a perspective view of a delivery drone according to an embodiment of the present invention;

Figure 11 is a perspective view of a delivery drone according to an embodiment of the present invention, wherein the warehouse is removed from the fuselage;

Figure 12 is a partial enlarged view of a connection structure for installing a cargo bin of a delivery drone according to an embodiment of the present invention; and

Figure 13 is a perspective schematic view of a cargo bin of a delivery drone in accordance with an embodiment of the present invention, schematically showing a portion of a connection structure for mounting a cargo bin.

detailed description

The technical solutions of the present invention will be further specifically described below by way of embodiments and with reference to the accompanying drawings. In the description, the same or similar reference numerals indicate the same or similar parts. The description of the embodiments of the present invention with reference to the accompanying drawings is intended to illustrate the general inventive concept of the invention, and should not be construed as a limitation of the invention.

It should be noted that when a component is referred to as being "fixed" to another component, it can be directly on the other component or the component can be present. When a component is considered to "connect" another component, it can be directly connected to another component or possibly a central component. When a component is considered to be "set to" another component, it can be placed directly on another component or possibly with a centered component.

In this paper, for convenience of description, the heading axis of the drone is marked as the X axis, the pitch axis is marked as the Y axis, the roll axis is marked as the Z axis, and the Z axis direction indicates the direction parallel to the axis of the drone, X The axis direction represents a direction perpendicular to the Z-axis direction and located within the plane of symmetry of the drone, and the Y-axis direction represents a direction perpendicular to a plane composed of the X-axis and the Z-axis. Also, the directional terms "vertical", "horizontal", "upper", "lower", "left", "right", and the like are used herein. However, the description or the description is only for the purpose of convenience of description, and is not to be construed as limiting the invention.

Hereinafter, a drone according to an embodiment of the present invention will be described by taking a rotor type drone as an example.

Referring also to Figures 1 through 3, the rotary wing drone 100 can fly and hover in the air to perform specific tasks such as flight, tracking, surveillance, delivery, exploration, search and rescue, seeding, spraying pesticides, fire fighting, Aerial photography, etc. A predetermined function module, such as a sensor, a photographing device, a warehouse, or the like, can be mounted on the drone 100 to achieve a specific function.

According to an embodiment of the invention, the drone 100 includes a fuselage 2, a boom assembly 4, and a rotor mechanism 6. The arm assembly 4 is coupled to the fuselage 2, and the rotor mechanism 6 is distributed around the fuselage 2 by the arm assembly 4.

In the illustrated embodiment, the drone 100 is a six-rotor unmanned aerial vehicle, i.e., the number of the rotor mechanisms 6 is six. The six rotor mechanisms 6 are distributed in a rectangular area around the fuselage 2, and wherein four rotor mechanisms 6 are respectively located at one vertex of the rectangle, and the other two rotor mechanisms 6 are respectively located on the long sides of the rectangle, for example, Located at the midpoint of the long side of the rectangle. According to the aerodynamic principle, in order to prevent the rotor mechanism 6 from causing a spoiler during the rotation, the rotation direction is caused, and the rotation direction of the rotor mechanism 6 during operation is alternately set to be different in the circumferential direction of the rectangle. That is to say, the direction of rotation of any of the rotor mechanisms 6 during operation is different from the direction of rotation of the adjacent rotor mechanisms during operation.

The fuselage 2 is a carrier of the drone 100, and the components, such as sensors, circuit boards, processors, communication modules, batteries, and warehouses, can be carried on or in the body 2. In the illustrated embodiment, the body 2 includes a housing 21 having a housing space for receiving the components therein. The outer casing 21 is streamlined to reduce air resistance during flight. In other embodiments, the outer casing 21 can have other shapes, such as polygonal, circular, elliptical, and the like.

The arm assembly 4 is used to support the rotor mechanism 6 and distribute the rotor mechanism 6 around the fuselage 2 in a predetermined pattern. According to some embodiments of the present invention, the arm assembly 4 may include two main arms 41, two carrying arms 42 and four connecting arms 44 for connecting the main arm 41 and the carrying arm 42, respectively. Two main arms 41 are mounted on the body 2, respectively. As shown in Figures 1 and 2, Two through holes 22 extending in the Y-axis direction are formed on the front and rear portions of the body 2, and the two main arms 41 are respectively mounted in the two through holes 22. In the illustrated embodiment, the main arm 41 is in the form of a circular shaft, for example, a hollow circular tube. Accordingly, the through hole 22 is a circular hole. In order to prevent vibration when the drone is flying, the main arm 41 and the through hole 22 may be connected by a tight fit or an interference fit. The carrier arm 42 carries a rotor mechanism 6, each of which extends in the Z-axis direction, and the two carrier arms 42 extend in parallel. In the illustrated embodiment, the carrier arm 42 forms the long side of the rectangle. One

end portion

421, 423 of one of the carrying arms 42 and an intermediate position (i.e., the midpoint) 422 carry a rotor mechanism 6 respectively. The connecting arm 44 is used to connect the carrying arm 42 to the main arm 41, thereby connecting the rotor mechanism 6 to the body 2. In the illustrated embodiment, four connecting arms 44 are provided, one end of each connecting arm 44 being coupled to the main arm 41 and the other end being coupled to the carrying arm 42. Each of the connecting arms 44 extends parallel to the Y-axis direction, that is, the extending direction of the connecting arm 44 and the main arm 41 are the same, and the extending direction of the connecting arms 44 is perpendicular to the extending direction of the carrying arm 42. Thus, as shown in FIG. 2, the arm assembly having two main arms 41, two carrying arms 42, and four connecting arms 42 is distributed in a generally "H" shape. Also, the fuselage 2 is disposed at a central position of the "H"-shaped distribution, and the six rotor mechanisms 6 are respectively disposed on both sides of the "H"-shaped distribution. The distribution of the fuselage 2 and the rotor mechanism 6 is balanced, so that the structural strength of the entire arm assembly is high and the rigidity is good.

Further, since the arm assembly is distributed in a substantially "H" shape, the space inside the drone 100 can be utilized as a whole. Thus, when the drone 100 is used for shipping, it is possible to load a bulky cargo. Moreover, in the arm assembly 4 according to the embodiment of the present invention, the main arm 41, the carrying arm 42 and the connecting arm 44 may each be made of a carbon rod, for example, may be made of a hollow circular carbon tube or a carbon rod. The weight of the entire arm assembly 4 is made lighter, so that the empty weight of the entire drone is lighter. Thus, when the drone 100 is used for shipping, the load of the drone 100 can be increased, that is, the effective load of the drone can be improved.

In accordance with an embodiment of the present invention, the rotor mechanism 6 includes a drive member 62 and a blade assembly 64 that is mounted on a carrier arm 42 that is removably coupled to the drive member 62. As an example, the drive member 62 can be a motor, such as a brushless motor, a brushed motor, or the like, of any suitable type. The blade assembly 64 can be a propeller that is rotated by the drive member 62 to provide power to the drone 100.

Next, the arrangement of the rotor mechanism 6 will be described in detail with reference to Figs. 1, 3 and 4. For convenience of description, the plane defined by the two carrying arms 42 is referred to as the carrying plane. As shown in Figure 1, four rotor mechanisms 6 are disposed below the load bearing plane and two rotor mechanisms 6 are disposed above the load bearing plane. Taking the three rotor mechanisms 6 located on one of the carrying arms 42 as an example, the three rotor mechanisms 6 are arranged in a "lower", "upper", "lower" manner. That is, the two rotor mechanisms 6 at both ends of one of the carrying arms 42 are disposed below the carrying plane, and one of the rotor mechanisms 6 at the intermediate position of the carrying arms 42 is disposed above the carrying plane. Each blade assembly or propeller 64 has its own paddle size (i.e., the area or area of the plane P swept by the propeller 64 as it rotates), as shown in FIG. In the conventional drone, the rotor mechanisms are all arranged in the same plane. In order to make the propellers not interfere with each other when rotating, it is necessary to reserve a certain amount between the propeller disc sizes of the propellers. The interval, for example, 2-3 cm. In the embodiment of the present invention, by the above arrangement of the rotor mechanism 6, in the XY plane perpendicular to the Z-axis, as shown in FIG. 3, the rotor mechanisms 6 are respectively located at the upper and lower positions, that is, adjacent rotor mechanisms 6 There is a certain vertical gap G between them. Thus, even if there is overlap in the projection of the paddle size of the propeller mechanism 6 in the bearing plane (as shown in FIG. 5), the propellers of the adjacent rotor mechanisms 6 do not mutually interact due to the existence of the vertical gap G. put one's oar in. That is to say, with the above arrangement of the rotor mechanism 6, the rotor mechanism 6 can be arranged more compactly in the Z-axis direction (ie, the length direction of the fuselage), so that the length direction of the fuselage can be reduced, thereby making the drone The size is smaller and the weight is lighter.

In the illustrated embodiment, two rotor mechanisms 6 located intermediate the carrier arms 42 are disposed above the load bearing plane. Thus, when the drone 100 is used as a delivery drone, since the cargo bin is installed under the fuselage 2, the two rotor mechanisms 6 do not interfere with the installation of the cargo bin, so that the drone 100 is not The cargo load has an impact.

Referring back to FIG. 1, one end of each of the connecting arms 44 is connected to the main arm 41 via a first connecting mechanism 441, and the other end is connected to the carrying arm 42 via a second connecting mechanism 442. According to an embodiment of the present invention, the first connection mechanism 441 may have a folding function, that is, it may be a folding mechanism. Next, the first connection mechanism 441 will be described in detail with reference to FIGS. 6-9.

Referring to FIGS. 6 and 7, the first connecting mechanism 441 includes a main arm connecting seat 4411, a connecting arm connecting seat 4412, a pivot 4413, and a fixing member 444. The main arm connecting seat 4411 is connected to the main arm 41, and the connecting arm connecting seat 4412 is connected to the connecting arm 44. In other embodiments, the main arm connector 4411 can be part of the main arm 41, ie it is made integrally with the main arm 41. The link arm connector 4412 can be part of the link arm 44, i.e., it is integrally formed with the link arm 44. As shown in FIG. 6, when the fixing member 444 is mounted, the main arm 41 and the connecting arm 44 are connected and fixed together by the connection of the main arm connecting seat 4411 and the connecting arm connecting seat 4412. As shown in FIG. 7, when the fixing member 444 is removed, the connecting arm connecting seat 4412 is rotatable relative to the main arm connecting seat 4411 about the pivot 4413 so that the connecting arm 44 can rotate relative to the main arm 41 about the pivot 4413. To achieve the folding function.

In the illustrated embodiment, the main arm connector 4411 is formed with a main arm flange portion 4414 on the top and bottom, respectively, and each of the main arm flange portions 4414 has a main arm mounting wall 4415. As shown, the upper main arm flange portion 4414 has two main arm mounting walls 4415, and the lower main arm flange portion 4414 has three main arm mounting walls 4415. A main arm through hole 4416 is formed in each of the main arm mounting walls 4415. The extending direction of the main arm through hole 4416 is perpendicular to the axial direction of the main arm 41. Accordingly, the link arm connector 4412 is formed with a link arm flange portion 4417 on the top and bottom. Each of the link arm flange portions 4417 has a link arm mounting wall 4418. As shown, the upper connecting arm flange portion 4417 has a connecting arm mounting wall 4418, and the lower connecting arm flange portion 4417 has two connecting arm mounting walls 4418. A connecting arm through hole 4419 is formed in each of the connecting arm mounting walls 4418. The extending direction of the connecting arm through hole 4419 is perpendicular to the axial direction of the connecting arm 41. When the main arm connecting seat 4411 and the connecting arm connecting seat 4412 are connected, the lower connecting arm flange portion 4417 is aligned with the lower main arm flange portion 4414 so that the two connecting arm mounting walls 4418 are respectively inserted into three In the gap formed by the main arm mounting walls 4415, that is, each of the two connecting arm mounting walls 4418 is clamped by the two main arm mounting walls 4415, and the connecting arm through holes 4419 in the connecting arm mounting walls 4418 are made. The main arm through holes 4416 in the main arm mounting wall 4415 are aligned with each other. The pivot 4413 is inserted into the mutually aligned connecting arm through hole 4419 and the main arm through hole 4416 to form a pivot shaft that rotates the connecting arm connecting seat 4412 with respect to the main arm connecting seat 4411. Further, the upper connecting arm flange portion 4417 is aligned with the upper main arm flange portion 4414 such that one connecting arm mounting wall 4418 is inserted into the gap formed by the two main arm mounting walls 4415, that is, one connection The arm mounting wall 4418 is clamped by the two main arm mounting walls 4415, and the connecting arm through holes 4419 in the connecting arm mounting wall 4418 and the main arm through holes 4416 in the main arm mounting wall 4415 are aligned with each other. The fixing member 444 is inserted into the mutually aligned connecting arm through hole 4419 and the main arm through hole 4416 to fix the connecting arm connecting seat 4412 and the main arm connecting seat 4411 together. It can be understood that the fixing member 444 can be tightly engaged with the mutually aligned connecting arm through hole 4419 and the main arm through hole 4416 to minimize the gap between the connecting arm connecting seat 4412 and the main arm connecting seat 4411. Thereby, the vibration that may be generated when the drone 100 is flying is effectively suppressed. In some embodiments, the fastener 444 can be a fastening bolt or screw or a thumb screw to facilitate installation.

In the above embodiment, the axis of the fixing member 444 is perpendicular to the axial direction of the main arm 41 and the connecting arm 44, which provides sufficient operation space for the mounting of the fixing member 444, thereby facilitating the connecting arm connecting seat 4412 and the main arm connecting seat. The connection of the 4411 is fixed.

According to the embodiment of the present invention, the first connecting mechanism 441 may be formed at each connection position where the four connecting arms 44 are connected to the main arm 41, that is, the four connecting arms 44 are connected to the main arm 41 through the first connecting mechanism 441. . In this way, the folding function can be implemented at four connection positions. Figure 8 is a schematic view showing a state in which both the carrying arms on both sides and their carried rotor mechanisms are folded, and Figure 9 is a perspective view schematically showing the carrying arms on both sides and their carried rotor mechanisms are folded status. As shown in the figure, in combination with the H-shaped arrangement and the first connecting mechanism 441, the carrying arms 42 on both sides and the rotor mechanism 6 carried thereon can be folded toward the inside of the fuselage, effectively reducing the number of unmanned The volume of machine 100 in an inactive state (ie, a non-flight state, such as a stored state). In the embodiment of the present invention, based on the structure of the first connecting mechanism 441 described above, the connecting arm 44 can be rotated about the pivot 4413 by about 90° with respect to the main arm 41. When both the carrying arms 42 on both sides and their carried rotor mechanisms 6 are folded, the width of the drone 100 can be reduced by about 30-40%.

Additionally, in some embodiments, the drone 100 can also include a rack 9 (shown in Figure 1). In order to facilitate the landing of the drone 100.

Hereinafter, an embodiment of the present invention will be further described by taking the drone 100 as a delivery drone as an example.

Referring to FIGS. 10 and 11, in addition to the structure of the drone 100 described above, the delivery drone 200 may further include a warehouse 8. The cargo compartment 8 is detachably mounted on the fuselage 2, for example, mounted below the fuselage 2. The warehouse 8 has a housing 81. When the warehouse 8 is mounted on the body 2, as shown in FIG. 10, the outer casing 81 of the cargo compartment 8 and the outer casing 21 of the fuselage 2 are So that the fuselage 2 and the warehouse 8 can form an integral part. For example, the outer casing of the integral part composed of the fuselage 2 and the cargo compartment 8 is streamlined, so that the air resistance during flight can be reduced. It should be understood that when the bin 8 is removed from the fuselage 2, as shown in FIG. 11, the drone 200 can still fly independently as a complete drone. Thus, when the warehouse is mounted to the fuselage, the outer casing of the fuselage and the cargo compartment is streamlined, compared to the manner in which the cargo parcel or express parcel is directly mounted or otherwise mounted on the fuselage. The delivery drone according to an embodiment of the present invention has a much smaller overall air resistance during flight, thereby greatly improving the life time of the delivery drone. On the other hand, in order to place the parcel or express parcel in the interior of the drone or in the nacelle, the fuselage needs to be designed to be large enough to have sufficient accommodation space inside to accommodate the cargo. Moreover, in order to accommodate a variety of cargo sizes, it is often necessary to design the fuselage to a larger size to meet the shipping requirements of the largest volume of cargo. However, the delivery drone according to the embodiment of the present invention sets the cargo compartment outside the fuselage, and does not need to design the fuselage to be large, so that the volume and weight of the drone can be effectively reduced.

It should be noted that "streamlined" herein refers to an external shape of an object, which generally appears as a smooth and regular surface without large undulations and sharp edges. The fluid is mainly laminar on the surface of the streamlined object, with little or no turbulence, so that the object can be subjected to less resistance.

With continued reference to Figures 12 and 13, the cargo bin 8 is mounted to the fuselage 2 by a detachable connection structure 82. According to an embodiment of the present invention, the detachable connection structure 82 may include a plurality of hooks 821 disposed on the body 2 and a plurality of hook points 822 disposed in the cargo bed 8, the hooks 821 being capable of engaging the hook points 822 Engaged to mount the cargo bin 8 to the fuselage 2. In an alternative embodiment, the detachable connection structure may include a plurality of hooks disposed on the cargo compartment and a plurality of hook points disposed in the fuselage, the hooks being capable of engaging the hook points Engaged to mount the cargo bin to the fuselage.

In other embodiments, a fixed aperture 823 is also provided at the location of the bin 8 adjacent the hook point 822. When the hook 821 is engaged with the hook point 822, a screw can be inserted into the fixing hole 823 to securely connect the cargo compartment 8 with the body 2.

The specific embodiments of the present invention have been described in detail in the foregoing detailed description of the embodiments of the present invention. All modifications, equivalents, improvements, etc., made within the spirit and scope of the invention are intended to be included within the scope of the invention.

Claims

An unmanned aerial vehicle comprising a fuselage, an arm assembly and a rotor mechanism, the arm assembly being coupled to the fuselage, the rotor mechanism being distributed around the fuselage by the arm assembly, wherein The arm assembly includes:

a main arm mounted on the fuselage;

At least two carrying arms on which the rotor mechanisms are carried, each of the carrying arms extending parallel to each other along the length of the fuselage; and

a connecting arm for connecting the main arm and the carrying arm, one end of the connecting arm is connected to the main arm, and the other end of the connecting arm is connected to the carrying arm, the connecting arm and the connecting arm The main arms extend in the same direction, and the extending direction of the connecting arm and the main arm is perpendicular to the extending direction of the carrying arm.
The drone according to claim 1, wherein the drone includes a plurality of rotor mechanisms, and the at least two carrying arms extending parallel to each other are located in the same carrying plane, among the plurality of rotor mechanisms A portion is disposed above the load bearing plane, and another portion of the plurality of rotor mechanisms is disposed below the load bearing plane.
The drone according to claim 1 or 2, wherein one end of the connecting arm is coupled to the main arm by a first connecting mechanism, the first connecting mechanism having a pivot, the pivot having a parallel The axial direction of the longitudinal direction of the fuselage, the first coupling mechanism is configured such that the connecting arm is rotatable relative to the main arm about the pivot.
The drone according to any one of claims 1 to 3, further comprising a cargo bin, the cargo bin being mounted to the fuselage by a detachable connection structure.
The drone according to any one of claims 1 to 4, wherein the drone includes two of the carrying arms, one of the carrying arms is located on one side of the fuselage, and the other of the carrying The arms are located on opposite sides of the fuselage and each of the carrying arms carries three of the rotor mechanisms.
The drone according to claim 5, wherein a rotor mechanism is carried at each of the two end portions of the carrying arm and at an intermediate position between the two ends.
The drone according to claim 6, wherein said rotor mechanism at an end of said carrying arm is disposed below said carrying plane at an intermediate position between both ends of said carrying arm The rotor mechanism at the location is disposed above the load bearing plane.
A drone according to claim 2 or claim 7, wherein each of said rotor mechanisms includes a propeller, and a region of the propeller located above said load-bearing plane swept during rotation and a propeller located below said load-bearing plane There is an overlap in the projections of the scanned area during rotation in the bearing plane.
The drone according to claim 3, wherein said first connecting mechanism further comprises a fixing member for fixedly connecting said connecting arm and said main arm to set said drone Into a working state.
The drone of claim 9, wherein the first attachment mechanism is configured such that the attachment arm is rotatable about the pivot relative to the main arm toward the body by about 90° to The drone is set to a non-working state.
The drone of claim 9, wherein the first connection mechanism further comprises:

a main arm connecting seat connected to the main arm, the main arm connecting seat having a plurality of main arm flange portions disposed opposite to each other in a radial direction thereof, each of the main arm flange portions Each has a main arm mounting wall, and each of the main arm mounting walls is formed with a main arm through hole, and an extending direction of the main arm through hole is parallel to an axial direction of the pivot; and

a connecting arm connecting seat, the connecting arm connecting seat being connected to the connecting arm, the connecting arm connecting seat having a connecting arm flange portion disposed opposite to each other in a radial direction thereof, each of the connecting arm flange portions having The connecting arm mounting wall is formed with a connecting arm through hole in each of the connecting arm mounting walls, and the connecting arm through hole extends in a direction parallel to an axial direction of the pivot.
The drone of claim 4, wherein the outer casing of the cargo bin matches the outer casing of the fuselage such that when the cargo bin is mounted on the fuselage, the cargo bin and The fuselage constitutes an integral part.
The drone according to claim 12, wherein the outer casing of the integral member composed of the body and the cargo bin is streamlined.
The drone according to claim 4, 12 or 13, wherein said detachable connection structure comprises a plurality of hooks provided on said body and a plurality of hook points provided in said magazine, a hook engageable with the hook point to mount the cargo bin to the fuselage; or

The detachable connection structure includes a plurality of hooks disposed on the cargo compartment and a plurality of hook points disposed in the fuselage, the hooks being engageable with the hook points to mount the cargo bin To the fuselage.