CN210212750U - Unmanned aerial vehicle fuselage and unmanned aerial vehicle - Google Patents

Abstract

The utility model provides an unmanned aerial vehicle fuselage. The unmanned aerial vehicle fuselage includes fuselage main part (10). The fuselage body (10) comprises a receiving structure (11) and at least one cantilever (12). The accommodating structure (11) comprises a bottom supporting frame (111) and a circumferential supporting frame (112), the bottom supporting frame (111) is located below the circumferential supporting frame (112), and the bottom supporting frame (111) and the circumferential supporting frame (112) are connected to form an accommodating space of the accommodating structure (11). A first end of each cantilever arm (12) of the at least one cantilever arm (12) is connected to the accommodating structure (11), and a second end opposite to the first end extends in a direction away from the accommodating structure (11). The present disclosure provides an unmanned aerial vehicle (1) comprising the unmanned aerial vehicle fuselage.

Description

Unmanned aerial vehicle fuselage and unmanned aerial vehicle

Technical Field

The utility model relates to a storage commodity circulation field, more specifically relates to an unmanned aerial vehicle fuselage and unmanned aerial vehicle.

Background

Among present commodity circulation unmanned aerial vehicle, the intermediate portion of fuselage is the major structure of fuselage, and the cantilever is outwards stretched out by the center of fuselage, installs the motor on the extreme point outside the cantilever to control the rotation of screw through the motor. The middle part of the fuselage is typically used for mounting avionics such as flight controls, resulting in cargo baskets that are usually placed only beneath the fuselage. As such, loading and unloading of cargo requires operations beneath the fuselage and is limited by the size of the volume beneath the fuselage, with the baskets typically being small.

SUMMERY OF THE UTILITY MODEL

In view of this, the present disclosure provides an unmanned aerial vehicle fuselage and unmanned aerial vehicle, wherein the middle part of unmanned aerial vehicle fuselage is used for placing the basket, can get goods or unload from the top of unmanned aerial vehicle moreover.

The present disclosure provides an unmanned aerial vehicle fuselage. The unmanned aerial vehicle fuselage includes the fuselage main part. The fuselage body includes a receiving structure and at least one cantilever. The accommodating structure comprises a bottom supporting frame and a circumferential supporting frame, the bottom supporting frame is located below the circumferential supporting frame, and the bottom supporting frame and the circumferential supporting frame are connected to form an accommodating space of the accommodating structure. The first end of each cantilever in the at least one cantilever is connected to the accommodating structure, and the second end opposite to the first end extends in the direction away from the accommodating structure.

According to the embodiment of the disclosure, the fuselage main body comprises at least three arms, the at least three arms are connected in a pairwise staggered manner, and two ends of each arm of the at least three arms extend out of a staggered area, wherein the staggered area is an area formed by the at least three arms in a pairwise staggered manner. Wherein a portion of the at least three horn within the interleaved region constitutes the circumferential support frame. The portion of the at least three arms outside the interleaved region constitutes the at least one boom.

According to an embodiment of the present disclosure, the at least three horn comprises four horns.

According to an embodiment of the present disclosure, each horn includes a first body, two second bodies, and two connectors. The two connecting pieces are respectively arranged at two ends of the first body. Wherein the first body and each of the two second bodies are foldably connected by one of the two connectors. The first body constitutes a part of said each horn belonging to said circumferential support frame and the two second bodies constitute a part of said each horn belonging to said at least one boom.

According to an embodiment of the present disclosure, the connector comprises a first frame structure and a second frame structure. The first frame structure includes a first clamping member and a first opening. The second frame structure is connected to the first frame structure. The second frame structure includes a second clamp member and a second opening oriented differently than the first opening. Wherein the first frame structure is configured to place an end of one of the two first bodies via the first opening, and the second frame structure is configured to place an end of the other of the two first bodies via the second opening. Wherein at least one of the first and second clamp members is configured to rotatably connect with the second body.

According to an embodiment of the present disclosure, the connector comprises a fixed part and at least one movable part. The fixed portion includes at least one first rotational engagement structure. The movable part comprises a second rotating fit structure, wherein the second rotating fit structure is matched with the first rotating fit structure to form a shaft hole fit structure, so that the movable part is rotatably connected with the fixed part through the shaft hole fit structure. Wherein the fixed part is configured to be connected with the first body, and the movable part is configured to be connected with the second body; the axis of rotation of shaft hole cooperation structure is the acute angle with the contained angle of first plane, wherein first plane perpendicular to is followed the fixed part points to the direction of first body.

According to the embodiment of the present disclosure, the unmanned aerial vehicle fuselage further includes a control system mounting structure. The control system mounting structure is arranged on the periphery of the accommodating structure.

According to an embodiment of the present disclosure, the control system mounting structure includes at least two power battery carrying structures. The at least two power battery carrying structures are symmetrically arranged on the periphery of the accommodating structure relative to a vertical line passing through the gravity center of the main body of the fuselage.

According to an embodiment of the present disclosure, the control system mounting structure includes an avionics pod. The avionics pod is disposed below the bottom support frame.

According to an embodiment of the present disclosure, the control system mounting structure includes a positioning device mounting structure. The positioning device mounting structure is arranged above the circumferential support frame.

According to an embodiment of the present disclosure, the fuselage body further comprises at least one basket securing structure. The at least one basket securing structure is mounted on the circumferential support frame.

Another aspect of the present disclosure also provides an unmanned aerial vehicle. The unmanned aerial vehicle includes the unmanned aerial vehicle fuselage as described above.

According to the embodiment of the disclosure, the containing structure can be arranged in the middle of the unmanned aerial vehicle body to bear goods, the control system of the unmanned aerial vehicle is installed on the periphery of the containing structure, goods taking or unloading can be achieved from the upper side of the unmanned aerial vehicle, and man-machine operation is facilitated.

Drawings

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

fig. 1A schematically illustrates a schematic view of a drone-containing cargo basket, according to an embodiment of the present disclosure;

fig. 1B schematically illustrates a schematic drawing of a cargo basket being removed from above a drone according to an embodiment of the present disclosure;

fig. 1C schematically illustrates a perspective structural view of a drone according to an embodiment of the present disclosure;

fig. 1D schematically illustrates a top view of a drone according to an embodiment of the present disclosure;

fig. 2A schematically illustrates a schematic view of a "groined" fuselage frame of a drone in a deployed state with a horn according to an embodiment of the present disclosure;

fig. 2B schematically illustrates a schematic view of a folding process of a horn in a "groined" fuselage frame of a drone according to an embodiment of the present disclosure;

fig. 2C schematically illustrates a schematic view of a folded arm in a "cross-shaped" fuselage frame of a drone according to an embodiment of the present disclosure;

FIG. 3A schematically illustrates a folded-up plan view of the horn taken from perspective A in FIG. 2C, in accordance with one embodiment of the present disclosure;

fig. 3B schematically shows a perspective view of the unmanned aerial vehicle of fig. 3A with the horn in a deployed state;

FIG. 3C is a perspective view schematically showing a connecting member partially shown in C of FIG. 3B

FIG. 3D is a perspective view schematically illustrating the connector part D of FIG. 3B;

FIG. 4A schematically illustrates a folded horn view from perspective A in FIG. 2C, according to another embodiment of the present disclosure;

FIG. 4B schematically illustrates an enlarged view of the linkage of FIG. 4A with the first and second bodies of the horn in a folded condition;

FIG. 4C schematically illustrates a perspective view of the connector of FIGS. 4A and 4B;

fig. 5 schematically illustrates a perspective view of a bottom support frame in a drone according to an embodiment of the present disclosure;

fig. 6A schematically illustrates a schematic view of a basket securing structure in a drone in contact with a basket, according to an embodiment of the present disclosure;

fig. 6B schematically illustrates a schematic view of a basket securing structure in a drone according to an embodiment of the present disclosure not in contact with a basket.

Fig. 7A schematically illustrates an installation location schematic of a power battery carrying structure in a drone according to an embodiment of the present disclosure;

fig. 7B schematically illustrates a three-dimensional structure of a power battery carrying structure according to an embodiment of the present disclosure;

fig. 8A schematically illustrates a block diagram of an avionics bay in a drone according to an embodiment of the present disclosure;

FIG. 8B schematically shows a block diagram of the avionics bay body of the avionics bay in FIG. 8A; and

fig. 9 schematically shows an installation schematic diagram of a positioning device installation structure in a drone according to an 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 illustrative only 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 disclosure. It may be evident, however, that one or more embodiments may be practiced without these specific details. Moreover, in the following description, descriptions of well-known structures and techniques are omitted so as to not 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, steps, operations, and/or components, but do not preclude the presence or addition of one or more other features, steps, 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 is noted that the terms used herein should be interpreted as having a meaning that is consistent with the context of this specification and should not be interpreted in an idealized or overly formal sense.

Where a convention analogous to "at least one of A, B and C, etc." is used, in general such a construction is intended in the sense one having skill in the art would understand the convention (e.g., "a system having at least one of A, B and C" would include but not be limited to systems that have 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 "A, B or at least one of C, etc." is used, in general such a construction is intended in the sense one having skill in the art would understand the convention (e.g., "a system having at least one of A, B or C" would include but not be limited to systems that have 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.).

In the context of the present disclosure, when an element is referred to as being "on" or "connected to" another element, it can be directly on or connected to the other element or other elements may be present therebetween. In addition, if a component is "on" another component in one orientation, that component may be "under" the other component when the orientation is reversed. When an element is referred to as being "between" two other elements, it can be directly between the two other elements or intervening elements may also be present.

The embodiment of the disclosure provides an unmanned aerial vehicle fuselage and an unmanned aerial vehicle comprising the unmanned aerial vehicle fuselage. This unmanned aerial vehicle fuselage includes the fuselage main part. The fuselage body includes a receiving structure and at least one cantilever. The accommodating structure comprises a bottom supporting frame and a circumferential supporting frame, the bottom supporting frame is located below the circumferential supporting frame, and the bottom supporting frame and the circumferential supporting frame are connected to form an accommodating space of the accommodating structure. The first end of each cantilever in the at least one cantilever is connected to the accommodating structure, and the second end opposite to the first end extends in the direction away from the accommodating structure. The second end of each of the at least one boom may be mounted with a motor on which a propeller is mounted, wherein rotation of the propeller is controlled by the motor.

According to an embodiment of the present disclosure, the control system mounting structure is disposed at a periphery of the accommodating structure. The control system mounting structure may include a power battery carrying structure, an avionics bay, and/or a positioning device mounting structure, among other things. The power battery carrying structure may be used for mounting a power battery. The avionics bay may be used to install avionics systems, which may include flight controls, IMUs, communication modules, and radio modules, among others. The positioning device mounting structure may be used to mount a positioning device, and the positioning device may be, for example, a GPS or an RTK (Real-Time Kinematic) related device.

The control system mounting structure is arranged on the periphery of the accommodating structure. For example, it may be mounted in corresponding positions on the circumferential support frame and/or the bottom support frame, depending on design and use requirements.

According to an embodiment of the present disclosure, the circumferential support frame may be formed of a portion of the at least three horn arms within a staggered area formed by staggering two by two, and the at least one cantilever may be formed of a portion of the at least three horn arms outside the staggered area formed by staggering two by two. Specifically, the fuselage body may include at least three arms, the at least three arms are connected in a staggered manner in pairs, and both ends of each of the at least three arms extend outside a staggered area, where the staggered area is an area formed by the at least three arms being staggered in pairs. The parts of the at least three arms located within the staggered area constitute the circumferential support frame. The portion of the at least three arms outside the interleaved region constitutes the at least one boom. In this way, a part of the at least three arms can be used as a circumferential support frame of the receiving structure, and another part can be used as at least one cantilever, so that the structure of the unmanned aerial vehicle fuselage can be simplified.

According to an embodiment of the present disclosure, the at least three horn may specifically be four horns. The four arms are staggered in pairs to form a framework shaped like a Chinese character jing. The framework in the shape of Chinese character 'jing' forms the framework of the fuselage main body.

According to some embodiments of the present disclosure, each horn of the unmanned aerial vehicle can be folded to reduce the size of the unmanned aerial vehicle, facilitating storage of the unmanned aerial vehicle.

Fig. 1A schematically shows a schematic view of a drone 1 holding a basket 2 according to an embodiment of the present disclosure. Fig. 1B schematically shows a schematic view of a cargo basket 2 being taken out from above a drone 1 according to an embodiment of the present disclosure.

As shown in fig. 1A and 1B, the basket 2 may be placed in a middle portion of the body of the drone 1, and the basket 2 may be taken out from above the drone 1.

The drone 1 comprises a fuselage body 10, wherein the fuselage body 10 comprises a containing structure 11 and at least one cantilever 12. The basket 2 is placed in the receiving structure 11. The receiving structure 11 has access to the basket 2 above it. For example, the upper side of the receiving structure 11 is open, so that the basket 2 can be taken out or put in from above the receiving structure 11. Alternatively, the accommodating structure 11 may have another structure such as an openable door above it. In the schematic of fig. 1A and 1B, the drone 1 comprises 8 cantilevers 12. A first end of the cantilever 12 is connected to the accommodating structure 11, and a second end of the cantilever, which is far away from the accommodating structure 11, is mounted with a motor (e.g., a dc brushless motor). The motor is provided with a propeller.

The drone 1 may also comprise at least two power batteries 201. In the schematic of fig. 1A and 1B, on the other side from the power cell 201 visible in the figures, there is also mounted another power cell 201. The at least two power batteries 201 are respectively mounted on one of the at least two corresponding power battery carrying structures 20. Wherein the at least two power cell carrying structures 20 may be seen in the description below with respect to fig. 7A and 7B. According to an embodiment of the present disclosure, the at least two power battery carrying structures 20 are symmetrically disposed at the periphery of the accommodating structure 11 with respect to a vertical line passing through the center of gravity of the body 10 (see fig. 1C). The at least two power cells 201 are fixed in the fuselage body 10 by the at least two power cell carrying structures 20, and such that the at least two power cells 201 are symmetrical with respect to a vertical line passing through the center of gravity of said fuselage body 10.

The drone 1 may also comprise positioning means 301. The positioning device 301 may be, for example, a GPS or an RTK (Real-time kinematic) related device. According to an embodiment of the present disclosure, the positioning device 301 is mounted in a positioning device mounting structure 30 (refer to the description of fig. 9 below). The positioning device mounting structure 30 may be disposed at an edge of the accommodating structure 11, so that the positioning device 301 is fixed at the edge of the accommodating structure 11. In the illustration of fig. 1A and 1B, the drone 1 comprises two positioning devices 301. The connecting line of the two positioning devices 301 is parallel to the connecting line of the head and the tail of the unmanned aerial vehicle 1. According to the embodiment of the present disclosure, two positioning devices 301 are disposed at the edge of the accommodating structure 11, and the positioning devices 301 can be prevented from being hit when loading and unloading the cargo basket 2 from above the unmanned aerial vehicle 1.

The drone 1 may also include an avionics system. The avionics system may be installed inside an avionics bay 40. The avionics pod 40 may be of an integrated sealed design. According to an embodiment of the present disclosure, the avionics bay 40 may be provided at the bottom of the housing structure 11 on a vertical line passing through the center of gravity of the fuselage body 10, so that the flight control may be mounted on the vertical line of the center of gravity of the fuselage body 10. According to the embodiment of the present disclosure, the avionics system of the unmanned aerial vehicle 1 and the power battery 201 may be arranged to different positions respectively, so that the avionics system can avoid the hidden danger that the power battery 201 is flammable and explosive.

According to an embodiment of the present disclosure, the fuselage body 10 of the drone 1 may also include at least one basket securing structure 13 (see description of fig. 6A and 6B below). One end of each of the at least one basket fixing structure 13 may be disposed on the receiving structure 11, and the other end may be separably contacted with the basket 2. When the cargo basket 2 is placed in the accommodating structure 11, the cargo basket fixing structure 13 clamps the cargo basket 2 to fix the cargo basket 2; when the basket 2 is to be removed from the receiving structure 11, the basket securing structure 13 is separated from the basket 2 without affecting the removal of the basket 2.

Fig. 1A and 1B show the structural form of the unmanned aerial vehicle 1, which avoids concentrating the control system and the fixed end of the cantilever 12 in the middle of the body of the unmanned aerial vehicle 1, so that there is a large space in the middle of the body of the unmanned aerial vehicle 1 for installing a cargo basket. Holding structure 11 includes the downwardly recessed accommodation space, and the basket is placed in holding structure 11, and basic and unmanned aerial vehicle 1's the focus position coincidence for unmanned aerial vehicle 1 can not have obvious change in the focus position when full-load and empty load. Specifically, when the unmanned aerial vehicle 1 is not loaded into a basket, the center of gravity of the unmanned aerial vehicle 1 is located below the geometric center of the unmanned aerial vehicle 1. When unmanned aerial vehicle 1 packed into the basket, unmanned aerial vehicle 1's focus was also in some positions of unmanned aerial vehicle 1's geometric centre under again, therefore unmanned aerial vehicle 1's focus position is unchangeable basically. Like this, be convenient for to unmanned aerial vehicle 1's flight control, be favorable to the stability of unmanned aerial vehicle 1 flight.

It should be noted that the drone 1 shown in fig. 1A and 1B is only one example of a structure of a drone that may be used in the embodiments of the present disclosure 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 used in drones of other structural forms.

Fig. 1C schematically shows a perspective structure diagram of the unmanned aerial vehicle 1 according to an embodiment of the present disclosure, and fig. 1D schematically shows a top view of the unmanned aerial vehicle 1 according to an embodiment of the present disclosure.

As shown in fig. 1C and 1D, from a structural division perspective, the unmanned aerial vehicle 1 includes a housing structure 11 and at least one suspension arm 12 (8 suspension arms 12 in the specific example in the figure). Wherein the receiving structure 11 comprises a bottom supporting frame 111 and a circumferential supporting frame 112. The bottom support frame 111 is connected below the circumferential support frame 112. The bottom support frame 111 may on the one hand serve as a bottom of the receiving structure 11 for carrying a basket; on the other hand, the circumferential support frame 12 can be connected and stabilized, and the structural stability of the fuselage body 10 is enhanced. A first end of each cantilever 12 of the at least one cantilever 12 is connected to the receiving structure 11, and a second end opposite to the first end extends away from the receiving structure 11.

From another structural division perspective, the fuselage body 10 of the drone 1 may include at least three arms 14 (specifically, four arms 14 are illustrated in the figure). The four arms 14 are connected in a pairwise staggered manner, and two ends of each arm 14 of the four arms 14 extend out of a staggered area 15, wherein the staggered area 15 is an area formed by the four arms 14 in a pairwise staggered manner. Wherein the portions of the four arms 14 located within the staggered area 15 constitute the circumferential support frame 112. The portions of the four arms 14 outside the crossover region 15 constitute the at least one boom 12 (so 8 booms 12 are obtained). The bottom support frame 111 is located in the space of the staggered area 15 and connected to the lower side of the circumferential support frame 112. The connection and combination of the bottom support frame 111 and the circumferential support frame 112 forms the containment structure 11.

As shown in fig. 1C and 1D, the main body 10 of the drone 1 includes four arms 14 staggered two by two, forming a "groined" fuselage frame. The receiving structure 11 may be disposed in the middle of the frame of the fuselage shaped like a Chinese character jing.

According to an embodiment of the present disclosure, each horn 14 of the drone 1 may be folded, for which reference may be made to the illustrations of fig. 2A-2C.

Fig. 2A schematically illustrates a schematic view of the "groined" frame of the drone 1 with the horn 14 in a deployed state, according to an embodiment of the present disclosure; fig. 2B schematically shows a schematic view of the folding process of the horn 14 in the "groined" frame of the drone 1 according to an embodiment of the present disclosure. Fig. 2C schematically illustrates a schematic view of the folded boom 14 in the "cross-shaped" fuselage frame of the drone 1 according to an embodiment of the present disclosure.

As shown in fig. 2A to 2C, when the unmanned aerial vehicle 1 is stored, the two cantilevers 12 in each arm 14 may be folded toward the intersection area 15 to reduce the space of the unmanned aerial vehicle 1.

As particularly shown in fig. 2A, according to an embodiment of the present disclosure, each horn 14 may include a first body 141, two second bodies 142, and two connectors 143. The two connecting members 143 are respectively disposed at two ends of the first body 141. Wherein the first body 141 and each of the two second bodies 142 are foldably connected by one of the two connecting members 143. The first body 141 forms part of said each horn 14 belonging to said circumferential support frame 112, and the two second bodies 142 form part of said each horn 14 belonging to said at least one boom 12. For example, each second body 142 may form a cantilever 12 as shown in the figures.

Fig. 3A schematically illustrates a folded plan view of the horn 14 taken from perspective a in fig. 2C, in accordance with an embodiment of the present disclosure. Fig. 3B schematically shows a perspective view of the arm 14 of the drone 1 in fig. 3A in a deployed state.

As shown in fig. 3A and 3B, according to an embodiment of the present disclosure, a minimum distance of two second bodies 142 (i.e., two second bodies 142 respectively connected to both ends of the same first body 141) in the same horn 14 in a direction perpendicular to a plane of a fuselage formed by the at least three horns 14 being staggered two by two is greater than zero. In this way, when the four arms 14 are assembled to form the shaft-shaped body frame of the unmanned aerial vehicle 1, the two adjacent second bodies 142 can be at different heights, and the minimum distance between the two adjacent second bodies 142 (i.e., the two second bodies 142 folded toward each other) in the direction perpendicular to the plane of the body can be greater than zero by the installation and combination (as shown in fig. 3B). In this way, when two adjacent second bodies 142 are folded relatively, the two adjacent second bodies can be not interfered with each other, and the problem existing when the horn is folded transversely relatively in the prior art is avoided.

Fig. 3C schematically shows a perspective view of the connecting member 143 shown in part C of fig. 3B. Fig. 3D schematically shows a perspective view of the connecting member 143 shown in part D of fig. 3B.

As shown in fig. 3C and 3D, the connecting member 143 may include a first frame structure 1410, and a second frame structure 1420. The first frame structure 1410 includes a first gripping member 1411 and a first opening 1412. The second frame structure 1420 is connected to the first frame structure 1410. The second frame structure 1420 includes a second clamp member 1421 and a second opening 1422, the second opening 1422 being oriented differently than the first opening 1412. Wherein the first frame structure 1410 places an end of one first body 141 through the first opening 1412, and the second frame structure 1420 places an end of another first body 141 through the second opening 1422. Wherein the first opening 1412 and the second opening 1422 are oriented in the same direction (e.g., perpendicular) as the two arms 14 that are staggered with each other.

At least one of the first and second clamp members 1411 and 1421 is rotatably coupled to at least one second body 142. For example, two horn members 14 are staggered with each other at staggered positions, one second body 142 is foldably connected to the first clamping part 1411, and the other second body 142 is foldably connected to the second clamping part 1421 (see a partially enlarged view of part c or part d in fig. 3B).

Fig. 3C and 3D are different in that the first clamping part 1411 and the first opening 1412 of the connecting member 143 in fig. 3C are adjacent to each other, and the second clamping part 1421 and the second opening 1422 are adjacent to each other. In fig. 3D, the first clamping part 1411 and the first opening 1412 of the connecting member 143 are opposite to each other, and the second clamping part 1421 and the second opening 1422 are opposite to each other.

As shown in fig. 3C in particular, according to one embodiment of the present disclosure, the first clamping member 1411 and the first opening 1412 are adjacent to each other, the second clamping member 1421 and the second opening 1422 are adjacent to each other, such that when the second body 142 (i.e., the cantilever 12) is unfolded, the second body 142 connected to the first clamping member 1411 is perpendicular to one first body 141 disposed in the first frame structure 1410 through the first opening 1412, and the second body 142 connected to the second clamping member 1421 is perpendicular to the other first body 141 disposed in the second frame structure 1420 through the second opening 1422. The first body 141 and the second body 142 of one horn 14 connected by the connecting member 143 in fig. 3C are at different heights (see part C in fig. 3B).

As shown in fig. 3D, according to another embodiment of the present disclosure, the first clamping member 1411 and the first opening 1412 are opposite to each other, and the second clamping member 1421 and the second opening 1422 are opposite to each other. Thus, such that when the second body 142 (i.e., boom 12) is unfolded, the second body 142 connected to the first clamping member 1411 and one of the first bodies 141 disposed in the first frame structure 1410 through the first opening 1412 are parallel to each other (e.g., in opposite directions), and the second body 142 connected to the second clamping member 1421 and the other of the first bodies 141 disposed in the second frame structure 1420 through the second opening 1422 are parallel to each other (e.g., in opposite directions). The first body 141 and the second body 142 of one horn 14 connected by the connecting member 143 in fig. 3D are at the same height (see part D in fig. 3B).

Fig. 4A schematically illustrates a folded view of the horn 14 from perspective a in fig. 2C, according to another embodiment of the present disclosure.

As shown in fig. 4A, according to another embodiment of the present disclosure, the connection member 143 may include a rotation axis at an acute angle with respect to a first plane perpendicular to a direction pointing from the connection member 143 to the first body 141, and each of the second bodies 142 may be rotatably folded about the rotation axis with respect to the first body 141. Therefore, when the directions of the rotation axes of the two connecting members 143 connected to the two adjacent second bodies 142 are parallel and the included angle with the first plane is properly selected, the two adjacent second bodies 142 can rotate in the planes which are parallel and separated from each other by a certain gap when folded relatively, and in this way, the interference problem when the two adjacent second bodies 142 are folded relatively can be avoided.

Fig. 4B schematically shows an enlarged view of the connecting member 143 of fig. 4A with the first body 141 and the second body 142 of the horn 14 in a folded state; fig. 4C schematically shows a perspective view of the connecting member 143 in fig. 4A and 4B.

As shown in fig. 4B and 4C, according to an embodiment of the present disclosure, the connection member 143 may include a fixed part 1431 and at least one movable part 1432. The fixed part 1431 is connected with the first body 141, and each movable part 1432 is connected with one of the at least one second body 142.

The fixed portion 1431 includes at least one first rotation engagement structure 14301.

Each movable portion 1432 of the at least one movable portion 1432 includes a second rotation engagement structure, wherein the second rotation engagement structure is coupled with one of the at least one first rotation engagement structure 14301 to form a shaft hole engagement structure 1430, such that each movable portion 1432 is rotatably coupled to the fixed portion 1431 through the shaft hole engagement structure 1430. The rotation axis of the shaft hole matching structure 1430 includes an acute angle a with a first plane perpendicular to the direction from the fixing portion 1431 to the first body 141 (see fig. 4B). In the illustration of fig. 4B, the first plane is illustrated as a vertical plane merely as an example.

The first rotation engagement feature 14301 may be one of a shaft or a bore in the shaft bore engagement feature 1430, and correspondingly the second rotation engagement feature is another portion of the shaft bore engagement feature 1430 that engages the first rotation engagement feature 14301. According to the embodiment of the present disclosure, the shaft hole matching structure 1430 is not limited to the matching of the rotating shaft and the hole shown in fig. 4A to 4C, but may be in other forms such as a screw and hole connection, a rivet connection, etc., as long as the relative rotation of the movable part 1432 and the fixed part 1431 can be achieved.

According to the embodiment of the present disclosure, the rotation axis of the shaft hole matching structure 1430 formed between the movable part 1432 and the fixed part 1431 forms an acute angle rather than parallel to the first plane, so that the second body 142 connected to the movable part 1432 can be rotatably folded in the plane of the first plane forming an acute angle. The acute angle between the rotation axis of the rotation shaft matching structure 30 and the first plane is related to the size of the first body 141 between two adjacent second bodies 142 and the degree to which the two adjacent second bodies 142 can be staggered. For example, the acute angle a may be 1.5 ° to 4 ° in one embodiment.

According to an embodiment of the present disclosure, the fixation portion 1431 includes two frame structures 1450. Each of the two frame structures 1450 includes oppositely disposed first and second connection ends 1451 and 1452. Wherein the two frame structures 1450 are staggered up and down. The first connection end 1451 includes one of at least one first rotational engagement feature 14301. The second connection end 1452 is configured to be connected with the first body 141. The second connection end 1452 may be connected to the first body 141 by any one or more of riveting, gluing, or bolting, for example.

According to the embodiment of the present disclosure, the rotation axes of the shaft hole fitting structures 1430 in the two connecting members 143 disposed at both ends of the same first body 141 are parallel to each other, and the other portions except for the shaft hole fitting structures 1430 may be mirror images of each other with respect to a perpendicular plane of a line segment connecting both ends of the first body 1 (see the illustration of fig. 4A). According to the embodiment of the present disclosure, the directions of the rotation axes of the shaft hole matching structures 1430 of the two connecting members 143 disposed at the two ends of the same first body 141 are parallel to each other, so that when the adjacent second bodies 142 are folded, the adjacent second bodies 142 can be rotated in two planes which are parallel to each other but not intersecting each other.

Fig. 5 schematically shows a perspective view of the bottom support frame 111 in the drone 1 according to an embodiment of the present disclosure.

As shown in fig. 1C and 5, the bottom support frame 111 may be formed by welding or connecting bent pipes, for example, and has a concave structure as a whole, and goods (for example, a basket 2 matched with the receiving structure 11) can be placed therein. The bottom support frame 111 is connected at an upper portion to a circumferential support frame 112 and at a lower portion to the landing gear. The bottom support frame 111 is of a concave structure, so that goods can be loaded; since the bottom support frame 111 has a certain height and is connected to the undercarriage through the lower portion, the height of the undercarriage is reduced.

The bottom support frame 111 may include at least two first beams 1121 and at least one second beam 1122. Each of the at least two first beams 1121 extends in the first direction, and both ends of each first beam 1121 are connected to the circumferential support frame 112. Each second beam 1122 of the at least one second beam 1122 extends in the second direction, wherein each second beam 1122 is connected to at least the at least two first beams 1121. Wherein the first direction is different from the second direction.

According to an embodiment of the present disclosure, the first direction may be parallel to the fuselage end-to-end line direction of the unmanned aerial vehicle 1. In this way, the extending direction of the first beam 1121 (which may be referred to as a longitudinal beam, for example) is parallel to the direction of the head-to-tail line of the body of the unmanned aerial vehicle 1, which helps to reduce the flight resistance of the unmanned aerial vehicle 1. The second direction may be perpendicular to the first direction. When the first direction is parallel to the end-to-end line direction of the unmanned aerial vehicle 1, the second direction is perpendicular to the end-to-end line direction of the unmanned aerial vehicle 1, and the second beam 1122 may also be referred to as a cross beam.

The bottom support frame 111 further comprises a limiting frame 1123 connected to at least the at least two first beams 1121; wherein the spacing frame 1123 is higher than the bottom of the bottom support frame (20). The limiting frame 23 is used for limiting and stabilizing goods (for example, a basket matched with the limiting frame 23) placed in the accommodating structure 111. The limiting frame 23 is connected to at least each of the at least two first beams 1121 through a connecting plate. The position relationship between the position limiting frame 1123 and the first beam 1121 and/or the second beam 1122 can be adjusted by connecting the connecting plates.

According to the disclosed embodiment, the accommodating structure 11 may be a rectangular frame, for example, the length of the accommodating structure 11 in the direction of the line connecting the head and the tail of the unmanned aerial vehicle 1 is greater than the length in the direction perpendicular to the line connecting the head and the tail of the unmanned aerial vehicle 1. Thus, the bottom support frame 111 may form a mechanism that is elongated in the fore-aft direction, thereby reducing drag.

It should be noted that, in the example of fig. 2A and 2B, the extending direction (i.e., the first direction) of the first beam 1121 is perpendicular to the second beam 1122 (i.e., the second direction) is merely an example. In practical applications, the first direction and the second direction may have other included angles. For example, the second beam 1122 may be a cross beam and connected to the first beam 1121.

Fig. 6A schematically shows a schematic view of a contact of a basket fixing structure 13 in a drone 1 with a basket 2 according to an embodiment of the present disclosure. Fig. 6B schematically illustrates a schematic view of the basket securing structure 13 in the drone 1 not in contact with the basket 2 according to an embodiment of the present disclosure.

According to an embodiment of the present disclosure, the fuselage body 10 further comprises at least one basket securing structure 13. The at least one basket securing structure 13 is mounted to the circumferential support frame 112.

Each of the at least one basket securing structure 13 includes a first portion 131 and a second portion 132 that are relatively rotatable, wherein the first portion 131 is connected with the receiving structure 11, and the second portion 132 is configured to be detachably contacted with the external object. For example, the second portion 132 may be a snap. In this way, second portion 132 rotates with respect to first portion 131 towards the inside of containment structure 11 to trap basket 2 when it is desired to trap basket 2, and second portion 132 rotates with respect to first portion 131 towards the outside of containment structure 11 when it is desired to unload.

Fig. 7A schematically shows an installation position schematic of the power battery carrying structure 20 in the unmanned aerial vehicle 1 according to the embodiment of the present disclosure.

With reference to fig. 1B and 7A, according to an embodiment of the present disclosure, the unmanned aerial vehicle 1 includes at least two power battery carrying structures 20, the at least two power battery carrying structures 20 being symmetrically disposed at the periphery of the accommodating structure 11 with respect to a vertical line passing through the center of gravity of the fuselage main body 10.

In particular, the drone 1 comprises two power battery carrying structures 20. The two power battery carrying structures 20 are symmetrically arranged at the periphery of the accommodating structure 11. Specifically, each of the two power cell carrying structures 20 is disposed between the circumferential support frame 112 and the bottom support frame 111.

Fig. 7B schematically illustrates a three-dimensional structure of the power battery carrying structure 20 according to the embodiment of the present disclosure.

Referring to fig. 7B, the power battery carrying structure 20 may include a first support structure 220a and a second support structure 220B. Wherein the first support structure 220a is connected to the bottom support frame 111 and the second support structure 220b is connected to the circumferential support frame 112. A receiving area 200 is formed between the first support structure 220a and the second support structure 220 b. The power battery 201 is placed in the receiving area 200.

According to an embodiment of the present disclosure, the power battery carrying structure 20 is used for placing the power battery 201. This power battery bearing structure 20 for example installs in the outward flange of the holding structure 11 of unmanned aerial vehicle 1, and then opens the region of holding structure 11 top in unmanned aerial vehicle 1, for getting goods from unmanned aerial vehicle 1 top and putting goods and facilitating, is favorable to alleviateing the length of power cord simultaneously, alleviates unmanned aerial vehicle 1 dead weight.

Fig. 8A schematically shows a structural view of the avionics bay 40 in the drone 1 according to an embodiment of the present disclosure. Fig. 8B schematically shows a structure of an avionics bay body 420 of the avionics bay 40 in fig. 8A.

As shown in fig. 1B, 1D, 8A, and 8B, the avionics bay 40 is disposed below the bottom support frame 111 on a vertical line at the center of gravity of the fuselage main body 10. The avionics bay 40 is used to install an avionics system.

According to an embodiment of the present disclosure, avionics pod 40 may include a pod door 410 and an avionics pod body 420. The avionics pod 420 includes a pod opening 422 and a pod connection structure 421. Wherein the cabin opening 422 is located at an upper portion of the avionics cabin 420. The hatch 410 is removably attached to the upper portion of the avionics bay body 420 and cooperates with the bay opening 422. The cabin connection structure 421 is connected to the main body 10 of the unmanned aerial vehicle 1, for example, the cabin connection structure 421 is connected to the bottom support frame 111 (see fig. 1D).

According to an embodiment of the present disclosure, the edge of the hatch 410 and the edge of the cabin opening 422 comprise cooperating sealing structures. In this way, the avionics bay 40 is hermetically designed, and the waterproof and rainproof performance of the avionics bay 40 is achieved.

According to an embodiment of the present disclosure, the cabin connection structure 421 comprises a shock absorbing device 4211. The damper 4211 may be, for example, a damper ball. For example, four vibration-damping balls may be bolted to a mounting plate in the body 10, and the vibration-damping balls may be disposed above the mounting plate of the body 10, so that vibration-damping of the entire avionics bay 40 may be achieved by squeezing the vibration-damping balls.

According to an embodiment of the present disclosure, the avionics compartment body 420 comprises at least one through hole 423, the at least one through hole 423 being configured for passing through at least one cable plug of the avionics system. According to an embodiment of the present disclosure, the at least one through hole 423 is disposed on a non-windward side of the avionics cabin body 420. The non-windward side of the avionics bay body 420 refers to a non-windward side determined in the direction of the end-to-end line of the unmanned aerial vehicle 1 when the avionics bay 40 is installed in the unmanned aerial vehicle 1. Like this, when unmanned aerial vehicle 1 flies under the condition of rainy, can avoid the rainwater to the influence of cable socket, reach rainproof effect.

Fig. 9 schematically shows a structural schematic view of the positioning device mounting structure 30 in the unmanned aerial vehicle 1 according to the embodiment of the present disclosure.

Referring to fig. 1A and 9, according to an embodiment of the present disclosure, the positioning device mounting structure 30 may be disposed above the circumferential support frame 112, on one side of the accommodating structure 11.

Specifically, the positioning device mounting structure 30 includes a pole structure 310, a carrier plate 320, and a fixing member 330. The first end of the upright structure 310 is connected to a connector 143. A load plate 320 is attached to the second end of the upright structure 310. The fixing member 330 can connect the upright structure 310 and the connecting member 143.

The pole structure 310 is a rod-like structure having a length, the pole structure 310 having, for example, two ends. A first of the two ends is secured to the connector 143, for example by a fastener 330, to effect a mounting securement of the positioning device mounting structure 30. Wherein the upright structure 310 may be perpendicular to the connecting element 143, such that a second end opposite the first end is e.g. remote from the connecting element 11. In addition, a carrier plate 320 is attached to the second end of the upright structure 310, the carrier plate 320 being used, for example, for mounting the positioning device 301. In the example of FIG. 9, the positioning device 301 may include both GPS and RTK.

The positioning device mounting structure 30 of the embodiment of the present disclosure can be directly fixed on the main body 10 of the unmanned aerial vehicle 1, and does not need to be fixed on the main body of the unmanned aerial vehicle 1 through other separate pipe clamp structures. That is, the connected mode of positioner mounting structure 30 and unmanned aerial vehicle 1's fuselage of this disclosed embodiment is comparatively brief, is favorable to alleviateing the weight of unmanned aerial vehicle 1 self, and is favorable to the installation to practice thrift the cost.

Those skilled in the art will appreciate that various combinations and/or combinations of features recited in the various embodiments and/or claims of the present disclosure can be made, even if such combinations or combinations are not expressly recited in the present disclosure. In particular, various combinations and/or combinations of the features recited in the various embodiments and/or claims of the present disclosure may be made without departing from the spirit or teaching of the present disclosure. All such combinations and/or associations are within the scope of the present disclosure.

The embodiments of the present disclosure have been 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 separately above, this does not mean that the measures in the embodiments cannot be used in advantageous combination. The scope of the disclosure is defined by the appended claims and equivalents thereof. Various alternatives and modifications can be devised by those skilled in the art without departing from the scope of the present disclosure, and such alternatives and modifications are intended to be within the scope of the present disclosure.

Claims (10)

1. An unmanned aerial vehicle fuselage, its characterized in that includes:

fuselage body (10) comprising a containment structure (11) and at least one cantilever (12), wherein:

the accommodating structure (11) comprises a bottom supporting frame (111) and a circumferential supporting frame (112), the bottom supporting frame (111) is positioned below the circumferential supporting frame (112), and the bottom supporting frame (111) and the circumferential supporting frame (112) are connected to form an accommodating space of the accommodating structure (11);

a first end of each cantilever arm (12) of the at least one cantilever arm (12) is connected to the accommodating structure (11), and a second end opposite to the first end extends in a direction away from the accommodating structure (11).

2. The unmanned aerial vehicle fuselage of claim 1, wherein the fuselage body (10) comprises at least three arms (14), wherein the at least three arms (14) are staggered two by two, and wherein both ends of each arm (14) of the at least three arms (14) extend beyond a staggered area (15), wherein the staggered area (15) is an area formed by staggering two by two the at least three arms (14); wherein:

the portion of the at least three arms (14) located inside the staggered area (15) constitutes the circumferential support frame (112);

the portion of the at least three arms (14) outside the intersection region (15) constitutes the at least one boom (12).

3. The drone fuselage of claim 2, wherein the at least three booms (14) includes four booms (14).

4. The drone fuselage of claim 2 or 3, wherein each horn (14) comprises:

a first body (141);

two second bodies (142); and

two connecting pieces (143) respectively arranged at two ends of the first body (141);

wherein the first body (141) and each of the two second bodies (142) are foldably connected by one of the two connectors (143);

the first body (141) constitutes a portion of each horn (14) belonging to the circumferential support frame (112), and the two second bodies (142) constitute a portion of each horn (14) belonging to the at least one boom (12).

5. The drone fuselage of claim 4, wherein the connector (143) comprises:

a first frame structure (1410), the first frame structure (1410) including a first clamping member (1411) and a first opening (1412); and

a second frame structure (1420) connected to the first frame structure (1410), the second frame structure (1420) including a second clamping member (1421) and a second opening (1422), the second opening (1422) being oriented differently from the first opening (1412);

wherein the first frame structure (1410) is configured to place an end of one of the two first bodies (141) via the first opening (1412), and the second frame structure (1420) is configured to place an end of the other of the two first bodies (141) via the second opening (1422);

wherein at least one of the first gripping member (1411) and the second gripping member (1421) is configured to rotatably connect with the second body (142).

6. The drone fuselage of claim 4, wherein the connector (143) comprises:

a fixation portion (1431) comprising at least one first rotation engagement structure (14301);

at least one movable part (1432), wherein the movable part (1432) comprises a second rotation matching structure, wherein the second rotation matching structure is matched and connected with the first rotation matching structure (14301) to form a shaft hole matching structure (1430), so that the movable part (1432) is rotatably connected with the fixed part (1431) through the shaft hole matching structure (1430);

wherein the fixed part (1431) is configured to be connected with the first body (141) and the movable part (1432) is configured to be connected with the second body (142); an included angle between a rotation axis of the shaft hole matching structure (1430) and a first plane is an acute angle, wherein the first plane is perpendicular to a direction pointing to the first body (141) from the fixing part (1431).

7. The unmanned aerial vehicle fuselage of claim 1, further comprising:

and the control system mounting structure is arranged on the periphery of the accommodating structure (11).

8. The drone fuselage of claim 7, wherein the control system mounting structure includes:

at least two power battery carrying structures (20) are arranged symmetrically with respect to a vertical line passing through the center of gravity of the fuselage body (10) at the periphery of the receiving structure (11).

9. The drone fuselage of claim 7, wherein the control system mounting structure includes:

an avionics pod (40) disposed below the bottom support frame (111).

10. Unmanned aerial vehicle (1), characterized in that, includes the unmanned aerial vehicle fuselage of any one of claims 1-9.

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