UAV fuselage and UAV

Abstract

The present disclosure provides a drone fuselage. The drone fuselage comprises a fuselage body (10). The fuselage body (10) comprises a containing structure (11) and at least one cantilever (12). The containing structure (11) comprises a bottom support frame (111) and a circumferential support frame (112), wherein the bottom support frame (111) is located below the circumferential support frame (112), and the bottom support frame (111) and the circumferential support frame (112) are connected to form a containing space of the containing structure (11). A first end of each cantilever (12) in the at least one cantilever (12) is connected to the containing structure (11), and a second end opposite to the first end extends in a direction away from the containing structure (11). The present disclosure provides a drone (1) comprising the drone fuselage.

Description

Technical Field

[0001] The present disclosure relates to the field of warehousing and logistics, and more specifically, to a drone fuselage and a drone. Background Art

[0002] In current logistics drones, the middle part of the fuselage is the main structure of the fuselage, and the cantilever extends outward from the center of the fuselage. The motor is installed on the outer end of the cantilever to control the rotation of the propeller. The middle part of the fuselage is generally used to install avionics equipment such as flight control, resulting in the cargo basket usually being placed under the fuselage. In this way, loading and unloading of goods need to be done under the fuselage, and due to the volume size under the fuselage, the cargo basket is generally small. Summary of the invention

[0003] In view of this, the present disclosure provides a drone fuselage and a drone, wherein the middle portion of the drone fuselage is used to place a cargo basket, and cargo can be picked up or unloaded from above the drone.

[0004] The present disclosure provides a drone fuselage. The drone fuselage includes a fuselage body. The fuselage body includes a housing structure and at least one cantilever. The housing structure includes a bottom support frame and a circumferential support frame, wherein the bottom support frame is located below the circumferential support frame, and the bottom support frame is connected to the circumferential support frame to form a housing space of the housing structure. The first end of each cantilever of the at least one cantilever is connected to the housing structure, and the second end opposite to the first end extends in a direction away from the housing structure.

[0005] According to an embodiment of the present disclosure, the fuselage body includes at least three arms, the at least three arms are staggered in pairs, and both ends of each of the at least three arms extend outside the staggered area, wherein the staggered area is an area formed by the at least three arms staggered in pairs. Parts of the at least three arms located within the staggered area constitute the circumferential support frame. Parts of the at least three arms located outside the staggered area constitute the at least one cantilever.

[0006] According to an embodiment of the present disclosure, the at least three arms include four arms.

[0007] According to an embodiment of the present disclosure, each of the arms comprises a first body, two second bodies and two connecting members. The two connecting members are respectively arranged at both ends of the first body. The first body and each of the two second bodies are foldably connected through one of the two connecting members. The first body constitutes a part of the circumferential support frame in each of the arms, and the two second bodies constitute a part of the at least one cantilever in each of the arms.

[0008] According to an embodiment of the present disclosure, the connecting member includes a first frame structure and a second frame structure. The first frame structure includes a first clamping component and a first opening. The second frame structure is connected to the first frame structure. The second frame structure includes a second clamping component and a second opening, and the second opening is oriented differently from the first opening. 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. At least one of the first clamping component and the second clamping component is configured to be rotatably connected to the second body.

[0009] According to an embodiment of the present disclosure, the connecting member includes a fixed portion and at least one movable portion. The fixed portion includes at least one first rotational matching structure. The movable portion includes a second rotational matching structure, wherein the second rotational matching structure is matched and connected with the first rotational matching structure to form an axial hole matching structure, so that the movable portion is rotatably connected to the fixed portion through the axial hole matching structure. The fixed portion is configured to be connected to the first body, and the movable portion is configured to be connected to the second body; the angle between the rotation axis of the axial hole matching structure and the first plane is an acute angle, wherein the first plane is perpendicular to the direction pointing from the fixed portion to the first body.

[0010] According to an embodiment of the present disclosure, the drone fuselage further includes a control system installation structure. The control system installation structure is arranged outside the accommodating structure.

[0011] According to an embodiment of the present disclosure, the control system installation structure includes at least two power battery bearing structures. The at least two power battery bearing structures are symmetrically arranged on the periphery of the accommodating structure relative to a vertical line passing through the center of gravity of the fuselage body.

[0012] According to an embodiment of the present disclosure, the control system installation structure includes an avionics cabin. The avionics cabin is arranged below the bottom support frame.

[0013] According to an embodiment of the present disclosure, the control system installation structure includes a positioning device installation structure. The positioning device installation structure is arranged above the circumferential support frame.

[0014] According to an embodiment of the present disclosure, the fuselage body further includes at least one cargo basket fixing structure. The at least one cargo basket fixing structure is installed on the circumferential support frame.

[0015] Another aspect of the present disclosure also provides a drone, which includes the drone body as described above.

[0016] According to an embodiment of the present disclosure, a containing structure can be set in the middle part of the drone fuselage to carry cargo, and the control system of the drone can be installed on the periphery of the containing structure, so that cargo can be picked up or unloaded from above the drone, which is convenient for human-machine operation. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] The above and other objects, features and advantages of the present disclosure will become more apparent through the following description of the embodiments of the present disclosure with reference to the accompanying drawings, in which:

[0018] Figure 1A A schematic diagram of a drone containing a cargo basket according to an embodiment of the present disclosure is schematically shown;

[0019] Figure 1B A schematic diagram schematically shows a method of taking out a cargo basket from above a drone according to an embodiment of the present disclosure;

[0020] Figure 1C The three-dimensional structure diagram of a drone according to an embodiment of the present disclosure is schematically shown;

[0021] Figure 1D A top view of a drone according to an embodiment of the present disclosure is schematically shown;

[0022] Figure 2A A schematic diagram schematically shows a schematic diagram of a drone in a "well"-shaped fuselage frame in an unfolded state according to an embodiment of the present disclosure;

[0023] Figure 2B A schematic diagram schematically shows a folding process of the arms in a "well"-shaped fuselage frame of a drone according to an embodiment of the present disclosure;

[0024] Figure 2C A schematic diagram showing a drone with its arms in a "well"-shaped fuselage frame folded completely according to an embodiment of the present disclosure is shown;

[0025] Figure 3A Schematically shows an embodiment of the present disclosure. Figure 2C The plane view of the folded arms obtained from the middle A perspective;

[0026] Figure 3B Schematically shows Figure 3A A three-dimensional structural diagram of the drone with its arms in an unfolded state;

[0027] Figure 3C Schematically shows Figure 3B The three-dimensional structure diagram of the connector shown in part c

[0028] Figure 3D Schematically shows Figure 3B The three-dimensional structure diagram of the connecting member shown in part d;

[0029] Figure 4A Schematically shows another embodiment of the present disclosure. Figure 2C The folded view of the aircraft arms obtained from the middle A perspective;

[0030] Figure 4B Schematically shows Figure 4A An enlarged view of the connecting member when the first body and the second body of the middle machine arm are in a folded state;

[0031] Figure 4C Schematically shows Figure 4A and Figure 4B A three-dimensional structural diagram of the connecting parts in FIG.

[0032] Figure 5 A three-dimensional structural diagram of a bottom support frame in a drone according to an embodiment of the present disclosure is schematically shown;

[0033] Fig. 6A A schematic diagram schematically shows the contact between the cargo basket fixing structure and the cargo basket in the drone according to an embodiment of the present disclosure;

[0034] Figure 6B A schematic diagram schematically shows that the cargo basket fixing structure in the drone according to an embodiment of the present disclosure is not in contact with the cargo basket.

[0035] Fig. 7A Schematically shows the installation position of the power battery bearing structure in the drone according to an embodiment of the present disclosure;

[0036] Figure 7B The three-dimensional structure of the power battery supporting structure according to an embodiment of the present disclosure is schematically shown;

[0037] Fig. 8A The structure diagram of the avionics cabin in the UAV according to the embodiment of the present disclosure is schematically shown;

[0038] Figure 8B Schematically shows Fig. 8A The structural diagram of the avionics compartment of the avionics compartment; and

[0039] Fig. 9 The following is a schematic diagram showing the installation of a positioning device installation structure in a drone according to an embodiment of the present disclosure. DETAILED DESCRIPTION

[0040] Hereinafter, embodiments of the present disclosure will be described with reference to the accompanying drawings. However, it should be understood that these descriptions are exemplary only and are not intended to limit the scope of the present disclosure. In the following detailed description, for ease of explanation, many specific details are set forth to provide a comprehensive understanding of the embodiments of the present disclosure. However, it is apparent that one or more embodiments may also be implemented without these specific details. In addition, in the following description, descriptions of known structures and technologies are omitted to avoid unnecessary confusion of the concepts of the present disclosure.

[0041] The terms used herein are only for describing specific embodiments and are not intended to limit the present disclosure. The terms "comprise", "include", etc. used herein indicate the existence of the features, steps, operations and / or components, but do not exclude the existence or addition of one or more other features, steps, operations or components.

[0042] All terms (including technical and scientific terms) used herein have the meanings commonly understood by those skilled in the art, unless otherwise defined. It should be noted that the terms used herein should be interpreted as having a meaning consistent with the context of this specification, and should not be interpreted in an idealized or overly rigid manner.

[0043] In the case of using expressions such as "at least one of A, B, and C, etc.", it should generally be interpreted in accordance with the meaning of the expression generally understood by those skilled in the art (for example, "a system having at least one of A, B, and C" should include but is not limited to a system having A alone, B alone, C alone, A and B, A and C, B and C, and / or A, B, C, etc.). In the case of using expressions such as "at least one of A, B, or C, etc.", it should generally be interpreted in accordance with the meaning of the expression generally understood by those skilled in the art (for example, "a system having at least one of A, B, or C" should include but is not limited to a system having A alone, B alone, C alone, A and B, A and C, B and C, and / or A, B, C, etc.).

[0044] In the context of the present disclosure, when a component is referred to as being located / connected to (being "on") another component, the component may be directly located / connected to (being "on") the other component, or other components may be present between them. In addition, if a component is located "on" another component in one orientation, the component may be located "under" the other component when the orientation is reversed. When a component is referred to as being located "between" two other components, the component may be directly located between the two other components, or other components may be present between the two other components in addition to the component.

[0045] The disclosed embodiments provide a drone fuselage and a drone including the drone fuselage. The drone fuselage includes a fuselage body. The fuselage body includes a housing structure and at least one cantilever. The housing structure includes a bottom support frame and a circumferential support frame, wherein the bottom support frame is located below the circumferential support frame, and the bottom support frame is connected to the circumferential support frame to form a housing space for the housing structure. The first end of each of the at least one cantilever is connected to the housing structure, and the second end opposite to the first end extends in a direction away from the housing structure. A motor can be installed at the second end of each of the at least one cantilever, and a propeller is installed on the motor, wherein the rotation of the propeller is controlled by the motor.

[0046] According to an embodiment of the present disclosure, the control system installation structure is arranged on the periphery of the accommodating structure. Among them, the control system installation structure may include a power battery bearing structure, an avionics cabin, and / or a positioning device installation structure. The power battery bearing structure can be used to install the power battery. The avionics cabin can be used to install the avionics system, which may include flight control, IMU, communication module, and radio module. The positioning device installation structure can be used to install a positioning device, which may be, for example, GPS or RTK (Real-Time Kinematic) and other related equipment.

[0047] The control system installation structure is arranged at the periphery of the accommodating structure, for example, it can be installed at the corresponding position of the circumferential support frame and / or the bottom support frame according to the design and use requirements.

[0048] According to one embodiment of the present disclosure, the circumferential support frame may be composed of a portion within an interlaced area formed by staggering at least three arms in pairs, and the at least one cantilever may be composed of a portion of the at least three arms located outside the interlaced area formed by staggering in pairs. Specifically, the fuselage body may include at least three arms, the at least three arms are staggered in pairs, and both ends of each of the at least three arms extend outside the interlaced area, wherein the interlaced area is an area formed by staggering the at least three arms in pairs. The portion of the at least three arms located within the interlaced area constitutes the circumferential support frame. The portion of the at least three arms located outside the interlaced area constitutes the at least one cantilever. In this way, a portion of the at least three arms can be used as a circumferential support frame of the accommodating structure, and another portion can be used as at least one cantilever, thereby simplifying the structure of the drone fuselage.

[0049] According to an embodiment of the present disclosure, the at least three arms may be four arms. The four arms are staggered in pairs to form a "well"-shaped frame. The "well"-shaped frame constitutes the frame of the fuselage body.

[0050] According to some embodiments of the present disclosure, each arm of the drone can be folded to reduce the size of the drone, thereby facilitating the storage of the drone.

[0051] Figure 1A A schematic diagram of a drone 1 containing a cargo basket 2 according to an embodiment of the present disclosure is schematically shown. Figure 1B A schematic diagram of taking out a cargo basket 2 from above a drone 1 according to an embodiment of the present disclosure is schematically shown.

[0052] like Figure 1A and Figure 1B As shown, the cargo basket 2 can be placed in the middle part of the fuselage of the drone 1, and the cargo basket 2 can be taken out from the top of the drone 1.

[0053] The drone 1 includes a fuselage body 10, wherein the fuselage body 10 includes a housing structure 11 and at least one cantilever 12. The cargo basket 2 is placed in the housing structure 11. The upper portion of the housing structure 11 has a passage that can provide access to the cargo basket 2. For example, the upper portion of the housing structure 11 is an opening, so that the cargo basket 2 can be taken out or loaded in from the upper portion of the housing structure 11. Alternatively, the upper portion of the housing structure 11 may also have other structures such as an openable door. Figure 1A and Figure 1B In the schematic diagram, the drone 1 includes eight cantilevers 12. The first end of the cantilever 12 is connected to the accommodating structure 11, and a motor (eg, a brushless DC motor) is installed at the second end away from the accommodating structure 11. A propeller is installed on the motor.

[0054] The drone 1 may also include at least two power batteries 201. Figure 1A and Figure 1B In the schematic diagram, another power battery 201 is installed on the other side opposite to the power battery 201 visible in the figure. The at least two power batteries 201 are respectively installed in one of the corresponding at least two power battery supporting structures 20. The at least two power battery supporting structures 20 can be referred to below for Fig. 7A and Figure 7B According to an embodiment of the present disclosure, the at least two power battery supporting structures 20 are symmetrically arranged on the periphery of the accommodating structure 11 relative to a vertical line passing through the center of gravity of the fuselage body 10 (see Figure 1C The at least two power batteries 201 are fixed in the fuselage body 10 by the at least two power battery supporting structures 20 , and the at least two power batteries 201 are symmetrical with respect to a vertical line passing through the center of gravity of the fuselage body 10 .

[0055] The drone 1 may further include a positioning device 301. The positioning device 301 may be, for example, a GPS or RTK (Real-Time Kinematic) or other related equipment. According to an embodiment of the present disclosure, the positioning device 301 is installed on the positioning device installation structure 30 (see below). Fig. 9 The positioning device installation structure 30 may be arranged at the edge of the accommodating structure 11, so that the positioning device 301 is fixed at the edge of the accommodating structure 11. Figure 1A and Figure 1B In the diagram, the drone 1 includes two positioning devices 301. The line connecting the two positioning devices 301 is parallel to the line connecting the front and rear of the fuselage of the drone 1. According to the embodiment of the present disclosure, the two positioning devices 301 are arranged at the edge of the accommodating structure 11, which can avoid colliding with the positioning devices 301 when loading and unloading the cargo basket 2 from above the drone 1.

[0056] The drone 1 may further include an avionics system. The avionics system may be installed inside the avionics compartment 40. The avionics compartment 40 may be of an integrated sealed design. According to an embodiment of the present disclosure, the avionics compartment 40 may be disposed at the bottom of the accommodating structure 11, on a vertical line passing through the center of gravity of the fuselage body 10, so that the flight control may be installed on a vertical line of the center of gravity of the fuselage body 10. According to an embodiment of the present disclosure, the avionics system and the power battery 201 of the drone 1 may be arranged in different positions, respectively, so that the avionics system can avoid the hidden dangers of the flammable and explosive power battery 201.

[0057] According to an embodiment of the present disclosure, the fuselage body 10 of the drone 1 may further include at least one cargo basket fixing structure 13 (see below). Fig. 6A and Figure 6B ). One end of each of the at least one cargo basket fixing structure 13 can be disposed on the accommodating structure 11, and the other end can be detachably contacted with the cargo 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 cargo basket 2 is to be taken out of the accommodating structure 11, the cargo basket fixing structure 13 is separated from the cargo basket 2, and does not affect the disassembly of the cargo basket 2.

[0058] Figure 1A and Figure 1BThe structural form of the drone 1 shown avoids concentrating the control system and the fixed end of the cantilever 12 in the middle of the fuselage of the drone 1, so that there is a large space in the middle of the fuselage of the drone 1 for installing the cargo basket. The accommodating structure 11 includes a downwardly recessed accommodating space, and the cargo basket is placed in the accommodating structure 11, which basically coincides with the center of gravity position of the entire drone 1, so that the center of gravity position of the drone 1 will not change significantly when fully loaded and unloaded. Specifically, when the drone 1 is not loaded with the cargo basket, the center of gravity of the drone 1 is located below the geometric center of the drone 1. When the drone 1 is loaded with the cargo basket, the center of gravity of the drone 1 is also located slightly below the geometric center of the drone 1, so the center of gravity position of the drone 1 remains basically unchanged. In this way, the flight control of the drone 1 is facilitated, which is beneficial to the stability of the flight of the drone 1.

[0059] It should be noted that Figure 1A and Figure 1B The drone 1 shown is only an example of the structure of a drone that can be used in the embodiment 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 embodiment of the present disclosure cannot be used in drones of other structural forms.

[0060] Figure 1C The three-dimensional structure diagram of the drone 1 according to an embodiment of the present disclosure is schematically shown. Figure 1D A top view of a drone 1 according to an embodiment of the present disclosure is schematically shown.

[0061] like Figure 1C and Figure 1D As shown, from a structural division perspective, the drone 1 includes a containing structure 11 and at least one cantilever 12 (the specific example in the figure is 8 cantilevers 12). The containing structure 11 includes a bottom support frame 111 and a circumferential support frame 112. The bottom support frame 111 is connected to the bottom of the circumferential support frame 112. On the one hand, the bottom support frame 111 can serve as the bottom of the containing structure 11 for carrying the cargo basket; on the other hand, it can also play a role in connecting and stabilizing the circumferential support frame 12 to enhance the structural stability of the fuselage body 10. The first end of each cantilever 12 in the at least one cantilever 12 is connected to the containing structure 11, and the second end opposite to the first end extends in a direction away from the containing structure 11.

[0062] 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 shown in the figure). The four arms 14 are staggered in pairs, and the two ends of each of the four arms 14 extend outside the staggered area 15, wherein the staggered area 15 is an area formed by the four arms 14 staggered in pairs. Among them, the parts of the four arms 14 located within the staggered area 15 constitute the circumferential support frame 112. The parts of the four arms 14 located outside the staggered area 15 constitute the at least one cantilever 12 (therefore, 8 cantilevers 12 are obtained). Among them, the bottom support frame 111 is located in the space where the staggered area 15 is located, and is connected to the bottom of the circumferential support frame 112. The connection and combination of the bottom support frame 111 and the circumferential support frame 112 form the accommodating structure 11.

[0063] like Figure 1C and Figure 1D As shown, the fuselage body 10 of the drone 1 includes four arms 14 staggered in pairs, forming a "well"-shaped fuselage frame. The accommodating structure 11 can be arranged in the middle of the "well"-shaped fuselage frame.

[0064] According to an embodiment of the present disclosure, each arm 14 of the drone 1 can be folded. Figure 2A to Figure 2C 's hint.

[0065] Figure 2A The schematic diagram schematically shows a schematic diagram of the arm 14 in the "well"-shaped frame of the drone 1 in an expanded state according to an embodiment of the present disclosure; Figure 2B The figure schematically shows a schematic diagram of the arm 14 in the "well"-shaped frame of the drone 1 in the folding process according to an embodiment of the present disclosure. Figure 2C The figure schematically shows a schematic diagram of a folded machine arm 14 in a “well”-shaped fuselage frame of a drone 1 according to an embodiment of the present disclosure.

[0066] like Figure 2A to Figure 2C As shown, when the drone 1 is stored, the two cantilevers 12 in each arm 14 can be folded toward the interlaced area 15 to reduce the space of the drone 1.

[0067] Specifically, Figure 2AAs shown, according to an embodiment of the present disclosure, each of the arms 14 may include a first body 141, two second bodies 142 and two connecting members 143. The two connecting members 143 are respectively arranged at both ends of the first body 141. The first body 141 and each of the two second bodies 142 are foldably connected through one of the two connecting members 143. The first body 141 constitutes a part of the circumferential support frame 112 in each of the arms 14, and the two second bodies 142 constitute a part of the at least one cantilever 12 in each of the arms 14. For example, as shown in the figure, each second body 142 may correspond to a cantilever 12.

[0068] Figure 3A Schematically shows an embodiment of the present disclosure. Figure 2C A plan view of the folded machine arm 14 obtained from the perspective of middle A. Figure 3B Schematically shows Figure 3A A three-dimensional structural diagram of the drone 1 in which the arms 14 are in an unfolded state.

[0069] like Figure 3A and 3B As shown, according to an embodiment of the present disclosure, the minimum distance between two second bodies 142 in the same arm 14 (i.e., two second bodies 142 respectively connected to the two ends of the same first body 141) in a direction perpendicular to the fuselage plane formed by the at least three arms 14 staggered in pairs is greater than zero. In this way, when the four arms 14 are assembled to form the "well"-shaped fuselage frame of the drone 1, the two adjacent second bodies 142 can be at different heights, and then the minimum distance between two adjacent second bodies 142 (i.e., two second bodies 142 folded toward each other) in a direction perpendicular to the fuselage plane can be greater than zero (such as Figure 3B In this way, when two adjacent second bodies 142 are folded relative to each other, they can avoid interfering with each other, thus avoiding the problems existing when the machine arms are folded relative to each other in the prior art.

[0070] Figure 3C Schematically shows Figure 3B Part c is a three-dimensional structural diagram of the connecting member 143. Figure 3D Schematically shows Figure 3B Part d is a three-dimensional structural diagram of the connecting member 143.

[0071] like Figure 3C and 3DAs shown, 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 clamping part 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 clamping part 1421 and a second opening 1422, and the second opening 1422 has a different orientation from the first opening 1412. The first frame structure 1410 places an end of a 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. The orientations of the first opening 1412 and the second opening 1422 are consistent with the directions of the two interlaced arms 14 (for example, perpendicular to each other).

[0072] At least one of the first clamping member 1411 and the second clamping member 1421 is rotatably connected to at least one second body 142. For example, at the staggered position of the two interlaced arms 14, one second body 142 is foldably connected to the first clamping member 1411, and the other second body 142 is foldably connected to the second clamping member 1421 (see Figure 3B (a partial enlarged view of part c or part d in FIG. 5 ).

[0073] Figure 3C and Figure 3D The difference is that Figure 3C The first clamping part 1411 of the connecting member 143 and the first opening 1412 are adjacent to each other, and the second clamping part 1421 and the second opening 1422 are adjacent to each other. Figure 3D The first clamping part 1411 of the middle connecting member 143 and the first opening 1412 are opposite to each other, and the second clamping part 1421 and the second opening 1422 are opposite to each other.

[0074] Specifically, Figure 3C As shown, according to one embodiment of the present disclosure, the first clamping part 1411 and the first opening 1412 are adjacent to each other, and the second clamping part 1421 and the second opening 1422 are adjacent to each other, so that when the second body 142 (i.e., the cantilever 12) is not folded, the second body 142 connected to the first clamping part 1411 and a first body 141 placed in the first frame structure 1410 through the first opening 1412 are perpendicular to each other, and the second body 142 connected to the second clamping part 1421 and another first body 141 placed in the second frame structure 1420 through the second opening 1422 are perpendicular to each other. Figure 3CThe first body 141 and the second body 142 connected by the connecting member 143 are at different heights (see Figure 3B (Part c).

[0075] like Figure 3D As shown, according to another embodiment of the present disclosure, the first clamping part 1411 and the first opening 1412 are opposite to each other, and the second clamping part 1421 and the second opening 1422 are opposite to each other. Thus, when the second body 142 (i.e., the cantilever 12) is not folded, the second body 142 connected to the first clamping part 1411 and a first body 141 placed in the first frame structure 1410 through the first opening 1412 are parallel to each other (for example, in opposite directions), and the second body 142 connected to the second clamping part 1421 and another first body 141 placed in the second frame structure 1420 through the second opening 1422 are parallel to each other (for example, in opposite directions). Figure 3D The first body 141 and the second body 142 connected by the connecting member 143 are at the same height (see Figure 3B (Part d in the figure).

[0076] Figure 4A Schematically shows another embodiment of the present disclosure. Figure 2C A folded view of the machine arm 14 obtained from the perspective of middle A.

[0077] like Figure 4A As shown, according to another embodiment of the present disclosure, the connecting member 143 may include a rotation axis with an acute angle to the first plane, wherein the first plane is perpendicular to the direction from the connecting member 143 to the first body 141, and each second body 142 can be rotated and folded around the rotation axis relative to the first body 141. Therefore, when the directions of the rotation axes of the two connecting members 143 connected to two adjacent second bodies 142 are parallel and the angle with the first plane is appropriately selected, the two adjacent second bodies 142 can rotate in parallel planes separated by a certain gap when folded relative to each other, in this way, the interference problem when the two adjacent second bodies 142 are folded relative to each other can be avoided.

[0078] Figure 4B Schematically shows Figure 4A An enlarged view of the connecting member 143 when the first body 141 and the second body 142 of the middle machine arm 14 are in a folded state; Figure 4C Schematically shows Figure 4A and Figure 4B A three-dimensional structural diagram of the connecting member 143 in FIG.

[0079] like Figure 4B and Figure 4CAs shown, according to an embodiment of the present disclosure, the connector 143 may include a fixed portion 1431 and at least one movable portion 1432. The fixed portion 1431 is connected to the first body 141, and each movable portion 1432 is connected to one of the at least one second body 142.

[0080] The fixing portion 1431 includes at least one first rotational matching structure 14301 .

[0081] Each of the at least one movable portion 1432 includes a second rotational matching structure, wherein the second rotational matching structure is matched and connected with one of the at least one first rotational matching structure 14301 to form an axis-hole matching structure 1430, so that each movable portion 1432 is rotatably connected to the fixed portion 1431 through the axis-hole matching structure 1430. The included angle a between the rotation axis of the axis-hole matching structure 1430 and the first plane is an acute angle, wherein the first plane is perpendicular to the direction from the fixed portion 1431 to the first body 141 (see Figure 4B ). Figure 4B In the illustration of FIG. 1 , the first plane is illustrated as a vertical plane for example only.

[0082] The first rotational matching structure 14301 may be one of the shaft or the hole in the shaft-hole matching structure 1430, and the second rotational matching structure is another part of the shaft-hole matching structure 1430 that matches the first rotational matching structure 14301. Figure 4A to Figure 4C The cooperation between the rotating shaft and the hole shown in the figure may also be other forms such as thread and screw hole connection, rivet connection, etc., as long as the relative rotation between the movable part 1432 and the fixed part 1431 can be achieved.

[0083] According to an embodiment of the present disclosure, the rotation axis of the shaft hole matching structure 1430 formed between the movable portion 1432 and the fixed portion 1431 is at an acute angle to the first plane rather than being parallel, so that the second body 142 connected to the movable portion 1432 can be rotated and folded in a plane at a certain acute angle to the first plane. The acute angle between the rotation axis of the rotating 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, in one embodiment, the acute angle a can be 1.5° to 4°.

[0084] According to an embodiment of the present disclosure, the fixing portion 1431 includes two frame structures 1450. Each of the two frame structures 1450 includes a first connection end 1451 and a second connection end 1452 that are arranged opposite to each other. The two frame structures 1450 are arranged alternately up and down. The first connection end 1451 includes at least one of the first rotational matching structures 14301. The second connection end 1452 is configured to be connected to the first body 141. The second connection end 1452 and the first body 141 can be connected by any one or more methods such as riveting, gluing or bolting.

[0085] According to the embodiment of the present disclosure, the rotation axes of the shaft-hole matching structures 1430 in the two connecting members 143 disposed at the two ends of the same first body 141 are parallel to each other, and the other parts except the shaft-hole matching structures 1430 can be mirror images of each other relative to the perpendicular midplane of the line segment connecting the two ends of the first body 1 (see Figure 4A According to an 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 both 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 parallel and non-intersecting planes.

[0086] Figure 5 The three-dimensional structure diagram of the bottom support frame 111 in the drone 1 according to an embodiment of the present disclosure is schematically shown.

[0087] Combination Figure 1C and Figure 5 As shown, the bottom support frame 111 can be formed by welding or connecting bent pipes, and the overall structure is a "concave" structure, and cargo (for example, a cargo basket 2 that matches the accommodating structure 11) can be placed in it. The upper part of the bottom support frame 111 is connected to the circumferential support frame 112, and the lower part can be connected to the landing gear. Since the bottom support frame 111 is a "concave" structure, it can carry cargo; since the bottom support frame 111 has a certain height and is connected to the landing gear through the lower part, the height of the landing gear is reduced.

[0088] 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 along a first direction, and both ends of each first beam 1121 are connected to the circumferential support frame 112. Each of the at least one second beam 1122 extends along a second direction, wherein each second beam 1122 is at least connected to the at least two first beams 1121. The first direction is different from the second direction.

[0089] According to an embodiment of the present disclosure, the first direction may be parallel to the direction of the front-to-rear line of the fuselage of the drone 1. In this way, the extension direction of the first beam 1121 (for example, it can be called a longitudinal beam) is parallel to the direction of the front-to-rear line of the fuselage of the drone 1, which helps to reduce the flight resistance of the drone 1. The second direction may be perpendicular to the first direction. When the first direction is parallel to the direction of the front-to-rear line of the drone 1, the second direction is perpendicular to the direction of the front-to-rear line of the drone 1, and the second beam 1122 may also be called a cross beam.

[0090] The bottom support frame 111 further comprises a limit frame 1123, which is at least connected to the at least two first beams 1121; wherein the limit frame 1123 is higher than the bottom of the bottom support frame (20). The limit frame 23 is used to limit and stabilize the goods (e.g., a basket matching the limit frame 23) placed in the accommodating structure 111. The limit frame 23 is at least connected to each of the at least two first beams 1121 through a connecting plate. Through the connection of the connecting plate, the positional relationship between the limit frame 1123 and the first beam 1121 and / or the second beam 1122 can be adjusted.

[0091] 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 head-to-tail line of the drone 1 is greater than the length in the direction perpendicular to the head-to-tail line of the drone 1. In this way, the bottom support frame 111 may form a slender structure along the head-to-tail line, thereby reducing flight resistance.

[0092] It should be noted that in Figure 2A and Figure 2B In the example, the extending direction of the first beam 1121 (i.e., the first direction) and the second beam 1122 (i.e., the second direction) being perpendicular to each other is only an example. In practical applications, the first direction and the second direction may also have other angles. For example, the second beam 1122 may be a cross beam connected to the first beam 1121.

[0093] Fig. 6A The schematic diagram schematically shows the contact between the cargo basket fixing structure 13 and the cargo basket 2 in the drone 1 according to the embodiment of the present disclosure. Figure 6B The schematic diagram schematically shows that the cargo basket fixing structure 13 in the drone 1 according to the embodiment of the present disclosure is not in contact with the cargo basket 2.

[0094] According to an embodiment of the present disclosure, the fuselage body 10 further includes at least one cargo basket fixing structure 13. The at least one cargo basket fixing structure 13 is installed on the circumferential support frame 112.

[0095] Each of the at least one cargo basket fixing structure 13 includes a first portion 131 and a second portion 132 that are relatively rotatable, wherein the first portion 131 is connected to the accommodating structure 11, and the second portion 132 is configured to be detachably in contact with the external object. For example, the second portion 132 may be a buckle. In this way, when the cargo basket 2 needs to be clamped, the second portion 132 rotates relative to the first portion 131 toward the inside of the accommodating structure 11 to clamp the cargo basket 2, and when unloading is required, the second portion 132 rotates relative to the first portion 131 toward the outside of the accommodating structure 11.

[0096] Fig. 7A FIG. 1 schematically shows the installation position of the power battery supporting structure 20 in the drone 1 according to an embodiment of the present disclosure.

[0097] Combination Figure 1B and Fig. 7A According to an embodiment of the present disclosure, the drone 1 includes at least two power battery supporting structures 20, and the at least two power battery supporting structures 20 are symmetrically arranged on the periphery of the accommodating structure 11 relative to a vertical line passing through the center of gravity of the fuselage body 10.

[0098] Specifically, the drone 1 includes two power battery bearing structures 20. The two power battery bearing structures 20 are symmetrically arranged at the periphery of the accommodating structure 11. Specifically, each of the two power battery bearing structures 20 is disposed between the circumferential support frame 112 and the bottom support frame 111.

[0099] Figure 7B The three-dimensional structure of the power battery supporting structure 20 according to an embodiment of the present disclosure is schematically shown.

[0100] refer to Figure 7B The power battery supporting structure 20 may include a first supporting structure 220a and a second supporting structure 220b. The first supporting structure 220a is connected to the bottom supporting frame 111, and the second supporting structure 220b is connected to the circumferential supporting frame 112. A receiving area 200 is formed between the first supporting structure 220a and the second supporting structure 220b. The power battery 201 is placed in the receiving area 200.

[0101] According to an embodiment of the present disclosure, the power battery carrying structure 20 is used to place the power battery 201. The power battery carrying structure 20 is, for example, installed on the outer edge of the accommodating structure 11 of the drone 1, thereby opening the area above the accommodating structure 11 in the drone 1, providing convenience for picking up and placing goods from above the drone 1, and at the same time helping to reduce the length of the power cord and reduce the weight of the drone 1.

[0102] Fig. 8AThe structure of the avionics compartment 40 in the drone 1 according to an embodiment of the present disclosure is schematically shown. Figure 8B Schematically shows Fig. 8A A structural diagram of the avionics compartment body 420 of the avionics compartment 40.

[0103] Combination Figure 1B , Figure 1D , Fig. 8A and Figure 8B As shown, the avionics compartment 40 is disposed below the bottom support frame 111 and is located on a vertical line where the center of gravity of the fuselage body 10 is located. The avionics compartment 40 is used to install an avionics system.

[0104] According to an embodiment of the present disclosure, the avionics cabin 40 may include a cabin door 410 and an avionics cabin body 420. The avionics cabin body 420 includes a cabin body opening 422 and a cabin body connection structure 421. The cabin body opening 422 is located at the upper part of the avionics cabin body 420. The cabin door 410 is detachably connected to the upper part of the avionics cabin body 420 and cooperates with the cabin body opening 422. The cabin body connection structure 421 is connected to the fuselage body 10 of the drone 1, for example, the cabin body connection structure 421 is connected to the bottom support frame 111 (see Figure 1D ).

[0105] According to an embodiment of the present disclosure, the edge of the hatch 410 and the edge of the cabin opening 422 include mutually matching sealing structures. In this way, the avionics cabin 40 is sealed to achieve waterproof and rainproof performance.

[0106] According to an embodiment of the present disclosure, the cabin connection structure 421 includes a shock absorbing device 4211. The shock absorbing device 4211 may be, for example, a shock absorbing ball, etc. For example, four shock absorbing balls may be connected to the mounting plate in the fuselage body 10 by bolts, and the shock absorbing balls are placed above the mounting plate of the fuselage body 10, so that the vibration of the entire avionics cabin 40 can be reduced by squeezing the shock absorbing balls.

[0107] According to an embodiment of the present disclosure, the avionics cabin body 420 includes at least one through hole 423, and the at least one through hole 423 is configured to allow at least one cable plug of the avionics system to pass through. According to an embodiment of the present disclosure, the at least one through hole 423 is arranged on the non-windward surface of the avionics cabin body 420. The non-windward surface of the avionics cabin body 420 refers to the non-windward surface determined by the head-to-tail connection direction of the drone 1 when the avionics cabin 40 is installed on the drone 1. In this way, when the drone 1 flies under rainy conditions, the influence of rain on the cable socket can be avoided, thereby achieving a rainproof effect.

[0108] Fig. 9The structural diagram of the positioning device installation structure 30 in the drone 1 according to the embodiment of the present disclosure is schematically shown.

[0109] refer to Figure 1A and Fig. 9 According to an embodiment of the present disclosure, the positioning device mounting structure 30 can be arranged above the circumferential support frame 112 and located on one side of the accommodating structure 11.

[0110] Specifically, the positioning device installation structure 30 includes a pole structure 310, a loading plate 320 and a fixing member 330. The first end of the pole structure 310 is connected to the connecting member 143. The loading plate 320 is connected to the second end of the pole structure 310. The fixing member 330 can connect the pole structure 310 and the connecting member 143.

[0111] The pole structure 310 is a rod-shaped structure with a certain length, and the pole structure 310 has two ends, for example. The first end of the two ends is fixed to the connecting member 143, for example, by a fixing member 330, so as to realize the installation and fixation of the positioning device installation structure 30. The pole structure 310 can be perpendicular to the connecting member 143, so that the second end opposite to the first end is, for example, far away from the connecting member 11. In addition, the second end of the pole structure 310 is connected to a carrier plate 320, and the carrier plate 320 is, for example, used to install the positioning device 301. Fig. 9 In the example, the positioning device 301 may include both GPS and RTK.

[0112] The positioning device installation structure 30 of the embodiment of the present disclosure can be directly fixed on the fuselage body 10 of the drone 1, and does not need to be fixed to the fuselage of the drone 1 through other separate pipe clamp structures. That is, the connection method between the positioning device installation structure 30 of the embodiment of the present disclosure and the fuselage of the drone 1 is relatively simple, which is conducive to reducing the weight of the drone 1 itself and saving installation costs.

[0113] It will be appreciated by those skilled in the art that the features described in the various embodiments and / or claims of the present disclosure may be combined and / or combined in a variety of ways, even if such combinations and / or combinations are not explicitly described in the present disclosure. In particular, the features described in the various embodiments and / or claims of the present disclosure may be combined and / or combined in a variety of ways without departing from the spirit and teachings of the present disclosure. All of these combinations and / or combinations fall within the scope of the present disclosure.

[0114] The embodiments of the present disclosure are described above. However, these embodiments are only for illustrative purposes and are not intended to limit the scope of the present disclosure. Although the embodiments are described above separately, this does not mean that the measures in the various embodiments cannot be used in combination to advantage. The scope of the present disclosure is defined by the attached claims and their equivalents. Without departing from the scope of the present disclosure, those skilled in the art may make a variety of substitutions and modifications, which should all fall within the scope of the present disclosure.

Claims

1. A drone fuselage, characterized in that: include: The fuselage body (10) comprises a containing structure (11) and at least one cantilever (12), wherein: The accommodating structure (11) comprises a bottom support frame (111) and a circumferential support frame (112), the bottom support frame (111) being located below the circumferential support frame (112), and the bottom support frame (111) and the circumferential support frame (112) being connected to form an accommodating space of the accommodating structure (11); A first end of each cantilever (12) of the at least one cantilever (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 fuselage body (10) comprises at least three arms (14), and the at least three arms (14) are staggeredly connected in pairs; each of the arms (14) comprises: First ontology (141); two second bodies (142); and Two connecting members (143) are respectively arranged at two ends of the first body (141); The first body (141) and each of the two second bodies (142) are foldably connected via one of the two connecting members (143), comprising: The minimum distance between two second bodies (142) connected to both ends of the same first body (141) in a direction perpendicular to a fuselage plane formed by the at least three arms (14) interlaced in pairs is greater than zero; or The connecting member (143) includes a rotation axis which forms an acute angle with the first plane, and each of the second bodies (142) can be rotated and folded around the rotation axis relative to the first body (141), and the first plane is perpendicular to the direction from the fixing portion (1431) of the connecting member (143) to the first body (141), wherein the connecting member (143) is connected to the first body (141) via the fixing portion (1431).

2. The UAV fuselage according to claim 1, characterized in that: Both ends of each of the at least three arms (14) extend outside the staggered area (15), wherein the staggered area (15) is an area formed by staggering two of the at least three arms (14); wherein: The portions of the at least three machine arms (14) located within the staggered area (15) constitute the circumferential support frame (112); The portion of the at least three arms (14) located outside the staggered area (15) constitutes the at least one cantilever (12).

3. The UAV fuselage according to claim 2, characterized in that: The at least three machine arms (14) include four machine arms (14).

4. The UAV fuselage according to claim 2 or 3, characterized in that: The first body (141) constitutes a part of the circumferential support frame (112) in each of the arms (14), and the two second bodies (142) constitute a part of the at least one cantilever (12) in each of the arms (14).

5. The UAV fuselage according to claim 4, characterized in that: The connecting member (143) comprises: a first frame structure (1410), the first frame structure (1410) comprising a first clamping component (1411) and a first opening (1412); and a second frame structure (1420) connected to the first frame structure (1410), the second frame structure (1420) comprising a second clamping component (1421) and a second opening (1422), the second opening (1422) and the first opening (1412) having a different orientation; 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 clamping component (1411) and the second clamping component (1421) is configured to be rotatably connected to the second body (142).

6. The UAV fuselage according to claim 4, characterized in that: The connecting member (143) comprises: The fixing portion (1431) comprises at least one first rotational matching structure (14301); at least one movable part (1432), the movable part (1432) comprising a second rotational matching structure, wherein the second rotational matching structure is matched and connected with the first rotational matching structure (14301) to form an axis-hole matching structure (1430), so that the movable part (1432) is rotatably connected to the fixed part (1431) through the axis-hole matching structure (1430); Wherein, the movable portion (1432) is configured to be connected to the second body (142); and the angle between the rotation axis of the shaft-hole matching structure (1430) and the first plane is an acute angle.

7. The UAV fuselage according to claim 1, characterized in that: Also includes: A control system installation structure is arranged on the periphery of the accommodating structure (11).

8. The UAV fuselage according to claim 7, wherein the control system installation structure comprises: At least two power battery bearing structures (20) are symmetrically arranged on the periphery of the accommodating structure (11) relative to a vertical line passing through the center of gravity of the fuselage body (10).

9. The UAV fuselage according to claim 7, characterized in that: The control system installation structure includes: The avionics cabin (40) is arranged below the bottom support frame (111).

10. A drone (1), characterized in that: It comprises the UAV fuselage according to any one of claims 1 to 9.

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