Fuselage assembly for unmanned aerial vehicle and unmanned aerial vehicle with fuselage assembly

Abstract

The invention discloses a fuselage assembly for an unmanned aerial vehicle and the unmanned aerial vehicle with the fuselage assembly. The connecting beam is fixedly connected with the mounting frame, and the connecting beam is an integrally formed piece; and the multiple vehicle arms are arranged on the connecting beam at intervals. According to the fuselage assembly, the production efficiency of the connecting beam is high, the structural strength is high, and the assembling efficiency of the fuselage assembly can be effectively improved. And the weight of the connecting beam can be reduced to a certain extent, so that the fuselage assembly is light.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicles, and in particular to a fuselage component for unmanned aerial vehicles and a unmanned aerial vehicle having the fuselage component. Background Art

[0002] In the fuselage assembly of the drone in the related art, the connecting beam structure used to connect the mounting frame and the arm has low structural strength, a long assembly time, and a large number of connecting parts (such as screws, pins, etc.) required for assembly, which makes the connecting beam structure relatively heavy. The structure of the fuselage assembly needs to be improved. Summary of the invention

[0003] The present invention aims to solve at least one of the technical problems existing in the prior art. To this end, one purpose of the present invention is to provide a fuselage assembly for a drone, wherein the connecting beam has high production efficiency and high structural strength, and can effectively improve the assembly efficiency of the fuselage assembly. The weight of the connecting beam can be reduced to a certain extent, making the fuselage assembly lightweight.

[0004] The present invention also provides a drone, comprising the above-mentioned fuselage assembly.

[0005] According to an embodiment of the present invention, a fuselage assembly for a drone includes: a mounting frame; a connecting beam, which is fixedly connected to the mounting frame and is an integrally formed part; and a plurality of arms, which are spaced apart and arranged on the connecting beam.

[0006] According to the fuselage assembly for a drone according to the embodiment of the present invention, by providing a connecting beam, the connecting beam is an integrally formed part, thereby improving the production efficiency of the connecting beam to a certain extent, improving the structural strength of the connecting beam, and effectively improving the assembly efficiency of the fuselage assembly. In addition, compared with the prior art, the connecting beam does not need to be assembled, thereby effectively reducing the use of connecting parts, etc., and further reducing the weight of the connecting beam to a certain extent, making the fuselage assembly lightweight.

[0007] According to some embodiments of the present invention, the connecting beam includes a first beam body and two second beam bodies, the two second beam bodies are respectively located at opposite ends of the first beam body and connected to the first beam body, the first beam body is cooperatively connected to the mounting frame, and there are two arms, the two arms correspond one-to-one to the two second beam bodies, and each arm is connected to the corresponding second beam body.

[0008] According to some embodiments of the present invention, a first reinforcing rib is provided at a connection between the second beam body and the first beam body.

[0009] According to some embodiments of the present invention, the first beam body is recessed in a direction away from the installation frame to define a first mating groove, a first connecting portion is provided on an inner wall of the first mating groove, a second connecting portion is provided on the installation frame, and a portion of the installation frame is suitable for extending into the first mating groove and being matingly connected with the second connecting portion through the first connecting portion.

[0010] In some embodiments of the present invention, the first connecting portion is formed as a boss provided on the inner wall of the first mating groove, and the first connecting portion is provided with a first connecting hole, and the first connecting hole penetrates the first beam body along the thickness direction of the first beam body, the second connecting portion is formed as a boss provided on the mounting frame, and the second connecting portion is provided with a second connecting hole, and the first connecting hole and the second connecting hole are fixedly connected by a connecting member.

[0011] In some embodiments of the present invention, a stop portion is provided on the inner wall of the first mating groove, at least a portion of the end surface of the stop portion facing the mounting frame forms a stop surface, and at least a portion of the mounting frame extending into the first mating groove is suitable for abutting against the stop surface to enable the first connecting portion to be mated and connected with the second connecting portion.

[0012] In some embodiments of the present invention, there are multiple stop portions distributed at intervals, and each of the stop portions extends along the circumference of the inner wall of the first matching groove to form a reinforcing rib structure.

[0013] According to some embodiments of the present invention, each of the second beam bodies includes a pivot portion and a mating portion that are connected to each other, the pivot portion is connected to the first beam body, the pivot portion is recessed in a direction away from the mounting frame to define a second mating groove, and one end of the arm extends into the second mating groove and is pivotally connected to the pivot portion.

[0014] In some embodiments of the present invention, pivot holes are respectively provided on two opposite side walls of the second mating groove, and the pivot holes on different side walls are arranged oppositely and coaxially. Each of the arms includes a pivot member and an arm rod, one end of the arm rod is fixed on the pivot member, a part of the pivot member is located in the second mating groove, and a mating hole is provided on the part of the pivot member located in the second mating groove. There are multiple mating holes and they correspond one-to-one to the pivot holes on the pivot part and are coaxially arranged.

[0015] In some embodiments of the present invention, a reinforcement protrusion is provided on the outer peripheral wall of the second matching groove, and the reinforcement protrusion is arranged around the pivot hole.

[0016] In some embodiments of the present invention, the mating portion is recessed in a direction away from the mounting frame to define a third mating groove, the third mating groove is connected to the second mating groove, a portion of the pivot member is located in the third mating groove, a first limiting groove recessed toward the third mating groove is provided on the outer peripheral wall of the third mating groove, and a limiting protrusion is provided on the bottom wall of the first limiting groove.

[0017] In some embodiments of the present invention, a second reinforcing rib is provided at a connection between the matching portion and the pivoting portion.

[0018] According to some embodiments of the present invention, the fuselage assembly further includes two protection frames, which are arranged on the first beam body at intervals and located on a side of the first beam body away from the installation frame.

[0019] In some embodiments of the present invention, a connecting column is provided on the first beam body, and a plug-in hole is provided on the connecting column. A part of the protective frame is suitable for being inserted into the plug-in hole to be connected with the first beam body.

[0020] According to some embodiments of the present invention, the second beam body extends upward and rearward relative to the first beam body.

[0021] In some embodiments of the present invention, the angle at which the second beam extends upward relative to the first beam is 10°-35°.

[0022] In some embodiments of the present invention, the angle at which the second beam extends upward relative to the first beam is 12°, 19°, 21° or 32°.

[0023] In some embodiments of the present invention, the angle at which the second beam extends rearward relative to the first beam is 5°-20°.

[0024] In some embodiments of the present invention, the angle at which the second beam extends rearward relative to the first beam is 9°, 12°, 14° or 16°.

[0025] The drone according to an embodiment of the present invention includes the fuselage assembly according to the above embodiment of the present invention.

[0026] According to the drone of the embodiment of the present invention, by setting the fuselage assembly according to the above embodiment of the present invention, the production efficiency of the connecting beam can be improved to a certain extent, the structural strength of the connecting beam can be improved, and the assembly efficiency of the drone can be improved. Compared with the prior art, the connecting beam does not need to be assembled, which can effectively reduce the use of connecting parts, etc., and can also reduce the weight of the connecting beam to a certain extent, making the drone lightweight.

[0027] Additional aspects and advantages of the present invention will be given in part in the following description and in part will be obvious from the following description, or will be learned through practice of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] The above and / or additional aspects and advantages of the present invention will become apparent and easily understood from the description of the embodiments in conjunction with the following drawings, in which:

[0029] Figure 1 is a schematic diagram of a drone according to some embodiments of the present invention;

[0030] Figure 2 is a schematic diagram of a drone according to some embodiments of the present invention;

[0031] Figure 3 is a schematic diagram of a drone according to some embodiments of the present invention;

[0032] Figure 4 yes Figure 3 A magnified view of part A;

[0033] Figure 5 is a schematic diagram of a drone according to some embodiments of the present invention;

[0034] Figure 6 is a schematic diagram of a connecting beam according to some embodiments of the present invention;

[0035] Figure 7 is a schematic diagram of a connecting beam according to some embodiments of the present invention;

[0036] Figure 8 is a schematic diagram of a connecting beam according to some embodiments of the present invention;

[0037] Fig. 9 is a schematic diagram of a connecting beam according to some embodiments of the present invention;

[0038] Fig.10 is a schematic diagram of a mounting frame according to some embodiments of the present invention;

[0039] Fig.11 is a schematic diagram of a mounting frame according to some embodiments of the present invention;

[0040] Fig.12 is a schematic diagram of a mounting frame according to some embodiments of the present invention;

[0041] Fig.13 is a schematic diagram of a partial structure of a drone according to some embodiments of the present invention;

[0042] Fig.14 is a schematic diagram of a machine arm according to some embodiments of the present invention;

[0043] Fig.15 is a schematic diagram of a pivotal member according to some embodiments of the present invention;

[0044] Fig.16 is a schematic diagram of a mounting member according to some embodiments of the present invention;

[0045] Fig.17 is a schematic diagram of a locking assembly according to some embodiments of the present invention;

[0046] Fig.18 is a schematic diagram of a first lock accessory according to some embodiments of the present invention;

[0047] Fig.19 is a schematic diagram of a second lock accessory according to some embodiments of the present invention;

[0048] Fig. 20 is a schematic diagram of a locking member according to some embodiments of the present invention;

[0049] Fig.21 is a schematic diagram of a partial structure of a drone according to some embodiments of the present invention;

[0050] Fig. 22 is a schematic diagram of a tripod support leg according to some embodiments of the present invention;

[0051] Fig.23 is a schematic diagram of a second matching member according to some embodiments of the present invention;

[0052] Fig.24 is a schematic diagram of a first fixing member according to some embodiments of the present invention;

[0053] Fig.25 is a schematic diagram of a second fixing member according to some embodiments of the present invention;

[0054] Fig.26 is a schematic diagram of a liquid storage container according to some embodiments of the present invention;

[0055] Fig. 27 is a schematic diagram of a liquid storage container according to some embodiments of the present invention;

[0056] Fig.28 is a schematic diagram of a first antenna according to some embodiments of the present invention;

[0057] Fig.29 is a schematic diagram of a second antenna according to some embodiments of the present invention;

[0058] Fig.30 is a schematic diagram of a power assembly according to some embodiments of the present invention;

[0059] Fig.31 yes Fig.30 Cross-sectional view in the BB direction;

[0060] Fig.32 is a schematic diagram of a power assembly according to some embodiments of the present invention;

[0061] Fig.33 is a schematic diagram of a connection socket according to some embodiments of the present invention.

[0062] Reference numerals:

[0063] UAV 100, fuselage assembly 10,

[0064] Body 1,

[0065] Connecting beam 11, first beam body 111, first matching groove 1110, upper end wall 1111, lower end wall 1112, front end wall 1113, first connecting portion 1114, first connecting hole 11141, stop surface 1115, stop portion 1116, connecting column 1117, plug-in hole 11171, wire hole 1118, reinforcement hole 1119,

[0066] The pivoting portion 112, the second matching groove 1120, the upper pivoting wall 1121, the lower pivoting wall 1122, the front pivoting wall 1123, the antenna mounting seat 1124, the first reinforcing rib 1125, the pivoting hole 1126, the reinforcing protrusion 1127,

[0067] The matching portion 113, the third matching groove 1130, the first limiting groove 1131, the limiting protrusion 1132, the second reinforcing rib 1133, the second beam body 114,

[0068] Installation frame 12, installation cavity 120, first installation cavity 1201, second installation cavity 1202,

[0069] The front end plate 121, the rear end plate 122, the side plate 123, the first side plate portion 1231, the second mounting protrusion 12311, the second side plate portion 1232, the transition portion 1233, the positioning groove 1234, the positioning hole 1235,

[0070] The second connecting part 124, the isolation plate 125, the reinforcing plate 126, the battery guide module 127,

[0071] Liquid storage container guide module 128,

[0072] Mounting frame 13,

[0073] Protection frame 14, protection rod 141, fixing seat 142,

[0074] Arm 2,

[0075] The pivot member 21, the sleeve portion 211, the sleeve hole 2110, the first outer wall 2111, the second outer wall 2112, the second limiting groove 2113, the pivot protrusion 212, the matching hole 2122,

[0076] Arm rod 22,

[0077] The support arm assembly 23, the mounting member 231, the mounting base plate 2311, the adapter 2312, the support arm 232,

[0078] The support arm 2321, the pivot member 2322, the locking assembly 233, the first locking component 2331, the first annular portion 23311, the first pivoting protrusion 23312, the pivoting block 23313, the first locking portion 23314, the groove portion 23315, the second locking component 2332, the second annular portion 23321, the second pivoting protrusion 23322, the second locking portion 23323, the third limiting groove 23324, the locking component 2333, the matching boss 23331, the third pivoting protrusion 23332, the connecting rod 23333, the protrusion 23334, the pivot rod 2334,

[0079] Landing gear 3,

[0080] Support leg assembly 301, tripod support leg 31, front support leg 311, first support leg section 3111, second support leg section 3112, support section 3113, bottom support leg 312, rear support leg 313,

[0081] The first matching member 32,

[0082] Landing gear connection assembly 33, first fixing member 331, second fixing member 332,

[0083] The second matching member 34, the connecting protrusion 341,

[0084] Power assembly 4,

[0085] Connecting seat 41, sleeve portion 411, sleeve hole 4110, extension portion 412, mounting portion 413,

[0086] Mounting assembly 42, mounting column 421, bearing 422, connecting kit 423, fixed support 424, rotating member 425,

[0087] Power unit 43, power motor 431, propeller assembly 432,

[0088] Driving device 44, steering gear 441, transmission shaft 442, connecting rod assembly 443, first adapter 4431,

[0089] The second adapter 4432, the connecting rod 4433,

[0090] Liquid storage container 5, liquid storage cavity 50, liquid storage cavity 51, upper box 511, mounting groove 5111, lower box 512,

[0091] Battery 6 , electronic control module 7 , communication module 71 , first antenna 711 , second antenna 712 , flight control module 72 , NFC reader / writer 8 . DETAILED DESCRIPTION

[0092] Embodiments of the present invention are described in detail below, examples of which are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present invention, and cannot be understood as limiting the present invention.

[0093] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise", "axial", "radial", "circumferential" and the like indicate positions or positional relationships based on the positions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention. In addition, features defined as "first" and "second" may explicitly or implicitly include one or more of the features. In the description of the present invention, unless otherwise specified, "multiple" means two or more.

[0094] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0095] Reference below Figure 1-Figure 33 The fuselage assembly 10 for the drone 100 according to an embodiment of the present invention is described. The drone 100 can be used in the farming industry to spray pesticides or water on crops. Of course, the drone 100 can also be used in other fields such as spraying fire extinguishing liquid in forest fires, aerial photography, power inspection, environmental monitoring, forest fire prevention and disaster inspection.

[0096] like Figure 1 and Figure 2 As shown, a fuselage assembly 10 for a drone 100 according to an embodiment of the present invention includes: a mounting frame 12 , a connecting beam 11 and a plurality of arms 2 .

[0097] Specifically, if Figure 2 As shown, the connecting beam 11 is fixedly connected to the mounting frame 12, and the connecting beam 11 is an integrally formed part. A plurality of arms 2 are arranged at intervals on the connecting beam 11. It should be noted that the mounting frame 12 can be used to install batteries and liquid storage containers of the drone 100.

[0098] It can be seen that in the fuselage assembly 10 of the drone 100, the mounting frame 12 and the plurality of arms 2 can be arranged on the connecting beam 11. The connecting beam 11 is a structural setting of an integrally formed part, which can improve the production efficiency of the connecting beam 11 to a certain extent, improve the structural strength of the connecting beam 11, and effectively improve the assembly efficiency of the fuselage assembly 10. Compared with the prior art, the connecting beam 11 does not need to be assembled, thereby effectively reducing the use of connecting parts, etc., and further reducing the weight of the connecting beam 11 to a certain extent, making the fuselage assembly 10 lightweight.

[0099] According to the fuselage assembly 10 for the drone 100 of the embodiment of the present invention, the connecting beam 11 is provided so that the connecting beam 11 is an integrally formed part, thereby improving the production efficiency of the connecting beam 11 to a certain extent, improving the structural strength of the connecting beam 11, and effectively improving the assembly efficiency of the fuselage assembly 10. In addition, compared with the prior art, the connecting beam 11 does not need to be assembled, thereby effectively reducing the use of connecting parts (such as screws), etc., and thereby reducing the weight of the connecting beam 11 to a certain extent, making the fuselage assembly 10 lightweight.

[0100] like Figure 1 and Figure 8 As shown, according to some embodiments of the present invention, the connecting beam 11 includes a first beam body 111 and two second beam bodies 114, the two second beam bodies 114 are respectively located at opposite ends of the first beam body 111 and connected to the first beam body 111, the first beam body 111 is cooperatively connected to the mounting frame 12, there are two arms 2, the two arms 2 correspond to the two second beam bodies 114 one by one, and each arm 2 is connected to the corresponding second beam body 114. It can be seen that the connecting beam 11 is fixedly connected to the mounting frame 12 through the first beam body 111, and is respectively connected to the two arms 2 through the two second beam bodies 114. It can be seen that the connecting beam 11 has a simple structure, and the connection positions with the mounting frame 12 and the arm 2 are reasonably distributed, which can avoid interference between the arm 2 and the mounting frame 12 when connected and assembled with the connecting beam 11 to a certain extent, which is conducive to improving the structural stability and reliability of the fuselage assembly 10.

[0101] like Figure 6As shown, according to some embodiments of the present invention, a first reinforcing rib 1125 is provided at the connection between the second beam body 114 and the first beam body 111. This can improve the overall structural strength of the connecting beam 11, thereby improving the reliability of the fuselage assembly 10 and the reliability of the drone 100.

[0102] like Figure 6 , Figure 7 and Fig.10 As shown, according to some embodiments of the present invention, the first beam body 111 is recessed in a direction away from the mounting frame 12 to define a first matching groove 1110, a first connecting portion 1114 is provided on the inner wall of the first matching groove 1110, a second connecting portion 124 is provided on the mounting frame 12, and a portion of the mounting frame 12 is suitable for extending into the first matching groove 1110 and being matched and connected with the second connecting portion 124 through the first connecting portion 1114. It can be seen that the mounting frame 12 and the connecting beam 11 can be fixedly connected through the first connecting portion 1114 and the second connecting portion 124, and at the same time, the structural setting in which a portion of the mounting frame 12 extends into the first matching groove 1110 can also support and position the mounting frame 12 through the inner wall of the first matching groove 1110, thereby improving the structural reliability of the fuselage assembly 10, and also facilitating the operator to match and connect the first connecting portion 1114 with the second connecting portion 124.

[0103] like Figure 6 and Figure 7 As shown, in some embodiments of the present invention, the first connecting portion 1114 is formed as a boss arranged on the inner wall of the first matching groove 1110, and the first connecting portion 1114 is provided with a first connecting hole 11141, and the first connecting hole 11141 penetrates the first beam body 111 along the thickness direction of the first beam body 111, and the second connecting portion 124 is formed as a boss arranged on the mounting frame 12, and the second connecting portion 124 is provided with a second connecting hole, and the first connecting hole 11141 and the second connecting hole are fixedly connected by a connecting member.

[0104] It can be seen that the structure of the first connection part 1114 and the second connection part 124 is simple, and the matching connection method is simple, reliable, and easy to operate. The connecting member can be a screw, so that the structure of the connecting member is simple, the source is wide, and the cost is low. At the same time, it can be understood that since the first connection part 1114 and the second connection part 124 are both formed as bosses, when the installation frame 12 is matched with the connecting beam 11, it is necessary to make the boss formed by the first connection part 1114 correspond to the boss formed by the second connection part 124 in place, and make the first connection hole 11141 relative to the second connection hole, so that the first connection part 1114 and the second connection part 124 can be fixedly connected through the connecting member. This makes it easier for the operator to more accurately align the first connection part 1114 with the second connection part 124, and can improve the efficiency of the matching connection between the installation frame 12 and the connecting beam 11 to a certain extent.

[0105] like Figure 6 As shown, in some embodiments of the present invention, a stop portion 1116 is provided on the inner wall of the first matching groove 1110, and at least a portion of the end surface of the stop portion 1116 facing the side of the installation frame 12 forms a stop surface 1115, and at least a portion of the installation frame 12 extending into the first matching groove 1110 is suitable for stopping on the stop surface 1115 so that the first connection portion 1114 and the second connection portion 124 are matched and connected. It can be seen that the setting of the stop portion 1116 can limit the installation frame 12 to a certain extent, so that when at least a portion of the installation frame 12 extending into the first matching groove 1110 stops on the stop surface 1115, the positions of the first connection portion 1114 and the second connection portion 124 can be roughly opposite, so as to facilitate the matching connection of the first connection portion 1114 and the second connection portion 124, which is conducive to improving the connection and assembly efficiency of the installation frame 12 and the connecting beam 11.

[0106] like Figure 6 As shown, in some embodiments of the present invention, there are multiple stop portions 1116 and they are spaced apart, and each stop portion 1116 extends along the circumference of the inner wall of the first matching groove 1110 to form a reinforcing rib structure. This is not only conducive to improving the connection and assembly efficiency between the installation frame 12 and the connecting beam 11, but also can improve the structural strength of the connecting beam 11 and improve the reliability of the fuselage assembly 10.

[0107] like Figure 6 , Figure 8 and Fig. 9As shown, in some embodiments of the present invention, a wire hole 1118 penetrating the first beam body 111 is further provided on the inner wall of the first matching groove 1110, and the wire hole 1118 is arranged away from the mounting frame 12. Thus, it is convenient for part of the connecting wires of the drone 100 to pass through the wire hole 1118 and pass into the first matching groove 1110, thereby preventing the drone 100 from being scraped against external objects (such as branches) during flight and causing the connecting wires to be cut or damaged, thereby improving the safety and reliability of the use of the drone 100, and also improving the appearance of the fuselage assembly 10 and reducing the space occupied by the fuselage assembly 10.

[0108] like Figure 6 , Figure 8 and Fig. 9 As shown, according to some embodiments of the present invention, each second beam body 114 includes a pivoting portion 112 and a matching portion 113 connected to each other, the pivoting portion 112 is connected to the first beam body 111, the pivoting portion 112 is recessed in a direction away from the mounting frame 12 to define a second matching groove 1120, and one end of the arm 2 extends into the second matching groove 1120 and is pivotally connected to the pivoting portion 112. It can be seen that the arm 2 can be pivoted relative to the pivoting portion 112, so that the arm 2 can be pivoted relative to the connecting beam 11, and then when the drone 100 is idle, the arm 2 can be folded, which is conducive to reducing the occupied space of the drone 100.

[0109] like Figure 6 , Figure 7 , Fig.13 and Fig.14 As shown, in some embodiments of the present invention, pivot holes 1126 are respectively provided on two opposite side walls of the second mating groove 1120, and the pivot holes 1126 on different side walls are oppositely and coaxially arranged, each arm 2 includes a pivot member 21 and an arm rod 22, one end of the arm rod 22 is fixed on the pivot member 21, a part of the pivot member 21 is located in the second mating groove 1120, and a mating hole 2122 is provided on the part of the pivot member 21 located in the second mating groove 1120, and there are multiple mating holes 2122 and they correspond one-to-one to the pivot holes 1126 on the pivot part 112 and are coaxially arranged. It can be seen from this that when the arm 2 is matched and connected with the connecting beam 11, it is necessary to extend a part of the pivot member 21 into the second matching groove 1120 so that the multiple matching holes 2122 correspond one by one with the multiple pivot holes 1126 and are coaxially arranged, and then a transfer shaft can be passed through the relatively corresponding pivot hole 1126, matching hole 2122, matching hole 2122, and pivot hole 1126 in sequence, thereby realizing the pivot connection between the pivot member 21 and the pivot part 112, and then the arm 2 and the connecting beam 11 can be pivotally connected.

[0110] Specifically, Figure 6 and Figure 7As shown, a reinforcing protrusion 1127 is provided on the outer peripheral wall of the second matching groove 1120, and the reinforcing protrusion 1127 is arranged around the pivot hole 1126. Thus, the reliability of the pivot connection between the machine arm 2 and the connecting beam 11 can be improved, and the structural strength of the connecting beam 11 can be improved.

[0111] like Figure 6 , Figure 8 and Fig. 9 As shown, in some embodiments of the present invention, the matching portion 113 is concave in a direction away from the installation frame 12 to define a third matching groove 1130, the third matching groove 1130 is connected to the second matching groove 1120, a part of the pivot 21 is located in the third matching groove 1130, and a first limiting groove 1131 is provided on the outer peripheral wall of the third matching groove 1130, which is concave toward the third matching groove 1130, and a limiting protrusion 1132 is provided on the bottom wall of the first limiting groove 1131. It can be seen that the machine arm 2 is connected to the connecting beam 11 through the pivot 21. At the same time, it can be seen that the concave direction of the first limiting groove 1131 is opposite to the concave direction of the third matching groove 1130, and the setting of the limiting protrusion 1132 and the first limiting groove 1131 can also improve the structural strength of the second beam body 114 to a certain extent.

[0112] like Figure 8 As shown, in some embodiments of the present invention, a second reinforcing rib 1133 is provided at the connection between the matching portion 113 and the pivoting portion 112. This can improve the structural strength of the second beam body 114, thereby improving the overall structural strength of the connecting beam 11, improving the reliability of the fuselage assembly 10, and improving the reliability of the drone 100.

[0113] like Figure 1 and Figure 6-Figure 9 As shown, in some embodiments of the present invention, an antenna mounting seat 1124 is provided on the pivoting portion 112, and a communication hole is provided on the antenna mounting seat 1124, which is communicated with the space defined by the second matching groove 1120. Thus, the antenna in the drone 100 can be provided on the antenna mounting seat 1124, and a part of it can be extended into the second matching groove 1120 through the communication hole.

[0114] like Figure 1 and Figure 5 As shown, according to some embodiments of the present invention, the fuselage assembly 10 further includes two protection frames 14, which are arranged on the first beam body 111 at intervals and are located on a side of the first beam body 111 away from the mounting frame 12. Thus, components that need to be protected in the drone 100 can be arranged between the two protection frames 14, for example, the electric control module 7 of the drone 100 can be arranged between the protection frames 14. In addition, the two protection frames 14 can protect the electric control module 7.

[0115] like Figure 1 , Figure 6-Figure 9 As shown, in some embodiments of the present invention, a connecting column 1117 is provided on the first beam body 111, and a plug-in hole 11171 is provided on the connecting column 1117, and a part of the protective frame 14 is suitable for being inserted into the plug-in hole 11171 to be connected with the first beam body 111. It can be seen that the matching mode of the protective frame 14 and the first beam body 111 is simple and easy to operate.

[0116] According to some embodiments of the present invention, the second beam body 114 extends upward and backward relative to the first beam body 111. It can be seen that the extension direction of the first beam body 111 is different from the extension direction of the second beam body 114. Since the connecting beam 11 is an integrally formed part, the structural strength of the connecting beam 11 can be improved to a certain extent.

[0117] In some embodiments of the present invention, the angle at which the second beam 114 extends upward relative to the first beam 111 is 10°-35°. Optionally, the angle at which the second beam 114 extends upward relative to the first beam 111 is 12°, 19°, 21° or 32°. It should be noted that, on a vertical plane parallel to the central axis of the first beam 111, the angle between the central axis of the second beam 114 and the orthographic projection of the central axis of the first beam 111 is the angle at which the second beam 114 extends upward relative to the first beam 111.

[0118] In some embodiments of the present invention, the angle at which the second beam 114 extends backward relative to the first beam 111 is 5°-20°. Optionally, the angle at which the second beam 114 extends backward relative to the first beam 111 is 9°, 12°, 14° or 16°. It should be noted that the angle between the orthographic projection of the central axis of the second beam 114 and the central axis of the first beam 111 on the horizontal plane is the angle at which the second beam 114 extends backward relative to the first beam 111.

[0119] like Figure 1-Figure 33 As shown, the drone 100 according to an embodiment of the present invention includes the fuselage assembly 10 according to the above embodiment of the present invention.

[0120] According to the drone 100 of the embodiment of the present invention, by providing the fuselage assembly 10 according to the above embodiment of the present invention, the production efficiency of the connecting beam 11 can be improved to a certain extent, the structural strength of the connecting beam 11 can be improved, and the assembly efficiency of the drone 100 can be improved. In addition, compared with the prior art, the connecting beam 11 does not need to be assembled, thereby effectively reducing the use of connecting parts, etc., and further reducing the weight of the connecting beam 11 to a certain extent, making the drone 100 lightweight.

[0121] Reference below Figure 1-Figure 33The following describes a drone 100 according to a specific embodiment of the present invention. It is worth noting that the following description is only exemplary and is intended to be used to explain the present invention, and should not be construed as limiting the present invention. Specifically, the drone 100 can be used in the farming industry for operations such as spraying pesticides or water irrigation on crops. Of course, the drone 100 can also be used in other fields such as spraying fire extinguishing fluids in forest fires, aerial photography, power inspections, environmental monitoring, forest fire prevention, and disaster inspections.

[0122] refer to Figure 1-Figure 33 According to an embodiment of the present invention, the drone 100 includes: a fuselage assembly 10, a landing gear 3, a power assembly 4, a liquid storage container 5, a battery 6 and an electronic control module 7. The arms 2 are distributed on both sides of the fuselage 1 and are connected to the fuselage 1. The fuselage assembly 10 includes a fuselage 1 and an arm 2. The landing gear 3 is fixed under the fuselage 1 to ensure the stability of the drone 100 during take-off and landing. The power assembly 4 is fixed to the end of the arm 2 away from the fuselage 1, and the power assembly 4 provides lift for the drone 100 to fly. The liquid storage container 5 is mounted on the fuselage 1 for containing items to be sprayed or transported, the battery 6 is fixed on the fuselage 1, the power assembly 4 provides power for the drone 100, and the electronic control module 7 is fixed on the fuselage 1 for controlling the flight posture of the drone 100.

[0123] Reference Figure 1-Figure 9 The fuselage 1 includes a connecting beam 11 and a mounting frame 12 fixedly connected to the connecting beam 11. The connecting beam 11 includes a first beam body 111 and two second beam bodies 114 connected at both ends of the first beam body 111, and each second beam body 114 includes a pivoting portion 112 and a matching portion 113 connected to each other.

[0124] Reference Figure 6 and Figure 7 The first beam body 111 includes an upper end wall 1111, a lower end wall 1112, and a front end wall 1113 connected between the upper end wall 1111 and the lower end wall 1112, wherein the front end wall 1113 is generally formed into a structure with a circular arc cross section. The upper end wall 1111, the lower end wall 1112, and the front end wall 1113 are collectively surrounded by a first matching groove 1110 with an opening facing backward, so that the first beam body 111 is formed into a structure with a generally "U"-shaped cross section. A first connecting portion 1114 and a stop surface 1115 are formed on the inner wall of the first matching groove 1110. The first connecting portion 1114 can extend along the upper end wall 1111, the lower end wall 1112, and the front end wall 1113, respectively, and a first connecting hole 11141 penetrating the outer wall of the first beam body 111 is opened on the first connecting portion 1114.

[0125] Preferably, a stop portion 1116 is further formed on the inner wall of the first matching groove 1110, and the stop portion 1116 can extend horizontally and / or longitudinally along the inner walls of the upper end wall 1111, the lower end wall 1112 and the front end wall 1113 to form a reinforcing rib structure. Among them, the stop surface 1115 can be formed on the stop portion 1116 located on the upper end wall 1111 and the lower end wall 1112, that is, at least a part of the end surface of the stop portion 1116 facing the installation frame 12 forms the stop surface 1115, and the stop surface 1115 located on the upper end wall 1111 and the stop surface 1115 located on the lower end wall 1112 are coplanar.

[0126] Furthermore, a connecting column 1117 is formed on the outer peripheral surface of the upper end wall 1111, and a plug-in hole 11171 with an opening facing forward is formed on the connecting column 1117. A wire hole 1118 is also provided on the front end wall 1113.

[0127] Reference Figure 6-9 , the pivotal parts 112 include two, each of which is also formed into a structure with a roughly "U"-shaped cross section, and each of which extends upward and backward along the end surface of the first beam body 111, wherein the angle at which each of the pivotal parts 112 extends upward relative to the first beam body 111 is 10°-35°. Specifically, the angle at which each of the pivotal parts 112 extends upward relative to the first beam body 111 is 12°, 19°, 21° or 32°. The angle at which each of the pivotal parts 112 extends backward relative to the first beam body 111 is 5°-20°. Specifically, the angle at which each of the pivotal parts 112 extends backward relative to the first beam body 111 is 9°, 12°, 14° or 16°. A second mating groove 1120 with an opening facing backward is formed in the pivotal part 112, and the second mating groove 1120 is connected to the first mating groove 1110.

[0128] Specifically, each pivoting portion 112 includes an upper pivoting wall 1121, a lower pivoting wall 1122, and a front pivoting wall 1123 connected to the upper pivoting wall 1121 and the lower pivoting wall 1122. The upper pivoting wall 1121, the lower pivoting wall 1122, and the front pivoting wall 1123 extend along the ends of the upper end wall 1111, the lower end wall 1112, and the front end wall 1113, respectively. A first reinforcing rib 1125 is formed at the connection between the upper pivoting wall 1121 and the upper end wall 1111, and the connection between the lower end wall 1112 and the lower pivoting wall 1122 to increase the connection strength between the pivoting wall 1121 and the upper end wall 1111, and between the lower end wall 1112 and the lower pivoting wall 1122. The upper pivot wall 1121, the lower pivot wall 1122 and the front pivot wall 1123 are arranged to form a second matching groove 1120 with an opening facing backwards, and the upper pivot wall 1121 and the lower pivot wall 1122 are respectively provided with coaxially arranged pivot holes 1126. The upper pivot wall 1121 and the lower pivot wall 1122 are also respectively provided with an antenna mounting seat 1124 extending vertically. The antenna mounting seat 1124 is provided with a connecting hole connected to the second matching groove 1120.

[0129] Furthermore, if Fig. 9 As shown, a matching portion 113 extends from the end of the pivoting portion 112, and second reinforcing ribs 1133 are respectively formed between the outer circumference of the matching portion 113 and the upper pivoting wall 1121, the lower pivoting wall 1122 and the front pivoting wall 1123 of the pivoting portion 112. The matching portion 113 is formed into a structure with an arc-shaped cross section, and a third matching groove 1130 with an opening facing backward is formed in the matching portion 113. The third matching groove 1130 is in an arc shape and communicates with the second matching groove 1120. A first limiting groove 1131 is also formed on the outer circumference of the matching portion 113, and a limiting protrusion 1132 is formed on the bottom wall of the first limiting groove 1131.

[0130] Reference Figure 6-Figure 7 and Figure 10-12 , the mounting frame 12 is suitable for connecting with the first beam body 111. Specifically, the mounting frame 12 includes a front end plate 121, a rear end plate 122, and two side plates 123 respectively connected to both ends of the front end plate 121 and the rear end plate 122. A second connecting portion 124 is formed on the front end plate 121 and the two side plates 123, and the second connecting portion 124 is suitable for connecting with the first connecting portion 1114 to fix the mounting frame 12 with the first beam body 111. During installation, when the end surface of the front end plate 121 abuts against the abutment surface 1115 on the inner wall of the first matching groove 1110, each second connecting portion 124 is opposite to each first connecting portion 1114.

[0131] Reference Figure 3 , Figure 10-12, the front end plate 121, the rear end plate 122 and the two side plates 123 together surround an installation cavity 120 that passes through from top to bottom. The liquid storage container 5 and the battery 6 are suitable for being inserted into the installation cavity 120 and detachably connected to the front end plate 121, the rear end plate 122 and one or more of the two side plates 123. Among them, the two side plates 123 are formed into a first side plate portion 1231 and a second side plate portion 1232 that are bent and connected, and the first side plate portion 1231 and the second side plate portion 1232 are connected by a transition portion 1233. Continuous reinforcing ribs are also formed on the sides of the first side plate portion 1231, the second side plate portion 1232 and the transition portion 1233.

[0132] Furthermore, the installation frame 12 further includes an isolation plate 125, and both ends of the isolation plate 125 are respectively connected to the ends of the two second side plate portions 1232 close to the transition portion 1233. The isolation plate 125 divides the installation cavity 120 into a first installation cavity 1201 and a second installation cavity 1202. The battery 6 can be installed in the first installation space 1201, and the liquid storage container 5 can be installed in the second installation space 1202.

[0133] Further, refer to Fig.12 A positioning groove 1234 is also formed on the first side plate 1231 , and a second mounting protrusion 12311 is formed on the side wall of the first side plate 1231 . A positioning hole 1235 is formed on the second mounting protrusion 12311 . The second mounting protrusion 12311 is used to mount the landing gear 3 .

[0134] Preferably, the mounting frame 12 further comprises a reinforcing plate 126, which is arranged parallel to the front end plate 121, and both ends of the reinforcing plate 126 are connected to the first side plate portion 1231. The reinforcing plate 126 is adapted to be connected with the reinforcing hole 1119 on the first beam body 11 to strengthen the strength between the mounting frame 12 and the connecting beam 11.

[0135] Preferably, refer to Figure 3 and Fig.10 A battery guide module 127 and a liquid storage container guide module 128 are also provided on the inner walls of the two side plates 123. When the battery 6 is installed in the first installation space 1201 and the liquid storage container 5 is installed in the second installation space 1202, the battery guide module 127 and the liquid storage container guide module 128 can guide, damp and fix the battery 6 and the liquid storage container 5.

[0136] Reference Figure 1-Figure 5 and Figure 13-14 The machine arm 2 includes two, and the two machine arms 2 are rotatably connected to the two pivoting parts 112 of the connecting beam 11. Each machine arm 2 includes a pivoting member 21, a machine arm rod 22 and an arm assembly 23.

[0137] Refer to the figure Fig.14 and15 The pivot member 21 includes a sleeve portion 211 and two pivot protrusions 212 extending along the sleeve portion 211. The sleeve portion 211 includes a first outer wall 2111 and a second outer wall 2112, and the first outer wall 2111 and the second outer wall 2112 are located on the same circumference (coaxial line). The first outer wall 2111 and the second outer wall 2112 of the sleeve portion 211 jointly define a sleeve hole 2110, and the sleeve hole 2110 is suitable for matching with one end of the machine arm rod 22. A second limiting groove 2113 is also provided on the peripheral wall of the second outer wall 2112. The two pivot protrusions 212 extend radially along the sleeve portion 211 respectively, and each pivot protrusion 212 is provided with a matching hole 2122, thereby making there two matching holes 2122, and the two matching holes 2122 correspond one by one to the pivot holes 1126 on the pivot portion 112 and are coaxially arranged, thereby realizing the pivot connection between the arm 2 and the pivot portion 112.

[0138] One end of the arm rod 22 is fixed in the sleeve hole 2110, and the other end of the arm rod 22 is used to fix the power assembly 5. In this embodiment, the arm rod 22 is an aluminum alloy tube wrapped with carbon fiber material. Of course, the arm rod 22 can also be a plastic tube made of plastic or a carbon tube made of carbon fiber material.

[0139] Reference Fig.13 and Fig.16 The support arm assembly 23 includes a mounting member 231 , a support arm 232 and a locking assembly 233 .

[0140] Specifically, the mounting member 231 includes a mounting base plate 2311 and a transition portion 2312 extending in a direction perpendicular to the mounting base plate 2311. The mounting member 231 is fixed to the transition portion 1233 through the mounting base plate 2311. The support arm 232 includes a support arm rod 2321 and pivot members 2322 connected to both ends of the support arm rod 2321. One end of the support arm 232 is pivotally connected to the transition portion 2312 of the mounting member 231 through the pivot member 2322. The other end of the support arm 232 is pivotally connected to the locking assembly 233 through the pivot member 2322.

[0141] Reference Fig.17 The locking assembly 233 includes a first locking component 2331 , a second locking component 2332 and a locking member 2333 .

[0142] Reference Fig.13 and Fig.18The first locking component 2331 includes a first annular portion 23311, two first pivoting protrusions 23312 extending outwardly from the outer circumference of the first annular portion 23311, a pivoting block 23313, and a first locking portion 23314. The two first pivoting protrusions 23312 are pivotally connected to one end of the support arm 232 away from the mounting member 231 through a pivoting member 2322. A groove portion 23315 is formed on the side wall of the first locking portion 23314.

[0143] Reference Figure 17-Figure 19 The second locking accessory 2332 includes a second annular portion 23321, two second pivoting protrusions 23322 and a second locking portion 23323 extending outwardly from the outer circumference of the second annular portion 23321. A third limiting groove 23324 is also provided on the inner circumference of the second annular portion 23321. The two second pivoting protrusions 23322 are pivotally connected to the pivot block 23313, so that the first annular portion 23311 and the second annular portion 23321 can be located on the same circumferential surface.

[0144] Reference Fig.17 and Fig. 20 The locking member 2333 is connected to the second locking part 23323 via a pivot rod 2334. The locking member 2333 includes a matching boss 23331, a third pivoting protrusion 23332 extending outwardly along the first end surface of the matching boss 23331, and a connecting rod 23333 (which can be a separate part) extending along the second end surface of the matching boss 23331. Further, a protrusion 23334 is formed on the second end surface.

[0145] The unfolding process of the machine arm 2 is described in detail below:

[0146] First, the arm 2 is rotated to fit the first outer wall 2111 of the pivot member 21 into the third matching groove 1130 of the matching portion 113. The matching portion 113 and the second outer wall 2112 are located on the same circumference, and the matching portion 113 and the second outer wall 2112 form a complete cylindrical tube. At the same time, the first limiting groove 1131 on the matching portion 113 and the second limiting groove 2113 on the peripheral wall of the second outer wall 2112 form a complete annular groove.

[0147] Secondly, the arm 232 fits the first annular portion 23311 of the first lock fitting 2331 and the second annular portion 23321 of the second lock fitting 2332 on the second limiting groove 2113 and the first limiting groove 1131 respectively. The limiting protrusion 1132 on the bottom wall of the first limiting groove 1131 fits with the third limiting groove 23324 on the inner circumference of the second annular portion 23321 to prevent the second annular portion 23321 and the bottom wall of the first limiting groove 1131 from rotating.

[0148] Finally, the locking member 2333 locks the first annular portion 23311 of the first locking member 2331 and the second annular portion 23321 of the second locking member 2332, so that the first annular portion 23311 and the second annular portion 23321 form a circular ring coaxially arranged with the cylindrical tube surrounded by the matching portion 113 and the second outer wall 2112. The first annular portion 23311 and the second annular portion 23321 lock the second outer wall 2112 and the matching portion 113 of the pivot 21. The protrusion 23334 on the second end surface of the locking member 2333 and the groove portion 23315 on the side wall of the first locking portion 23312 cooperate to squeeze the outer peripheral wall of the second outer wall 2112 of the pivot 21.

[0149] Folding process of the arm 2: The folding process of the arm 2 is opposite to the unfolding process of the arm 2, and will not be described in detail here.

[0150] Reference Fig.21 The landing gear 3 includes two support leg assemblies 301, the two support leg assemblies 201 are mirror-symmetrical structures, and the two support leg assemblies 301 are installed symmetrically below the fuselage 1. Each support leg assembly 301 includes a tripod support leg 31, a first matching piece 32, a second matching piece 34, and a landing gear connection assembly 33. The tripod support leg 31 is connected to the bottom of the fuselage 1 through the first matching piece 32, the second matching piece 34, and the landing gear connection assembly 33.

[0151] Reference Fig. 22 The tripod support leg 31 includes: a front support leg 311, a bottom support leg 312 and a rear support leg 313, wherein the front support leg 311 and the rear support leg 313 are respectively connected to the front and rear ends of the bottom support leg 312. The bottom support leg 312 is tubular and extends in the front and rear directions in the horizontal plane. The front support leg 311 includes a first support leg section 3111 connected to the bottom support leg 312, a second support leg section 3112 connected to the first support leg section 3111 and a support section 3113 connected to the second support leg section 3112. The support section 3113 is arranged parallel to the bottom support leg 312.

[0152] Reference Fig.12 and 21 -23, the supporting section 3113 of the tripod supporting leg 31 is engaged with the positioning groove 1234 and connected with the second mounting protrusion 12311 through the connecting protrusion 341 provided on the second engaging member 34.

[0153] The first fitting 32 connects the rear legs 313 to the rear end plate 122 .

[0154] Reference Fig.21 , Figure 24-25The landing gear connection assembly 33 includes a first fixing member 331 and a second fixing member 332. The first fixing member 331 and the second fixing member 332 connect the second leg section 3112 to the lower end wall 1112 of the first beam body 111.

[0155] Reference Figure 30-Figure 33 The power assembly 4 includes a connecting seat 41, a mounting assembly 42, a power unit 43 and a driving device 44.

[0156] The connecting seat 41 (divided into two parts) includes a mounting portion 413, a fitting portion 411 extending along one end of the mounting portion 413, and an extending portion 412 extending along the upper end surface of the mounting portion 413. A fitting hole 4110 is provided inside the fitting portion 411, and the end of the arm rod 22 away from the fuselage 1 is suitable for fitting in the fitting hole 4110.

[0157] The mounting assembly 42 includes a mounting column 421, a bearing 422, a connecting sleeve 423, a fixed support 424, and a rotating member 425. The two ends of the mounting column 421 are rotatably fixed to the extension portion 412 through the bearings 422. The connecting sleeve 423 and the fixed support 424 are connected to each other and fixed to the mounting column 421. The rotating member 425 is connected to the mounting column 421.

[0158] The power units 43 include two, and each power unit 43 includes a power motor 431 fixed on a fixed support 424 and a propeller assembly 432 fixed on the power motor 431 .

[0159] Reference Fig.31 and Fig.32 The driving device 44 includes a steering gear 441, a transmission device, a transmission shaft 442 and a connecting rod assembly 443, wherein the connecting rod assembly 443 includes a first adapter 4431 connected to the rotating member 425, a second adapter 4432 connected to the transmission shaft 442, and a connecting rod 4433 connected between the first adapter 4431 and the second adapter 4432. The first adapter 4431 and the second adapter 4432 are pivotally connected to the connecting rod 4433, respectively.

[0160] Reference Fig.26 and Fig. 27 The liquid storage container 5 includes a container body 51 having a liquid storage cavity 50, and the liquid storage cavity 50 is used to contain liquid medicine; the container body 51 includes an upper box body 511 and a lower box body 512 extending vertically downward from the bottom of the upper box body 511, and the upper box body 511 and the lower box body 512 are integrally formed and together form the liquid storage cavity 50. The upper box body 511 and the lower box body 512 form a "T" shape.

[0161] Reference Figure 2 and Fig.26The front end surface of the upper box body 511 is provided with a mounting groove 5111. The mounting groove 5111 is suitable for installing an NFC module, and the upper end surface of the connecting beam 11 is also provided with an NFC reader 8.

[0162] Reference Figure 1 The electronic control module 7 includes a communication module 71 and a flight control module 72. The communication module 71 and the flight control module 72 are connected to the fuselage 1. Specifically, the fuselage 1 includes a mounting frame 13. The mounting frame 13 is connected to the first beam body 111. The communication module 71 and the flight control module 72 are arranged on the mounting frame 13. The connection line between the electronic control module 7 and the power assembly 4 can pass through the wire hole 1118 into the first matching groove 1110, and then pass through the second matching groove 1120 and the machine arm rod 22.

[0163] Preferably, the fuselage 1 further comprises a protection frame 14, which is arranged outside the mounting frame 13, and comprises two protection rods 141, one end of which is fixed to the mating hole 11171 of the connecting column 1117. The other end of the protection rod 141 is fixed to the lower end wall 1112 through a fixing seat 142.

[0164] Reference Figure 1 , Fig.28 and Fig.29 The communication module 71 includes a first antenna 711 and a second antenna 712. In this embodiment, the first antenna 711 and the second antenna 712 are respectively fixed to the antenna mounting base 1124 of the upper pivot wall 1121 and the lower pivot wall 1122.

[0165] Other components and operations of the drone 100 according to the embodiment of the present invention are known to those skilled in the art and will not be described in detail here.

[0166] In the description of this specification, the description with reference to the terms "one embodiment", "some embodiments", "illustrative embodiments", "examples", "specific examples", or "some examples" means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representation of the above terms does not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described may be combined in any one or more embodiments or examples in a suitable manner.

[0167] Although the embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the claims and their equivalents.

Claims

1. A fuselage assembly for an unmanned aerial vehicle, characterized in that: include: Mounting frame; A connecting beam, wherein the connecting beam is fixedly connected to the mounting frame; A plurality of machine arms, wherein the plurality of machine arms are arranged on the connecting beam at intervals; Wherein, the connecting beam comprises a first beam body and two second beam bodies, the two second beam bodies are respectively located at opposite ends of the first beam body and connected to the first beam body, the first beam body is cooperatively connected to the mounting frame, the machine arms correspond to the second beam bodies one by one, and each of the machine arms is connected to the corresponding second beam body; Each of the second beam bodies includes a pivot portion, which is connected to the first beam body. The pivot portion is recessed in a direction away from the installation frame to define a second matching groove, and one end of the arm extends into the second matching groove and is pivotally connected to the pivot portion.

2. The fuselage assembly for a drone according to claim 1, characterized in that: Two opposite side walls of the second matching groove are respectively provided with pivot holes, and the pivot holes on different side walls are oppositely and coaxially arranged.

3. The fuselage assembly for a drone according to claim 2, characterized in that: Each of the machine arms comprises a pivot member and an arm rod, one end of the arm rod is fixed on the pivot member, and a part of the pivot member is located in the second matching groove.

4. The fuselage assembly for a drone according to claim 3, characterized in that: A matching hole is provided on the portion of the pivot member located in the second matching groove. There are a plurality of matching holes which correspond to the pivot holes on the pivot part one by one and are coaxially arranged.

5. The fuselage structure for a drone according to claim 3, characterized in that: Each of the second beam bodies also includes a matching portion connected to the pivotal portion, the matching portion is concave in a direction away from the installation frame to define a third matching groove, the third matching groove is connected to the second matching groove, and a portion of the pivotal member is located in the third matching groove.

6. The fuselage structure for a drone according to claim 5, characterized in that: A first limiting groove recessed toward the third matching groove is provided on the outer peripheral wall of the third matching groove, and a limiting protrusion is provided on the bottom wall of the first limiting groove.

7. The fuselage assembly for a drone according to claim 3, characterized in that: The pivot member includes a sleeve portion and two pivot protrusions extending along the sleeve portion, the sleeve portion includes a first outer wall and a second outer wall, the first outer wall and the second outer wall are located on the same circumference, the first outer wall and the second outer wall of the sleeve portion jointly define the sleeve hole, and the sleeve hole is used to cooperate with one end of the arm rod.

8. The fuselage assembly for a drone according to claim 7, characterized in that: The two pivoting protrusions extend radially along the sleeve portion respectively, and each of the pivoting protrusions is provided with a matching hole. The two matching holes correspond to the pivoting holes on the pivoting portion one by one and are coaxially arranged.

9. The fuselage assembly for a drone according to claim 2, characterized in that: A reinforcement protrusion is provided on the outer peripheral wall of the second matching groove, and the reinforcement protrusion is arranged around the pivot hole.

10. The fuselage assembly for a drone according to claim 1, characterized in that: The first beam body includes an upper end wall, a lower end wall and a front end wall connected between the upper end wall and the lower end wall. The upper end wall, the lower end wall and the front end wall are jointly formed to enclose a first matching groove opening toward the rear.

11. The fuselage assembly for a drone according to claim 10, characterized in that: The pivoting portion includes an upper pivoting wall, a lower pivoting wall and a front pivoting wall connected to the upper pivoting wall and the lower pivoting wall. The upper pivoting wall, the lower pivoting wall and the front pivoting wall extend along the ends of the upper end wall, the lower end wall and the front end wall respectively.

12. The fuselage assembly for a drone according to claim 11, characterized in that: A first reinforcing rib is formed at the connection between the upper pivot wall and the upper end wall, and between the lower end wall and the lower pivot wall.

13. The fuselage assembly for a drone according to claim 11, characterized in that: The upper pivot wall, the lower pivot wall and the front pivot wall are arranged to form the second matching groove with an opening facing backwards.

14. The fuselage assembly for a drone according to claim 10, characterized in that: A first connecting portion is formed on the inner wall of the first matching groove, and the first connecting portion is used to extend along the upper end wall, the lower end wall and the front end wall respectively.

15. The fuselage assembly for a drone according to claim 14, characterized in that: A stop portion is formed on the inner wall of the first matching groove, and the stop portion is used to extend laterally and / or longitudinally along the inner walls of the upper end wall, the lower end wall and the front end wall.

16. The fuselage assembly for a drone according to claim 15, characterized in that: At least a portion of the end surface of the stop portion 1116 facing the installation frame is formed with a stop surface, and the stop surface located on the upper end wall and the stop surface located on the lower end wall are coplanar.

17. The fuselage assembly for a drone according to any one of claims 1 to 16, characterized in that: A second reinforcing rib is provided at the connection between the matching portion and the pivoting portion.

18. The fuselage assembly for a drone according to any one of claims 1 to 16, characterized in that: The first beam body and the second beam body are integrally formed.

19. The fuselage assembly for a drone according to any one of claims 1 to 16, characterized in that: An antenna mounting seat is provided on the pivotal portion, and a connecting hole is provided on the antenna mounting seat. The connecting hole is connected to the space defined by the second matching groove.

20. The fuselage assembly for a drone according to any one of claims 1 to 16, characterized in that: It also includes two protection frames, which are arranged on the first beam body at intervals and located on a side of the first beam body away from the installation frame.

21. The fuselage assembly for a drone according to claim 20, characterized in that: The first beam body is provided with a connecting column, and the connecting column is provided with an inserting hole. A part of the protective frame is suitable for being inserted into the inserting hole to be matched and connected with the first beam body.

22. The fuselage assembly for a drone according to any one of claims 1 to 16, characterized in that: The second beam body extends upward and rearward relative to the first beam body.

23. The fuselage assembly for a drone according to claim 22, characterized in that: The second beam body extends upwardly at an angle of 10°-35° relative to the first beam body.

24. The fuselage assembly for a drone according to claim 22, characterized in that: The angle at which the second beam body extends rearward relative to the first beam body is 5°-20°.

25. A drone, characterized in that: Comprising a fuselage assembly for a drone according to any one of claims 1-24.

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