Fuselage assembly for drone and drone having the same

Abstract

The present invention discloses a fuselage assembly for a drone and a drone having the same. The fuselage assembly includes: a mounting frame; a connecting beam fixedly connected to the mounting frame, the connecting beam being an integrally formed part; and a plurality of arms spaced apart on the connecting beam. According to the fuselage assembly of the present invention, the connecting beam has high production efficiency and high structural strength, which can effectively improve the assembly efficiency of the fuselage assembly. And to a certain extent, the weight of the connecting beam can be reduced, making the fuselage assembly lightweight.

Description

Technical Field

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

[0002] In the fuselage assembly of an unmanned aerial vehicle in the related art, the connecting beam for connecting the mounting frame and the arm has low structural strength, long assembly time, and requires a large number of connecting parts (such as screws, pin shafts, etc.), so that the connecting beam structure is relatively heavy, and 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. For this purpose, an object of the present invention is to provide a fuselage assembly for an unmanned aerial vehicle, in which the connecting beam has high production efficiency and high structural strength, and can effectively improve the assembly efficiency of the fuselage assembly. And to a certain extent, the weight of the connecting beam can be reduced, making the fuselage assembly lightweight.

[0004] The present invention also provides an unmanned aerial vehicle including the above-mentioned fuselage assembly.

[0005] The fuselage assembly for an unmanned aerial vehicle according to an embodiment of the present invention includes: a mounting frame; a connecting beam fixedly connected to the mounting frame, the connecting beam being an integrally formed part; and a plurality of arms spaced apart on the connecting beam.

[0006] By providing a connecting beam which is an integrally formed part in the fuselage assembly for an unmanned aerial vehicle according to an 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 at the same time, the assembly efficiency of the fuselage assembly can be effectively improved. And compared with the prior art, the connecting beam does not need to be assembled, so that the use of connecting parts and the like can be effectively reduced, and to a certain extent, the weight of the connecting beam can also be reduced, 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 are connected to the first beam body, the first beam body is in mating connection with the mounting frame, there are two arms, and the two arms correspond to the two second beam bodies one by one, 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 the 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 away from the mounting frame to define a first fitting groove. A first connecting portion is provided on the inner wall of the first fitting groove, and a second connecting portion is provided on the mounting frame. A part of the mounting frame is adapted to extend into the first fitting groove and is connected in cooperation 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 fitting groove, and a first connecting hole is provided on the first connecting portion. The first connecting hole penetrates through 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 a second connecting hole is provided on the second connecting portion. The first connecting hole and the second connecting hole are fixedly connected through a connecting member.

[0011] In some embodiments of the present invention, a stopping portion is provided on the inner wall of the first fitting groove. At least a part of the end face of the side of the stopping portion facing the mounting frame forms a stopping surface. At least a part of the mounting frame extending into the first fitting groove is adapted to be stopped on the stopping surface so that the first connecting portion is connected in cooperation with the second connecting portion.

[0012] In some embodiments of the present invention, there are a plurality of the stopping portions which are spaced apart. Each of the stopping portions extends along the circumferential direction of the inner wall of the first fitting groove to form a reinforcing rib structure.

[0013] According to some embodiments of the present invention, each second beam body includes a pivot joint portion and a fitting portion connected to each other. The pivot joint portion is connected to the first beam body. The pivot joint portion is recessed away from the mounting frame to define a second fitting groove. One end of the machine arm extends into the second fitting groove and is pivotally connected to the pivot joint portion.

[0014] In some embodiments of the present invention, pivot holes are respectively provided on two opposite side walls of the second fitting groove. The pivot holes on different side walls are opposite and coaxially arranged. Each machine arm includes a pivot joint member and a machine arm rod. One end of the machine arm rod is fixed on the pivot joint member. A part of the pivot joint member is located in the second fitting groove, and a fitting hole is provided on the part of the pivot joint member located in the second fitting groove. There are a plurality of the fitting holes, which are in one-to-one correspondence and coaxially arranged with the pivot holes on the pivot joint portion.

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

[0016] In some embodiments of the present invention, the mating portion is recessed away from the mounting frame to define a third mating groove, which communicates with the second mating groove. A part of the pivoting member is located in the third mating groove. On the outer peripheral wall of the third mating groove, there is a first limiting groove recessed towards 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 the connection between the mating portion and the pivoting portion.

[0018] According to some embodiments of the present invention, the fuselage assembly further includes two protective frames, which are spaced apart on the first beam body and are located on the side of the first beam body away from the mounting frame.

[0019] In some embodiments of the present invention, a connecting column is provided on the first beam body, and an insertion hole is provided on the connecting column. A part of the protective frame is adapted to be inserted into the insertion hole to be cooperatively connected with the first beam body.

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

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

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

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

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

[0025] The unmanned aerial vehicle according to an embodiment of the present invention includes the fuselage assembly according to the above embodiments of the present invention.

[0026] The unmanned aerial vehicle according to an embodiment of the present invention, by providing the fuselage assembly according to the above embodiments of the present invention, can improve the production efficiency of the connecting beam to a certain extent, enhance the structural strength of the connecting beam, and at the same time improve the assembly efficiency of the unmanned aerial vehicle. And compared with the prior art, the connecting beam does not need to be assembled, thus effectively reducing the use of connecting parts, etc., and further reducing the weight of the connecting beam to a certain extent, making the unmanned aerial vehicle lightweight.

[0027] Additional aspects and advantages of the present invention will be given in part in the following description, become apparent in part from the following description, or be learned by 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 be readily understood from the description of 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 is Figure 3 an enlarged view of part A in

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

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

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

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

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

[0042] Figure 14 is a schematic diagram of an arm according to some embodiments of the present invention;

[0043] Figure 15 Schematic diagram of a pivot according to some embodiments of the present invention;

[0044] Figure 16 Schematic diagram of a mounting member according to some embodiments of the present invention;

[0045] Figure 17 Schematic diagram of a locking assembly according to some embodiments of the present invention;

[0046] Figure 18 Schematic diagram of a first locking fitting according to some embodiments of the present invention;

[0047] Figure 19 Schematic diagram of a second locking fitting according to some embodiments of the present invention;

[0048] Figure 20 Schematic diagram of a locking member according to some embodiments of the present invention;

[0049] Figure 21 Schematic diagram of a partial structure of a drone according to some embodiments of the present invention;

[0050] Figure 22 Schematic diagram of a tripod support leg according to some embodiments of the present invention;

[0051] Figure 23 Schematic diagram of a second mating member according to some embodiments of the present invention;

[0052] Figure 24 Schematic diagram of a first fixing member according to some embodiments of the present invention;

[0053] Figure 25 Schematic diagram of a second fixing member according to some embodiments of the present invention;

[0054] Figure 26 Schematic diagram of a liquid storage container according to some embodiments of the present invention;

[0055] Figure 27 Schematic diagram of a liquid storage container according to some embodiments of the present invention;

[0056] Figure 28 Schematic diagram of a first antenna according to some embodiments of the present invention;

[0057] Figure 29 Schematic diagram of a second antenna according to some embodiments of the present invention;

[0058] Figure 30 Schematic diagram of a power assembly according to some embodiments of the present invention;

[0059] Figure 31 is Figure 30 a sectional view taken along the B-B direction in the figure;

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

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

[0062] Reference numerals:

[0063] drone 100, fuselage assembly 10,

[0064] fuselage 1,

[0065] connection beam 11, first beam body 111, first mating groove 1110, upper end wall 1111, lower end wall 1112, front end wall 1113, first connection portion 1114, first connection hole 11141, abutting surface 1115, abutting portion 1116, connection column 1117, insertion hole 11171, wire passing hole 1118, strengthening hole 1119,

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

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

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

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

[0070] second connection portion 124, isolation plate 125, reinforcing plate 126, battery guiding module 127,

[0071] liquid storage container guiding module 128,

[0072] mounting bracket 13,

[0073] protective frame 14, protective rod 141, fixed 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 body 511, installation groove 5111, lower box body 512,

[0091] Battery 6, electronic control module 7, communication module 71, first antenna 711, second antenna 712, flight control module 72, NFC reader 8. Specific implementation manner

[0092] The embodiments of the present invention will be described in detail below. The examples of the embodiments are shown in the drawings, where the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the drawings are exemplary and are only used to explain the present invention and should not be construed as a limitation of the present invention.

[0093] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc. indicate the orientation or positional relationship based on the orientation or positional relationship shown in the 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 thus should not be construed as a limitation of the present invention. In addition, the features defined as "first" and "second" may explicitly or implicitly include one or more of such features. In the description of the present invention, unless otherwise stated, the meaning of "plurality" is two or more.

[0094] In the description of the present invention, it should be noted that unless otherwise clearly defined and limited, the terms "installation", "connection", and "connection" should be understood in a broad sense. For example, it may be a fixed connection, a detachable connection, or an integral connection; it may be a mechanical connection or an electrical connection; it may be a direct connection or an indirect connection through an intermediate medium, and it may be the communication inside two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific situations.

[0095] The following refers to Figures 1 - 33 Describe the fuselage assembly 10 for the unmanned aerial vehicle 100 according to an embodiment of the present invention. Among them, the unmanned aerial vehicle 100 can be used for operations such as pesticide spraying or water irrigation on crops in the agricultural industry. Of course, the unmanned aerial vehicle 100 can also be used in other fields such as spraying fire extinguishing liquid in forest fires, aerial photography, power line inspection, environmental monitoring, forest fire prevention, and disaster inspection.

[0096] Such as Figure 1 AndFigure 2 As shown in Figure 2 , the fuselage assembly 10 for the unmanned aerial vehicle 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, as Figure 2 shown in Figure 2 , the connecting beam 11 is fixedly connected to the mounting frame 12, and the connecting beam 11 is an integrally formed part. The plurality of arms 2 are arranged on the connecting beam 11 at intervals. It should be noted that the mounting frame 12 can be used to mount the battery and liquid storage container of the unmanned aerial vehicle 100, etc.

[0098] It can be seen from this that in the fuselage assembly 10 of the unmanned aerial vehicle 100, the mounting frame 12 and the plurality of arms 2 can both be arranged on the connecting beam 11. And the structural setting that the connecting beam 11 is an integrally formed part can, to a certain extent, improve the production efficiency of the connecting beam 11, improve the structural strength of the connecting beam 11, and at the same time can effectively improve the assembly efficiency of the fuselage assembly 10. And compared with the prior art, the connecting beam 11 does not need to be assembled, and thus the use of connecting parts (such as screws) etc. can be effectively reduced, and furthermore, the weight of the connecting beam 11 can be reduced to a certain extent, making the fuselage assembly 10 lightweight.

[0099] For the fuselage assembly 10 of the unmanned aerial vehicle 100 according to an embodiment of the present invention, by setting the connecting beam 11 to be an integrally formed part, 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 at the same time the assembly efficiency of the fuselage assembly 10 can be effectively improved. And compared with the prior art, the connecting beam 11 does not need to be assembled, and thus the use of connecting parts (such as screws) etc. can be effectively reduced, and furthermore, the weight of the connecting beam 11 can be reduced to a certain extent, making the fuselage assembly 10 lightweight.

[0100] As Figure 1 and Figure 8 shown in Figure 1 and Figure 8 , 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 are 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, and 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 from this 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. Thus, it can be known that the structure of the connecting beam 11 is simple, and at the same time the connection positions with the mounting frame 12 and the arms 2 are reasonably distributed, which can avoid interference between the arms 2 and the mounting frame 12 to a certain extent when connecting and assembling with the connecting beam 11, and is beneficial to improving the structural stability and reliability of the fuselage assembly 10.

[0101] As 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. Thereby, the overall structural strength of the connecting beam 11 can be improved, and then the reliability of the fuselage assembly 10 can be improved, and the reliability of the unmanned aerial vehicle 100 can be improved.

[0102] As Figure 6 , Figure 7 and Figure 10 As shown, according to some embodiments of the present invention, the first beam body 111 is recessed away from the mounting frame 12 to define a first mating groove 1110. A first connecting portion 1114 is provided on the inner wall of the first mating groove 1110, and a second connecting portion 124 is provided on the mounting frame 12. A part of the mounting frame 12 is adapted to extend into the first mating groove 1110 and is fixedly connected to the second connecting portion 124 through the first connecting portion 1114. It can be seen therefrom 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. At the same time, the structural setting that a part of the mounting frame 12 extends into the first mating groove 1110 can also support and position the mounting frame 12 through the inner wall of the first mating groove 1110, thereby improving the structural reliability of the fuselage assembly 10 and also facilitating the operator to connect the first connecting portion 1114 and the second connecting portion 124.

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

[0104] It can be seen from this that the structures of the first connecting portion 1114 and the second connecting portion 124 are simple, and the mating 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 both the first connecting portion 1114 and the second connecting portion 124 are formed as bosses, when the mounting frame 12 is mated and connected to the connecting beam 11, the boss formed by the first connecting portion 1114 needs to be aligned with the boss formed by the second connecting portion 124, and the first connecting hole 11141 needs to be opposite to the second connecting hole, so that the first connecting portion 1114 and the second connecting portion 124 can be fixedly connected through the connecting member. This facilitates the operator to more accurately align the first connecting portion 1114 with the second connecting portion 124, and can improve the mating connection efficiency of the mounting frame 12 and the connecting beam 11 to a certain extent.

[0105] As Figure 6 shown, in some embodiments of the present invention, a stop portion 1116 is provided on the inner wall of the first mating groove 1110. At least a part of the end surface of the side of the stop portion 1116 facing the mounting frame 12 forms a stop surface 1115. At least a part of the mounting frame 12 extending into the first mating groove 1110 is adapted to abut against the stop surface 1115 so that the first connecting portion 1114 and the second connecting portion 124 are mated and connected. It can be seen from this that the setting of the stop portion 1116 can limit the mounting frame 12 to a certain extent, so that when at least a part of the mounting frame 12 extending into the first mating groove 1110 abuts against the stop surface 1115, the positions of the first connecting portion 1114 and the second connecting portion 124 can be made generally opposite, and then it is convenient to mate and connect the first connecting portion 1114 and the second connecting portion 124, which is beneficial to improving the connection and assembly efficiency of the mounting frame 12 and the connecting beam 11.

[0106] As Figure 6 shown, in some embodiments of the present invention, there are a plurality of stop portions 1116 which are spaced apart. Each stop portion 1116 extends along the circumferential direction of the inner wall of the first mating groove 1110 to form a reinforcing rib structure. This is not only beneficial to improving the connection and assembly efficiency of the mounting frame 12 and the connecting beam 11, but also can improve the structural strength of the connecting beam 11 and the reliability of the fuselage assembly 10.

[0107] As Figure 6 、 Figure 8 and Figure 9As shown, in some embodiments of the present invention, a wire passing hole 1118 penetrating through the first beam body 111 is further provided on the inner wall of the first mating groove 1110, and the wire passing hole 1118 is arranged away from the mounting frame 12. Thus, it is convenient for some connecting wires of the drone 100 to pass through the wire passing hole 1118 and penetrate into the first mating groove 1110, which is beneficial to avoid the connecting wires being scratched or damaged when the drone 100 rubs against external objects (such as tree branches) during flight. Furthermore, the safety and reliability of the drone 100 during use can be improved, and at the same time, the appearance beauty of the fuselage assembly 10 can be enhanced, and the occupied space of the fuselage assembly 10 can be reduced.

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

[0109] As Figure 6 , Figure 7 , Figure 13 and Figure 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. The pivot holes 1126 on different side walls are opposite 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. There are multiple mating holes 2122, which are in one-to-one correspondence and coaxially arranged with the pivot holes 1126 on the pivoting portion 112. Thus, it can be seen that when the arm 2 is matingly connected to the connecting beam 11, a part of the pivot member 21 needs to be extended into the second mating groove 1120 so that the multiple mating holes 2122 are in one-to-one correspondence and coaxially arranged with the multiple pivot holes 1126. Furthermore, a transfer shaft can be sequentially passed through the relatively corresponding pivot holes 1126, mating holes 2122, mating holes 2122, and pivot holes 1126, thereby realizing the pivotal connection between the pivot member 21 and the pivoting portion 112, and further enabling the arm 2 to be pivotally connected to the connecting beam 11.

[0110] Specifically, as Figure 6 and Figure 7As shown, reinforcing protrusions 1127 are provided on the outer peripheral wall of the second mating groove 1120, and the reinforcing protrusions 1127 are arranged around the pivot hole 1126. Thereby, the reliability after the arm 2 is pivotally connected to the connecting beam 11 can be improved, and the structural strength of the connecting beam 11 can be enhanced.

[0111] As Figure 6 , Figure 8 and Figure 9 As shown, in some embodiments of the present invention, the mating portion 113 is recessed away from the mounting frame 12 to define a third mating groove 1130. The third mating groove 1130 communicates with the second mating groove 1120. A part of the pivot member 21 is located in the third mating groove 1130. On the outer peripheral wall of the third mating groove 1130, a first limiting groove 1131 recessed toward the third mating groove 1130 is provided, and a limiting protrusion 1132 is provided on the bottom wall of the first limiting groove 1131. It can be seen therefrom that the arm 2 is cooperatively connected to the connecting beam 11 through the pivot member 21. At the same time, it can be known that the recessed direction of the first limiting groove 1131 is opposite to the recessed direction of the third mating groove 1130. The arrangement 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] As Figure 8 As shown, in some embodiments of the present invention, a second reinforcing rib 1133 is provided at the connection between the mating portion 113 and the pivot portion 112. Thereby, the structural strength of the second beam body 114 can be improved, and further the overall structural strength of the connecting beam 11 can be enhanced, the reliability of the fuselage assembly 10 can be improved, and the reliability of the drone 100 can be improved.

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

[0114] As Figure 1 and Figure 5 As shown, according to some embodiments of the present invention, the fuselage assembly 10 further includes two protective frames 14. The two protective frames 14 are spaced apart and provided on the first beam body 111 and are located on the side of the first beam body 111 away from the mounting frame 12. Thereby, components that need to be protected in the drone 100 can be arranged between the two protective frames 14. For example, the electronic control module 7 of the drone 100 can be arranged between the protective frames 14. Further, the two protective frames 14 can protect the electronic control module 7.

[0115] As Figure 1 ,Figures 6 - 9 As shown, in some embodiments of the present invention, a connecting column 1117 is provided on the first beam body 111, and an insertion hole 11171 is provided on the connecting column 1117. A part of the protective frame 14 is adapted to be inserted into the insertion hole 11171 to cooperate and connect with the first beam body 111. It can be seen therefrom that the cooperation mode between 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 therefrom that the extending direction of the first beam body 111 is different from that 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 body 114 extends upward relative to the first beam body 111 is 10° - 35°. Optionally, the angle at which the second beam body 114 extends upward relative to the first beam body 111 is 12°, 19°, 21° or 32°. It should be noted that in a vertical plane parallel to the central axis of the first beam body 111, the included angle between the central axis of the second beam body 114 and the positive projection of the central axis of the first beam body 111 is the angle at which the second beam body 114 extends upward relative to the first beam body 111.

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

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

[0120] The drone 100 according to an embodiment of the present invention, by providing the fuselage assembly 10 according to the above embodiments of the present invention. Thus, 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 at the same time, the assembly efficiency of the drone 100 can be improved. And compared with the prior art, the connecting beam 11 does not need to be assembled, and thus the use of connecting parts and the like can be effectively reduced, and the weight of the connecting beam 11 can also be reduced to a certain extent, making the drone 100 lighter.

[0121] Next, refer to Figures 1 - 33Describe the drone 100 according to specific embodiments of the present invention. It should be understood that the following description is merely exemplary and is intended to explain the present invention, and should not be construed as a limitation of the present invention. Specifically, the drone 100 can be used for operations such as pesticide spraying or water irrigation on crops in the farming industry. Of course, the drone 100 can also be used in other fields such as spraying fire extinguishing liquid in forest fires, aerial photography, power line inspection, environmental monitoring, forest fire prevention, and disaster inspection.

[0122] Reference Figures 1 - 33 , the drone 100 according to an embodiment of the present invention includes: a fuselage assembly 10, landing gears 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 the fuselage 1 and the arms 2. The landing gears 3 are fixed below the fuselage 1 to ensure the stability of the takeoff and landing of the drone 100. 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 flight of the drone 100. The liquid storage container 5 is carried on the fuselage 1 for containing items to be sprayed or transported, the battery 6 is fixed to the fuselage 1, the power assembly 4 provides power for the drone 100, and the electronic control module 7 is fixed to the fuselage 1 for controlling the flight attitude of the drone 100.

[0123] Refer to Figures 1 - 9 , the fuselage 1 includes a connecting beam 11 and a mounting frame 12 fixedly connected to the connecting beam 11. Among them, the connecting beam 11 includes a first beam body 111 and two second beam bodies 114 connected to both ends of the first beam body 111. Each second beam body 114 includes a pivoting portion 112 and a mating portion 113 connected to each other.

[0124] Refer to 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. Among them, 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 jointly enclose a first mating 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 stopping surface 1115 are formed on the inner wall of the first mating groove 1110. Among them, 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 provided on the first connecting portion 1114.

[0125] Preferably, a stop portion 1116 is further formed on the inner wall of the first mating groove 1110. The stop portion 1116 can extend transversely 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 mounting 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 post 1117 is further formed on the outer peripheral surface of the upper end wall 1111. The connecting post 1117 is provided with an insertion hole 11171 with an opening facing forward. A wire passing hole 1118 is also provided on the front end wall 1113.

[0127] Referring to Figures 6 - 9 , there are two pivot joints 112. Each pivot joint 112 is also formed into a structure with a cross-section substantially in the shape of a "U". Each pivot joint 112 extends upward and backward along the end face of the first beam body 111. Among them, the angle at which each pivot joint 112 extends upward relative to the first beam body 111 is 10° - 35°. Specifically, the angle at which each pivot joint 112 extends upward relative to the first beam body 111 is 12°, 19°, 21°, or 32°. Among them, the angle at which each pivot joint 112 extends backward relative to the first beam body 111 is 5° - 20°. Specifically, the angle at which each pivot joint 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 pivot joint 112. The second mating groove 1120 communicates with 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. First reinforcing ribs 1125 are formed at the joints of the upper pivoting wall 1121 and the upper end wall 1111, and the lower pivoting wall 1122 and the lower end wall 1112 to increase the connection strength between the pivoting wall 1121 and the upper end wall 1111, and the lower pivoting wall 1122 and the lower end wall 1112. The upper pivoting wall 1121, the lower pivoting wall 1122, and the front pivoting wall 1123 enclose a second mating groove 1120 with an opening facing backward. The upper pivoting wall 1121 and the lower pivoting wall 1122 are respectively provided with coaxially arranged pivoting holes 1126. Antenna mounting seats 1124 vertically extend from the upper pivoting wall 1121 and the lower pivoting wall 1122 respectively. The antenna mounting seat 1124 is provided with a communication hole communicating with the second mating groove 1120.

[0129] Further, as Figure 9 shown, a mating portion 113 extends from the end of the pivoting portion 112. Second reinforcing ribs 1133 are respectively formed between the outer peripheral surface of the mating 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 mating portion 113 is formed into a structure with an arc-shaped cross-section. A third mating groove 1130 with an opening facing backward is formed in the mating portion 113. The third mating groove 1130 is arc-shaped and communicates with the second mating groove 1120. A first limiting groove 1131 is also formed on the outer peripheral surface of the mating portion 113, and a limiting protrusion 1132 is formed on the bottom wall of the first limiting groove 1131.

[0130] Referring to Figures 6 - 7 and Figures 10 - 12 shown, the mounting frame 12 is adapted to be connected to 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. Second connecting portions 124 are formed on the front end plate 121 and the two side plates 123. The second connecting portions 124 are adapted to be connected to the first connecting portions 1114 to fixedly connect the mounting frame 12 to the first beam body 111. During installation, when the end face of the front end plate 121 abuts against the abutting surface 1115 on the inner wall of the first mating groove 1110, each second connecting portion 124 is opposite to each first connecting portion 1114.

[0131] Referring to Figure 3 、 Figures 10 - 12, the front end plate 121, the rear end plate 122, and the two side plates 123 jointly enclose an installation cavity 120 that penetrates up and down. The liquid storage container 5 and the battery 6 are adapted to be inserted into the installation cavity 120 and detachably connected to one or more of the front end plate 121, the rear end plate 122, and 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] Further, the installation frame 12 further includes a partition plate 125, and both ends of the partition plate 125 are respectively connected to the ends of the two second side plate portions 1232 close to the transition portion 1233. The partition 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, referring to Figure 12 , a positioning groove 1234 is further formed on the first side plate portion 1231, a second installation protrusion 12311 is formed on the side wall of the first side plate portion 1231, and a positioning hole 1235 is provided on the second installation protrusion 12311. The second installation protrusion 12311 is used to install the landing gear 3.

[0134] Preferably, the installation frame 12 further includes a reinforcing plate 126, the reinforcing plate 126 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 in cooperation with the reinforcing hole 1119 on the first beam body 11 to strengthen the strength between the installation frame 12 and the connecting beam 11.

[0135] Preferably, referring to Figure 3 and Figure 10 , battery guiding modules 127 and liquid storage container guiding modules 128 are further arranged 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 guiding modules 127 and the liquid storage container guiding modules 128 can guide, damp, and fix the battery 6 and the liquid storage container 5.

[0136] Referring to Figures 1 - 5 and Figures 13 - 14 , there are two arm bodies 2, and the two arm bodies 2 are respectively rotatably connected to the two pivot joints 112 of the connecting beam 11. Among them, each arm body 2 includes a pivot member 21, an arm rod 22, and a support arm assembly 23.

[0137] Referring to Figure Figure 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 Figure 13 and Figure 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 Figure 17 The locking assembly 233 includes a first locking component 2331 , a second locking component 2332 and a locking member 2333 .

[0142] Reference Figure 13 and Figure 18, the first locking fitting 2331 includes a first circular ring portion 23311, two first pivot protrusions 23312, a pivot block 23313, and a first locking portion 23314 that extend outward along the outer peripheral surface of the first circular ring portion 23311. The two first pivot protrusions 23312 are pivotally connected to the end of the support arm 232 away from the mounting member 231 through a pivot member 2322. A groove portion 23315 is formed on the side wall of the first locking portion 23314.

[0143] Referring to Figures 17 - 19 , the second locking fitting 2332 includes a second circular ring portion 23321, two second pivot protrusions 23322, and a second locking portion 23323 that extend outward along the outer peripheral surface of the second circular ring portion 23321. A third limiting groove 23324 is further formed on the inner peripheral surface of the second circular ring portion 23321. The two second pivot protrusions 23322 are pivotally connected to the pivot block 23313, so that the first circular ring portion 23311 and the second circular ring portion 23321 can be located on the same circumferential surface.

[0144] Referring to Figure 17 and Figure 20 , the locking member 2333 is connected to the second locking portion 23323 through a pivot rod 2334. The locking member 2333 includes a mating boss 23331, a third pivot protrusion 23332 that extends outward along the first end surface of the mating boss 23331, and a connecting rod 23333 (which can be a separate part) that extends along the second end surface of the mating boss 23331. Further, a protrusion portion 23334 is formed on the second end surface.

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

[0146] First, rotate the machine arm 2 to fit the first outer wall 2111 of the pivot member 21 into the third mating groove 1130 of the mating portion 113. So that the mating portion 113 and the second outer wall 2112 are located on the same circumferential surface, and the mating portion 113 and the second outer wall 2112 enclose a complete cylindrical tube. At the same time, the first limiting groove 1131 on the mating portion 113 and the second limiting groove 2113 on the peripheral wall of the second outer wall 2112 together form a complete circular ring groove.

[0147] Secondly, the support arm 232 fits the first circular ring portion 23311 of the first locking fitting 2331 and the second circular ring portion 23321 of the second locking fitting 2332 into the second limiting groove 2113 and the first limiting groove 1131 respectively. Among them, the limiting protrusion 1132 on the bottom wall of the first limiting groove 1131 cooperates with the third limiting groove 23324 on the inner peripheral surface of the second circular ring portion 23321 to prevent the second circular ring portion 23321 from rotating with the bottom wall of the first limiting groove 1131.

[0148] Finally, the locking member 2333 locks the first circular ring portion 23311 of the first locking fitting 2331 and the second circular ring portion 23321 of the second locking fitting 2332, such that the first circular ring portion 23311 and the second circular ring portion 23321 form a circular sleeve coaxially arranged with the cylindrical tube formed by the mating portion 113 and the second outer wall 2112. The first circular ring portion 23311 and the second circular ring portion 23321 lock the second outer wall 2112 of the pivot member 21 and the mating portion 113. Among them, the protrusion portion 23334 on the second end face of the locking member 2333 cooperates with the groove portion 23315 on the side wall of the first locking portion 23312, so that the first circular ring portion 23311 and the second circular ring portion 23321 squeeze the outer peripheral wall of the second outer wall 2112 of the pivot member 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, which will not be elaborated here.

[0150] Refer to Figure 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 symmetrically installed on the lower side of the fuselage 1 in the left-right direction. Each support leg assembly 301 includes a tripod support leg 31, a first fitting 32, a second fitting 34, and a landing gear connection assembly 33. The tripod support leg 31 is connected to the lower side of the fuselage 1 through the first fitting 32, the second fitting 34, and the landing gear connection assembly 33.

[0151] Refer to Figure 22 , the tripod support leg 31 includes: a front support leg 311, a bottom support leg 312, and a rear support leg 313. 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. Among them, the bottom support leg 312 is tubular and extends in the front-rear direction in the horizontal plane. The front support leg 311 includes a first leg segment 3111 connected to the bottom support leg 312, a second leg segment 3112 connected to the first leg segment 3111, and a support segment 3113 connected to the second leg segment 3112. The support segment 3113 is arranged parallel to the bottom support leg 312.

[0152] Refer to Figure 12 and 21 -23, the support segment 3113 of the tripod support leg 31 fits into the positioning groove 1234 and is connected to the second mounting protrusion 12311 through the connection protrusion 341 provided on the second fitting 34.

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

[0154] Refer to Figure 21 , Figures 24 - 25, the 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 segment 3112 to the lower end wall 1112 of the first beam body 111.

[0155] Referring to Figures 30 - 33 , the power assembly 4 includes a connection seat 41, a mounting assembly 42, a power unit 43, and a driving device 44.

[0156] The connection 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 extension portion 412 extending along the upper end surface of the mounting portion 413. A fitting hole 4110 is formed inside the fitting portion 411, and the end of the machine arm rod 22 away from the fuselage 1 is adapted to be fitted in the fitting hole 4110.

[0157] The mounting assembly 42 includes a mounting post 421, a bearing 422, a connection kit 423, a fixed support 424, and a rotating member 425. Among them, both ends of the mounting post 421 are rotatably fixed on the extension portion 412 through the bearings 422. The connection kit 423 and the fixed support 424 are fixedly connected to the mounting post 421. The rotating member 425 is connected to the mounting post 421.

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

[0159] Referring to Figure 31 and Figure 32 , the driving device 44 includes a steering gear 441, a transmission device, a transmission shaft 442, and a connecting rod assembly 443. Among them, 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 respectively pivotally connected to the connecting rod 4433.

[0160] Referring to Figure 26 and Figure 27 , the liquid storage container 5 includes a container body 51 having a liquid storage cavity 50 for storing liquid medicine; the container body 51 includes an upper box body 511 and a lower box body 512 vertically extending downward from the bottom of the upper box body 511. The upper box body 511 and the lower box body 512 are integrally formed and jointly form the liquid storage cavity 50. The upper box body 511 and the lower box body 512 form a "T" shape.

[0161] Referring to Figure 2 and Figure 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 , Figure 28 and Figure 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. An airframe assembly for a drone, characterized in that, Comprising: Installation frame; Connecting beam, which is fixedly connected to the installation frame; Multiple arms, which are spaced apart on the connecting beam; Wherein, 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 are connected to the first beam body, the first beam body is cooperatively connected to the installation frame, the arms correspond to the second beam bodies one by one, and each arm is connected to the corresponding second beam body; Each second beam body includes a pivoting portion, the pivoting portion is connected to the first beam body, the pivoting portion is recessed away from the installation frame to define a second fitting groove, and one end of the arm extends into the second fitting groove and is pivotally connected to the pivoting portion; Pivoting holes are respectively provided on two opposite side walls of the second fitting groove, and the pivoting holes on different side walls are opposite and coaxially arranged; Each arm includes a pivoting member and an arm rod, one end of the arm rod is fixed on the pivoting member, and a part of the pivoting member is located in the second fitting groove; A plurality of fitting holes are provided on the part of the pivoting member located in the second fitting groove, and the fitting holes are in one-to-one correspondence and coaxially arranged with the pivoting holes on the pivoting portion; 2. The fuselage assembly for a drone according to claim 1, characterized in that, Each second beam body further includes a fitting portion connected to the pivoting portion, the fitting portion is recessed away from the installation frame to define a third fitting groove, the third fitting groove communicates with the second fitting groove, and a part of the pivoting member is located in the third fitting groove; 3. The fuselage component for a drone according to claim 2, characterized in that, A first limiting groove recessed towards the third fitting groove is provided on the outer peripheral wall of the third fitting groove, and a limiting protrusion is provided on the bottom wall of the first limiting groove; 4. The fuselage assembly for a drone according to claim 1, characterized in that, The pivoting member includes a sleeving portion and two pivoting convex portions extending along the sleeving portion, the sleeving 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 sleeving portion jointly define a sleeving hole, and the sleeving hole is used for cooperating with one end of the arm rod; 5. The fuselage assembly for a drone according to claim 4, characterized in that, The two pivoting convex portions respectively extend along the radial direction of the sleeving portion, a fitting hole is provided on each pivoting convex portion, and the two fitting holes are in one-to-one correspondence and coaxially arranged with the pivoting holes on the pivoting portion respectively; 6. The fuselage assembly for an unmanned aerial vehicle according to claim 1, characterized in that, A reinforcing protrusion is provided on the outer peripheral wall of the second fitting groove, and the reinforcing protrusion is arranged around the pivoting hole; 7. The fuselage assembly for an unmanned aerial vehicle 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, and the upper end wall, the lower end wall, and the front end wall jointly enclose a first fitting groove with an opening facing backwards; 8. The fuselage assembly for a drone according to claim 7, wherein, 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, and the upper pivoting wall, the lower pivoting wall, and the front pivoting wall respectively extend along the ends of the upper end wall, the lower end wall, and the front end wall; 9. The fuselage assembly for a drone according to claim 8, characterized in that, First reinforcing ribs are formed at the joints of the upper pivoting wall and the upper end wall and the lower pivoting wall and the lower end wall; 10. The fuselage assembly for a drone according to claim 8, characterized in that, The upper pivoting wall, the lower pivoting wall, and the front pivoting wall enclose the second fitting groove with an opening facing backwards.

11. The fuselage assembly for a drone according to claim 7, characterized in that, A first connecting portion is formed on the inner wall of the first mating groove, and the first connecting portion is adapted to extend along 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, wherein, A stopping portion is formed on the inner wall of the first mating groove, and the stopping portion is adapted to extend transversely and / or longitudinally along the inner walls of the upper end wall, the lower end wall, and the front end wall.

13. The fuselage assembly for a drone according to claim 12, characterized in that, At least a part of the end face of the stopping portion facing the mounting frame forms a stopping surface, and the stopping surfaces located on the upper end wall and the lower end wall are coplanar.

14. The fuselage assembly for a drone according to any one of claims 1-13, characterized in that, A second reinforcing rib is provided at the connection between the mating portion and the pivoting portion.

15. The fuselage assembly for a drone according to any one of claims 1-13, characterized in that, The first beam body and the second beam body are integrally formed.

16. The fuselage assembly for a drone according to any one of claims 1-13, characterized in that, An antenna mounting seat is provided on the pivoting portion, and a communication hole is provided on the antenna mounting seat, and the communication hole communicates with the space defined by the second mating groove.

17. The fuselage assembly for a drone according to any one of claims 1-13, characterized in that, It further includes two protective frames, and the two protective frames are provided on the first beam body at intervals and are located on the side of the first beam body away from the mounting frame.

18. The fuselage assembly for an unmanned aerial vehicle according to claim 17, wherein, A connecting column is provided on the first beam body, and an insertion hole is provided on the connecting column, and a part of the protective frame is adapted to be inserted into the insertion hole to cooperate with and connect to the first beam body.

19. The fuselage assembly for a drone according to any one of claims 1-13, characterized in that, The second beam body extends upward and backward relative to the first beam body.

20. The fuselage assembly for a drone according to claim 19, characterized in that, The angle at which the second beam body extends upward relative to the first beam body is 10° - 35°.

21. The fuselage assembly for a drone according to claim 19, characterized in that, The angle at which the second beam body extends backward relative to the first beam body is 5° - 20°.

22. A drone, characterized in that, It includes a fuselage assembly for an unmanned aerial vehicle according to any one of claims 1 - 21.

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