Aircraft fuselage assembly and aircraft having the same

Abstract

The present invention discloses a fuselage assembly for an aircraft and an aircraft having the same. The fuselage assembly includes: a fuselage; a plurality of arms, the plurality of arms being distributed along the circumference of the fuselage, one end of each arm being rotatably connected to the fuselage; a plurality of support arms, the number of the support arms being the same as the number of the arms and corresponding to each other, each support arm being adjacent to a corresponding arm, one end of each support arm being rotatably connected to the fuselage, and a locking assembly being provided at an end of each support arm away from the fuselage, the support arm being engaged with the corresponding arm via the locking assembly; wherein each arm has an extended position and a folded position, and the locking assembly has a locked state and an unlocked state. In the locked state, the locking assembly locks the arm in the extended position, and in the unlocked state, the locking assembly is disengaged from the arm, allowing the arm to rotate to the folded position. According to the fuselage assembly of the present invention, the arm can be folded, and the arm is structurally stable and reliable when in the extended position.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft, and in particular to an aircraft fuselage assembly and an aircraft having the same. Background Art

[0002] Multi-rotor aircraft have relatively long arms, which take up a lot of space. Some aircraft in the related art have arms that cannot be folded, while others can be folded, but these arms are structurally unstable when deployed. 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 object of the present invention is to provide an aircraft fuselage assembly having foldable arms that are structurally stable and reliable when in the unfolded position.

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

[0005] According to an embodiment of the present invention, the fuselage assembly of an aircraft includes: a fuselage; a plurality of arms, wherein the plurality of arms are distributed along the circumference of the fuselage, and one end of each arm is rotatably connected to the fuselage; a plurality of support arms, wherein the number of the support arms is the same as the number of the arms and corresponds one to one, each support arm is adjacent to the corresponding arm, and one end of each support arm is rotatably connected to the fuselage, and a locking assembly is provided at the end of each support arm away from the fuselage, and the support arm cooperates with the corresponding arm through the locking assembly; wherein each arm has an expanded position and a folded position, and the locking assembly has a locked state and an unlocked state, wherein in the locked state, the locking assembly locks the arm in the expanded position, and in the unlocked state, the locking assembly is disengaged from the arm, and the arm can be rotated to the folded position.

[0006] According to the fuselage assembly of the aircraft of an embodiment of the present invention, one end of each support arm is rotatably connected to the fuselage, and a locking assembly is provided at the end of each support arm away from the fuselage, and the support arm cooperates with the corresponding arm through the locking assembly. Each arm has an unfolded position and a folded position, and the locking assembly has a locked state and an unlocked state. In the locked state, the locking assembly locks the arm in the unfolded position. In the unlocked state, the locking assembly is disengaged from the arm, and the arm can be rotated to the folded position. In this way, the arm can be folded and is easy to operate. When the arm is in the unfolded position, the support arm supports the arm, so that the arm is structurally stable and reliable when in the unfolded position.

[0007] According to some embodiments of the present invention, the fuselage includes a connecting beam and a mounting frame, the connecting beam is fixedly connected to the mounting frame, and one end of each of the arms is rotatably connected to the connecting beam.

[0008] According to some embodiments of the present invention, each of the arms includes a pivot member and an arm rod, one end of the arm rod is fixed to the pivot member, and the pivot member is rotatably connected to the connecting beam. In the locked state, the locking assembly cooperates with the connecting beam and the pivot member respectively to lock the arm in the deployed position.

[0009] In some embodiments of the present invention, a mating groove is formed on the connecting beam, and pivot holes are respectively provided on two opposite side walls of the mating groove. The pivot holes on different side walls are oppositely and coaxially arranged. A portion of the pivot member is located in the mating groove, and a mating hole is provided on the portion of the pivot member located in the mating groove. There are multiple mating holes and they correspond one-to-one to the pivot holes on the connecting beam and are coaxially arranged.

[0010] In some embodiments of the present invention, a first limiting groove that is recessed toward the mating groove is provided on the outer side wall of the mating groove, and a second limiting groove that is recessed toward the mating groove is provided on the portion of the pivot member that is not provided with the mating groove. The second limiting groove is connected to the first limiting groove to form an annular groove. In the locked state, the locking assembly is sleeved on the annular groove formed by the second limiting groove and the first limiting groove to lock the arm in the deployed position.

[0011] In some embodiments of the present invention, the locking assembly includes: a first locking accessory, a second locking accessory and a locking piece, the first locking accessory is pivotally connected to the corresponding support arm, the first end of the first locking accessory is pivotally connected to the first end of the second locking accessory, the second end of the first locking accessory is detachably connected to the second end of the second locking accessory via the locking piece, in the locked state, the second end of the first locking accessory is connected to the second end of the second locking accessory via the locking piece to be sleeved on the first limiting groove and the second limiting groove to lock the arm in the expanded position; in the unlocked state, the locking piece is disengaged from the first locking accessory so that the second end of the first locking accessory and the second end of the second lock accessory are separable.

[0012] In some embodiments of the present invention, a limiting protrusion is provided on one of the bottom wall of the first limiting groove and the inner side wall of the second lock accessory, and a third limiting groove is provided on the other of the bottom wall of the first limiting groove and the inner side wall of the second lock accessory, and the limiting protrusion is suitable for extending into the third limiting groove.

[0013] In some embodiments of the present invention, two first locking parts are provided at an interval on the second end of the first locking accessory, and two second locking parts are provided at an interval on the second end of the second locking accessory, and a rotatable pivot rod is provided between the two second locking parts, and a locking hole is provided on the pivot rod, and a locking slot is provided on a side of at least one of the two first locking parts away from the second locking part. The locking piece includes a locking body, a locking wrench and a locking connecting rod, and the locking connecting rod is provided on the locking body, the locking wrench is provided on the locking body and is located on the side of the locking body away from the locking connecting rod, and a locking protrusion is further provided on the side of the locking body where the locking connecting rod is provided, and a part of the locking connecting rod passes through the space defined by the two first locking parts to extend into the locking hole, and in the locked state, the locking protrusion is clamped in the locking slot.

[0014] In some embodiments of the present invention, the locking connecting rod is axially movably disposed in the locking hole. In the unlocked state, the locking connecting rod moves in a direction away from the locking hole to disengage the locking protrusion from the locking slot.

[0015] According to some embodiments of the present invention, the support arm is connected to the mounting frame through a connecting member, the connecting member includes a mounting base and a transition portion, the mounting base is fixedly connected to the mounting frame, the transition portion is provided on a side of the mounting base away from the mounting frame, a pivot member is provided on the support arm, and the pivot member is pivotally connected to the transition portion.

[0016] An aircraft according to an embodiment of the present invention includes the fuselage assembly according to the above embodiment of the present invention.

[0017] The aircraft according to the embodiment of the present invention is provided with the fuselage assembly according to the above embodiment of the present invention, so that the arms can be folded, and the structure of the arms is stable and reliable when in the unfolded position.

[0018] Additional aspects and advantages of the present invention will be set forth in part in the description which follows and, in part, will be obvious from the description which follows, or may be learned by practice of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] The above and / or additional aspects and advantages of the present invention will become apparent and readily understood from the following description of the embodiments with reference to the accompanying drawings, in which:

[0020] Figure 1 is a schematic diagram of an aircraft according to some embodiments of the present invention;

[0021] Figure 2 is a schematic diagram of an aircraft according to some embodiments of the present invention;

[0022] Figure 3 is a schematic diagram of an aircraft according to some embodiments of the present invention;

[0023] Figure 4 yes Figure 3 Enlarged view of part A;

[0024] Figure 5 is a schematic diagram of an aircraft according to some embodiments of the present invention;

[0025] Figure 6 is a schematic diagram of a connecting beam according to some embodiments of the present invention;

[0026] Figure 7 is a schematic diagram of a connecting beam according to some embodiments of the present invention;

[0027] Figure 8 is a schematic diagram of a connecting beam according to some embodiments of the present invention;

[0028] Figure 9 is a schematic diagram of a connecting beam according to some embodiments of the present invention;

[0029] Figure 10 is a schematic diagram of a mounting frame according to some embodiments of the present invention;

[0030] Figure 11 is a schematic diagram of a mounting frame according to some embodiments of the present invention;

[0031] Figure 12 is a schematic diagram of a mounting frame according to some embodiments of the present invention;

[0032] Figure 13 is a schematic diagram of a partial structure of an aircraft according to some embodiments of the present invention;

[0033] Figure 14 is a schematic diagram of a machine arm according to some embodiments of the present invention;

[0034] Figure 15 is a schematic diagram of a pivotal member according to some embodiments of the present invention;

[0035] Figure 16 is a schematic diagram of a connector according to some embodiments of the present invention;

[0036] Figure 17 is a schematic diagram of a locking assembly according to some embodiments of the present invention;

[0037] Figure 18 is a schematic diagram of a first lock assembly according to some embodiments of the present invention;

[0038] Figure 19is a schematic diagram of a second lock assembly according to some embodiments of the present invention;

[0039] Figure 20 is a schematic diagram of a locking member according to some embodiments of the present invention;

[0040] Figure 21 is a schematic diagram of a partial structure of an aircraft according to some embodiments of the present invention;

[0041] Figure 22 is a schematic diagram of a tripod support leg according to some embodiments of the present invention;

[0042] Figure 23 is a schematic diagram of a second fitting according to some embodiments of the present invention;

[0043] Figure 24 is a schematic diagram of a first fixing member according to some embodiments of the present invention;

[0044] Figure 25 is a schematic diagram of a second fixing member according to some embodiments of the present invention;

[0045] Figure 26 is a schematic diagram of a liquid storage container according to some embodiments of the present invention;

[0046] Figure 27 is a schematic diagram of a liquid storage container according to some embodiments of the present invention;

[0047] Figure 28 is a schematic diagram of a first antenna according to some embodiments of the present invention;

[0048] Figure 29 is a schematic diagram of a second antenna according to some embodiments of the present invention;

[0049] Figure 30 is a schematic diagram of a power assembly according to some embodiments of the present invention;

[0050] Figure 31 yes Figure 30 Cross-sectional view in the middle BB direction;

[0051] Figure 32 is a schematic diagram of a power assembly according to some embodiments of the present invention;

[0052] Figure 33 is a schematic diagram of a connection socket according to some embodiments of the present invention.

[0053] Reference numerals:

[0054] Aircraft 100, fuselage assembly 10,

[0055] Body 1,

[0056] Connecting beam 11, first beam body 111, first matching groove 1110, upper end wall 1111, lower end wall 1112,

[0057] Front end wall 1113, first connecting portion 1114, first connecting hole 11141, stop surface 1115, stop portion 1116,

[0058] Connecting column 1117, mating hole 11171, wire hole 1118, reinforcement hole 1119,

[0059] The pivoting portion 112, the second matching groove 1120, the upper pivoting wall 1121, the lower pivoting wall 1122, the front pivoting wall 1123,

[0060] Antenna mounting base 1124, first reinforcing rib 1125, pivot hole 1126, reinforcing protrusion 1127,

[0061] Matching portion 113, third matching groove 1130, first limiting groove 1131, limiting protrusion 1132, second reinforcing rib 1133,

[0062] The second beam 114 cooperates with the groove 115.

[0063] Mounting frame 12, mounting cavity 120, first mounting cavity 1201, second mounting cavity 1202,

[0064] Front end plate 121, rear end plate 122, side plate 123, first side plate portion 1231, second mounting protrusion 12311,

[0065] The second side plate portion 1232, the transition portion 1233, the positioning groove 1234, the positioning hole 1235,

[0066] The second connecting portion 124, the isolation plate 125, the reinforcing plate 126, the battery guide module 127,

[0067] Liquid storage container guide module 128,

[0068] Mounting frame 13,

[0069] Protective frame 14, protective rod 141, fixed seat 142,

[0070] Arm 2,

[0071] The pivot member 21, the sleeve portion 211, the sleeve hole 2110, the first outer wall 2111, the second outer wall 2112,

[0072] The second limiting groove 2113, the pivoting protrusion 212, the matching hole 2122, the arm rod 22,

[0073] Connector 231, mounting base plate 2311, adapter 2312,

[0074] Support arm 232, support arm rod 2321, pivot member 2322,

[0075] Locking assembly 233, first locking component 2331, first annular portion 23311, first pivoting protrusion 23312,

[0076] Pivot block 23313, first locking portion 23314, locking slot 23315, second locking component 2332,

[0077] The second annular portion 23321, the second pivoting protrusion 23322, the second locking portion 23323, the third limiting groove 23324,

[0078] Locking piece 2333, locking body 23331, locking wrench 23332, locking connecting rod 23333, locking protrusion 23334,

[0079] Pivot rod 2334, locking hole 23341,

[0080] Landing gear 3,

[0081] Support leg assembly 301,

[0082] Tripod support leg 31, front support leg 311, first support leg section 3111, second support leg section 3112, support section 3113,

[0083] Bottom support leg 312, rear support leg 313,

[0084] The first matching piece 32,

[0085] Landing gear connection assembly 33, first fixing member 331, second fixing member 332,

[0086] The second matching piece 34, the connecting protrusion 341,

[0087] Power assembly 4,

[0088] Connecting seat 41, sleeve portion 411, sleeve hole 4110, extension portion 412, mounting portion 413,

[0089] Mounting assembly 42, mounting column 421, bearing 422, connecting kit 423, fixed support 424, rotating member 425,

[0090] Power unit 43, power motor 431, propeller assembly 432,

[0091] Driving device 44, steering gear 441, transmission shaft 442, connecting rod assembly 443, first adapter 4431,

[0092] Second adapter 4432, connecting rod 4433,

[0093] Liquid storage container 5, liquid storage cavity 50, liquid storage cavity 51, upper box 511, mounting groove 5111, lower box 512,

[0094] Battery 6, electronic control module 7, communication module 71, first antenna 711, second antenna 712, flight control module 72,

[0095] NFC reader / writer 8. DETAILED DESCRIPTION

[0096] The following describes embodiments of the present invention in detail. Examples of the embodiments 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 intended only to explain the present invention and are not to be construed as limiting the present invention.

[0097] 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 orientations or positional relationships based on the orientations 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 limiting the present invention. In addition, features defined as "first" or "second" may explicitly or implicitly include one or more of such features. In the description of the present invention, unless otherwise specified, "multiple" means two or more.

[0098] In the description of the present invention, it should be noted that, unless otherwise expressly specified or limited, the terms "mounted," "connected," and "connected" should be understood in a broad sense. For example, they may refer to fixed, detachable, or integral connections; mechanical or electrical connections; direct or indirect connections through an intermediate medium; and internal communication between two components. Those skilled in the art will understand the specific meanings of the above terms in the present invention based on the specific circumstances.

[0099] Reference below Figure 1-Figure 33The fuselage assembly 10 of an aircraft 100 according to an embodiment of the present invention is described. The aircraft 100 may be a drone, which can be used in agricultural operations such as spraying pesticides or watering crops. Of course, the aircraft 100 can also be used in other fields, such as spraying fire extinguishing fluid during forest fires, aerial photography, power inspections, environmental monitoring, forest fire prevention, and disaster inspections.

[0100] like Figure 1-Figure 3 and Figure 5 As shown, the fuselage assembly 10 of the aircraft 100 according to an embodiment of the present invention includes: a fuselage 1 , a plurality of arms 2 and a plurality of support arms 232 .

[0101] Specifically, multiple arms 2 are distributed along the circumference of the fuselage 1. For example, there are two arms 2, and the two arms 2 are distributed on the left and right sides of the fuselage 1. One end of each arm 2 is rotatably connected to the fuselage 1. Therefore, it can be seen that each arm 2 is rotatable relative to the fuselage 1.

[0102] The number of support arms 232 is the same as the number of arms 2 and corresponds one to one. Each support arm 232 is adjacent to the corresponding arm 2. For example, when there are two arms 2, there are also two support arms 232. When the two arms 2 are distributed on the left and right sides of the fuselage 1, the two support arms 232 are also distributed on the left and right sides of the fuselage 1. Each support arm 232 can be located on the rear side of the corresponding arm 2 and adjacent to its corresponding arm 2.

[0103] One end of each support arm 232 is rotatably connected to the fuselage 1. A locking assembly 233 is provided at the end of each support arm 232 away from the fuselage 1. The support arm 232 engages with the corresponding arm 2 through the locking assembly 233. Each arm 2 has an extended position and a folded position. The locking assembly 233 has a locked state and an unlocked state. In the locked state, the locking assembly 233 locks the arm 2 in the extended position. In the unlocked state, the locking assembly 233 disengages from the arm 2, allowing the arm 2 to rotate to the folded position.

[0104] As can be seen, each arm 2 is rotatable relative to the fuselage 1 between an extended position and a folded position. In the locked state, the locking assembly 233 locks the arm 2 in the extended position. This means that in this state, the support arm 232 is connected to the corresponding arm 2 via the locking assembly 233, thereby forming a stable triangular structure with the support arm 232, the arm 2, and the fuselage 1. At the same time, the support arm 232 can support the arm 2, ensuring that the arm 2 is structurally stable and reliable in the extended position.

[0105] In the unlocked state, the locking assembly 233 is disengaged from the arm 2, and the arm 2 can be rotated to the folded position. It can be understood that when the arm 2 is in the folded position, the space occupied by the fuselage assembly 10 can be reduced to a certain extent, thereby reducing the space occupied by the aircraft 100, thereby facilitating the storage and transportation of the aircraft 100.

[0106] It is also understood that the arm 2 can be deployed and folded by simply adjusting the mating relationship between the locking assembly 233 and the arm 2. Simply disengaging the locking assembly 233 from the arm 2 releases the rotational restriction of the arm 2 relative to the body 1, allowing the arm 2 to rotate to the folded position. This makes the folding process of the arm 2 simple and easy to operate.

[0107] According to an embodiment of the present invention, the fuselage assembly 10 of the aircraft 100 is configured such that one end of each support arm 232 is rotatably connected to the fuselage 1. Each support arm 232 is provided with a locking assembly 233 at the end away from the fuselage 1. The support arm 232 engages with the corresponding arm 2 via the locking assembly 233. Each arm 2 has an extended position and a folded position. The locking assembly 233 has a locked state and an unlocked state. In the locked state, the locking assembly 233 locks the arm 2 in the extended position. In the unlocked state, the locking assembly 233 disengages from the arm 2, allowing the arm 2 to rotate to the folded position. This allows the arm 2 to be folded and easily operated. When the arm 2 is in the extended position, the support arm 232 supports the arm 2, ensuring that the arm 2 maintains a stable and reliable structure in the extended position.

[0108] like Figure 2 As shown, according to some embodiments of the present invention, a fuselage 1 includes a connecting beam 11 and a mounting frame 12. The connecting beam 11 is fixedly connected to the mounting frame 12, and one end of each arm 2 is rotatably connected to the connecting beam 11. As can be seen, the structure of the fuselage 1 is simple. It should be noted that the mounting frame 12 can be used to mount batteries 6 and liquid storage containers 5 of the aircraft 100. The arms 2 can be rotatably connected to the fuselage 1 by cooperating with the connecting beam 11.

[0109] like Figure 13-15As shown, according to some embodiments of the present invention, each arm 2 includes a pivot 21 and an arm rod 22, one end of the arm rod 22 is fixed to the pivot 21, and the pivot 21 is rotatably connected to the connecting beam 11. In the locked state, the locking assembly 233 cooperates with the connecting beam 11 and the pivot 21 to lock the arm 2 in the deployed position. As can be seen, each arm 2 can be rotatably connected to the connecting beam 11 through the pivot 21, and the support arm 232 can be locked in the deployed position by cooperating with the pivot 21 through the locking assembly 233. At the same time, when the locking assembly 233 is disengaged from the pivot 21 and the connecting beam 11, the arm 2 can be rotated relative to the fuselage 1, thereby folding the arm 2 to the folded position, which is convenient for storage and transportation of the aircraft 100.

[0110] like Figure 6 、 Figure 7 、 Figure 13 and Figure 15 As shown, in some embodiments of the present invention, a mating groove 115 is formed on the connecting beam 11, and two opposing side walls of the mating groove 115 are respectively provided with pivot holes 1126. The pivot holes 1126 on different side walls are opposite and coaxially arranged. A portion of the pivot member 21 is located within the mating groove 115, and the portion of the pivot member 21 located within the mating groove 115 is provided with a mating hole 2122. There are multiple mating holes 2122, which correspond one-to-one with the pivot holes 1126 on the connecting beam 11 and are coaxially arranged. Therefore, when mating the arm 2 with the connecting beam 11, it is necessary to extend a portion of the pivot member 21 into the mating groove 115 so that the multiple mating holes 2122 correspond one-to-one with the multiple pivot holes 1126 and are coaxially arranged. Then, the adapter shaft can be sequentially passed through the corresponding pivot holes 1126 and mating holes 2122, thereby achieving a pivotal connection between the pivot member 21 and the connecting beam 11, thereby achieving a pivotable connection between the arm 2 and the connecting beam 11. This ensures the reliability of the foldability of the machine arm 2.

[0111] like Figure 8 、 Figure 9 and Figure 14As shown, in some embodiments of the present invention, a first limiting groove 1131 is provided on the outer wall of the mating groove 115, which is recessed toward the mating groove 115. A second limiting groove 2113 is provided on the portion of the pivot member 21 not provided in the mating groove 115, which is recessed toward the mating groove 115. The second limiting groove 2113 communicates with the first limiting groove 1131 to form an annular groove. In the locked state, the locking assembly 233 is sleeved on the annular groove formed by the second limiting groove 2113 and the first limiting groove 1131 to lock the arm 2 in the deployed position. It can be seen that the provision of the first limiting groove 1131 and the second limiting groove 2113 can limit the locking assembly 233 in the axial direction of the arm 2, to a certain extent preventing the locking assembly 233 from sliding along the axial direction of the arm 2, thereby facilitating the operation of locking the arm 2 in the deployed position using the locking assembly 233. This improves the reliability of the locking assembly 233 in locking the arm 2.

[0112] like Figure 13 and Figures 17-20 As shown, in some embodiments of the present invention, the locking assembly 233 includes: a first locking accessory 2331, a second locking accessory 2332 and a locking piece 2333, the first locking accessory 2331 is pivotally connected to the corresponding support arm 232, the first end of the first locking accessory 2331 is pivotally connected to the first end of the second locking accessory 2332, and the second end of the first locking accessory 2331 is detachably connected to the second end of the second locking accessory 2332 through the locking piece 2333. In the locked state, the second end of the first locking accessory 2331 and the second end of the second locking accessory 2332 are connected through the locking piece 2333 to be sleeved on the first limiting groove 1131 and the second limiting groove 2113 to lock the arm 2 in the deployed position; in the unlocked state, the locking piece 2333 is disengaged from the first locking accessory 2331 so that the second end of the first locking accessory 2331 and the second end of the second lock accessory 2332 can be separated.

[0113] It can be seen that the structure of the locking assembly 233 is simple, and the switching of the locking assembly 233 between the locked state and the unlocked state is easy to operate. Figure 13 and Figure 17As shown, in the locked state, the second end of the first locking accessory 2331 and the second end of the second locking accessory 2332 are connected by the locking piece 2333 to form an annular structure and are arranged in the annular groove defined by the first limiting groove 1131 and the second limiting groove 2113, thereby locking the arm 2 in the expanded position. In the unlocked state, the locking member 2333 disengages from the first locking member 2331, thereby separating the second end of the first locking member 2331 from the second end of the second locking member 2332. As is known, the first end of the first locking member 2331 and the first end of the second locking member 2332 are pivotally connected. Thus, after the locking member 2333 disengages from the first locking member 2331, the second ends of the first locking member 2331 and the second ends of the second locking member 2332 can rotate away from each other, thereby gradually increasing the distance between the second end of the second locking member 2332 and the second end of the first locking member 2331. This allows the locking assembly 233 to disengage from the arm 2 and separate. This releases the restriction on the rotation of the arm 2 relative to the body 1, allowing the arm 2 to rotate to the folded position. This simplifies and facilitates the folding process of the arm 2.

[0114] like Figure 8 、 Figure 9 and Figure 19 As shown, in some embodiments of the present invention, a limiting protrusion 1132 is provided on one of the bottom wall of the first limiting groove 1131 and the inner side wall of the second locking member 2332, and a third limiting groove 23324 is provided on the other of the bottom wall of the first limiting groove 1131 and the inner side wall of the second locking member 2332. The limiting protrusion 1132 is adapted to extend into the third limiting groove 23324. Therefore, during the operation of locking the arm 2 in the deployed position using the locking assembly 233, the cooperation between the limiting protrusion 1132 and the third limiting groove 23324 can, to a certain extent, prevent the second locking member 2332 from rotating relative to the arm 2 and the body 1, thereby facilitating the operation of locking the arm 2 in the deployed position using the locking assembly 233. This improves the reliability of the locking assembly 233 in locking the arm 2.

[0115] like Figures 17-20As shown, in some embodiments of the present invention, two first locking parts 23314 are provided at a distance from each other on the second end of the first locking part 2331, two second locking parts 23323 are provided at a distance from each other on the second end of the second locking part 2332, a rotatable pivot rod 2334 is provided between the two second locking parts 23323, a locking hole 23341 is provided on the pivot rod 2334, a locking slot 23315 is provided on a side away from the second locking part 23323 of at least one of the two first locking parts 23314, and the locking part 2333 includes a locking body 23331, a locking wrench 23323, and a locking screw 23324. 332 and a locking connecting rod 23333, the locking connecting rod 23333 is arranged on the locking body 23331, the locking wrench 23332 is arranged on the locking body 23331 and is located on the side of the locking body 23331 away from the locking connecting rod 23333, and a locking protrusion 23334 is also provided on the side of the locking body 23331 on which the locking connecting rod 23333 is arranged, a part of the locking connecting rod 23333 passes through the space defined by the two first locking parts 23314 to extend into the locking hole 23341, and in the locked state, the locking protrusion 23334 is clamped in the locking slot 23315.

[0116] Thus, it can be seen that the locking assembly 233 has a reliable structure and can effectively lock the arm 2 in the deployed position in the locked state. The arrangement of the locking protrusion 23334 and the locking slot 23315 can further improve the reliability of the locking assembly 233, ensuring that the arm 2 can be reliably maintained in the deployed position during flight of the aircraft 100, thereby improving the reliability of the aircraft 100.

[0117] At the same time, it can be understood that since the pivot rod 2334 is rotatable, a part of the locking connecting rod 23333 passes through the space defined by the two first locking parts 23314 to extend into the locking hole 23341, and the two first locking parts 23314 are arranged at intervals, so that if the locking protrusion 23334 is disengaged from the locking slot 23315, the locking piece 2333 as a whole can be rotated around the central axis of the pivot rod 2334 through the locking connecting rod 23333, thereby causing the locking connecting rod 23333 to gradually disengage from the space between the two first locking parts 23314, thereby switching the locking assembly 233 from the locked state to the unlocked state. At this time, the locking assembly 233 is disengaged from the arm 2, and the arm 2 can rotate relative to the fuselage 1, and then the arm 2 can be rotated to the folded position. If the aircraft 100 needs to be used, the arm 2 can be rotated from the folded position to the unfolded position first, and then the locking assembly 233 can be put on the arm 2. Then the locking wrench 23332 can be moved so that the locking piece 2333 as a whole can be rotated around the central axis of the pivot rod 2334 toward the two first locking parts 23314 through the locking connecting rod 23333. When the locking piece 2333 is rotated until a part of the locking connecting rod 23333 is located between the two first locking parts 23314 and the locking protrusion 23334 is stuck in the locking slot 23315, the locking assembly 233 is switched to the locked state, and the arm 2 can be reliably locked in the unfolded position.

[0118] In some embodiments of the present invention, the locking connecting rod 23333 is axially movably disposed in the locking hole 23341. In the unlocked state, the locking connecting rod 23333 moves in a direction away from the locking hole 23341 to disengage the locking protrusion 23334 from the locking slot 23315. Therefore, it can be seen that when the locking assembly 233 is switched from the locked state to the unlocked state, a force can be applied to the locking wrench 23332 to move the locking connecting rod 23333 in a direction away from the locking hole 23341, so that the locking protrusion 23334 can be disengaged from the locking slot 23315, and then the locking piece 2333 as a whole can be rotated around the central axis of the pivot rod 2334 through the locking connecting rod 23333, so that the locking connecting rod 23333 gradually disengages from the space between the two first locking parts 23314, thereby switching the locking assembly 233 from the locked state to the unlocked state. At this time, the locking assembly 233 is disengaged from the arm 2, and the arm 2 can rotate relative to the fuselage 1, and then the arm 2 can be rotated to the folded position. When switching the locking assembly 233 from the unlocked state to the locked state, the arm 2 can be rotated from the folded position to the deployed position first, and then the locking assembly 233 can be put on the arm 2. Then the locking wrench 23332 can be moved so that the locking piece 2333 as a whole can be rotated around the central axis of the pivot rod 2334 toward the two first locking parts 23314 through the locking connecting rod 23333. When the locking piece 2333 is rotated until a part of the locking connecting rod 23333 is located between the two first locking parts 23314, the locking connecting rod 23333 can be moved toward the direction close to the locking hole 23341 so that the locking protrusion 23334 is locked in the locking slot 23315, and the arm 2 can be reliably locked in the deployed position.

[0119] like Figure 13 and Figure 16 As shown, according to some embodiments of the present invention, the support arm 232 is connected to the mounting frame 12 via a connector 231. The connector 231 includes a mounting base 2311 and an adapter 2312. The mounting base 2311 is fixedly connected to the mounting frame 12. The adapter 2312 is located on a side of the mounting base 2311 away from the mounting frame 12. The support arm 232 is provided with a pivot 2322, which is pivotally connected to the adapter 2312. It can be seen that the structure of the connector 231 is simple and reliable, and the rotatable connection between the support arm 232 and the mounting frame 12 is simple and reliable, making it easy to assemble and disassemble.

[0120] like Figure 1-Figure 33 As shown, an aircraft 100 according to an embodiment of the present invention includes a fuselage assembly 10 according to the above-mentioned embodiment of the present invention.

[0121] According to the aircraft 100 of the embodiment of the present invention, by providing the fuselage assembly 10 according to the above embodiment of the present invention, the arm 2 can be folded and the folding structure is reliable. The arm 2 is structurally stable and reliable when in the unfolded position.

[0122] Reference below Figure 1-Figure 33 An aircraft 100 according to a specific embodiment of the present invention will now be described. It should be understood that the following description is merely illustrative and intended to explain the present invention, and should not be construed as limiting the present invention. Specifically, aircraft 100 may be a drone, which can be used in the agricultural industry for operations such as spraying pesticides or watering crops. Of course, aircraft 100 can also be used in other fields, such as spraying fire extinguishing fluids during forest fires, aerial photography, power inspections, environmental monitoring, forest fire prevention, and disaster inspections.

[0123] refer to Figure 1-Figure 33 , the aircraft 100 according to an embodiment of the present invention 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, an arm 2 and a support arm 233. The landing gear 3 is fixed under the fuselage 1 to ensure the stability of the aircraft 100 during takeoff 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 flight of the aircraft 100. The liquid storage container 5 is mounted on the fuselage 1 for holding items to be sprayed or transported, the battery 6 is fixed on the fuselage 1, the power assembly 4 provides power for the aircraft 100, and the electronic control module 7 is fixed on the fuselage 1 for controlling the flight posture of the aircraft 100.

[0124] Reference Figures 1-9 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. Each second beam body 114 includes a pivot portion 112 and a mating portion 113 connected to each other.

[0125] Reference Figure 6 and Figure 7The 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 and lower end walls 1111 and 1112. The front end wall 1113 is generally formed into a structure with an arcuate cross-section. The upper, lower, and front end walls 1111 and 1112 collectively enclose a first mating groove 1110 with a rearward opening, giving the first beam body 111 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 mating groove 1110. The first connecting portion 1114 extends along the upper, lower, and front end walls 1113, respectively. A first connecting hole 11141 is defined in the first connecting portion 1114, which extends through the outer wall of the first beam body 111.

[0126] Preferably, a stop portion 1116 is further formed on the inner wall of the first mating groove 1110. The stop portion 1116 can extend horizontally and / or vertically 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. A 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 portion 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.

[0127] Furthermore, a connecting post 1117 is formed on the outer circumference of the upper end wall 1111. The connecting post 1117 is provided with a mating hole 11171 with its opening facing forward. A wire hole 1118 is also provided on the front end wall 1113.

[0128] Reference Figure 6-9The pivotal connection 112 includes two pivotal connections 112, each of which is also formed into a structure with a roughly "U"-shaped cross-section. Each pivotal connection 112 extends upward and rearward along the end surface of the first beam body 111, wherein the angle at which each pivotal connection 112 extends upward relative to the first beam body 111 is 10°-35°. Specifically, the angle at which each pivotal connection 112 extends upward relative to the first beam body 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 body 111, the angle between the central axis of the second beam body 114 and the orthographic 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. The angle at which each pivotal connection 112 extends rearward relative to the first beam body 111 is 5°-20°. Specifically, each pivotal portion 112 extends rearward at an angle of 9°, 12°, 14°, or 16° relative to the first beam 111. It should be noted that the angle between the horizontal projection of the central axis of the second beam 114 and the central axis of the first beam 111 is the angle at which the second beam 114 extends rearward relative to the first beam 111. A second mating slot 1120 is formed within the pivotal portion 112, opening rearward and communicating with the first mating slot 1110.

[0129] 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 connections between the upper pivoting wall 1121 and the upper end wall 1111, and 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 define a rearwardly facing second mating slot 1120. Coaxially disposed pivot holes 1126 are defined in each of the upper pivot wall 1121 and the lower pivot wall 1122. Antenna mounting bases 1124 extend perpendicularly from each of the upper pivot wall 1121 and the lower pivot wall 1122. Antenna mounting bases 1124 define a communication hole that communicates with the second mating slot 1120.

[0130] Further, if Figure 9As shown, a mating portion 113 extends from the end of the pivotal portion 112. Second reinforcing ribs 1133 are formed between the outer circumference of the mating portion 113 and the upper pivot wall 1121, lower pivot wall 1122, and front pivot wall 1123 of the pivotal portion 112. The mating portion 113 has an arc-shaped cross-section and includes a third mating groove 1130 with a rearward opening. The third mating groove 1130 is arc-shaped and communicates with the second mating groove 1120. A first limiting groove 1131 is also defined on the outer circumference of the mating portion 113, with a limiting protrusion 1132 formed on the bottom wall of the first limiting groove 1131.

[0131] Reference Figure 6-Figure 7 and Figure 10-12 , the mounting frame 12 is suitable for connecting 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 the 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. The second connecting portion 124 is suitable for connecting with the first connecting portion 1114 to fix the mounting frame 12 to the first beam body 111. During installation, when the end surface of the front end plate 121 abuts against the stop 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.

[0132] Reference Figure 3 、 Figure 10-12 The front end plate 121, the rear end plate 122 and the two side plates 123 together enclose 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 are 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 side surfaces of the first side plate portion 1231, the second side plate portion 1232 and the transition portion 1233.

[0133] Furthermore, the mounting frame 12 includes a separator 125, the ends of which are connected to the ends of the two second side panels 1232 near the transition portion 1233. The separator 125 divides the mounting cavity 120 into a first mounting cavity 1201 and a second mounting cavity 1202. The battery 6 can be installed in the first mounting cavity 1201, and the liquid storage container 5 can be installed in the second mounting cavity 1202.

[0134] Further, refer to Figure 12The first side plate portion 1231 is further provided with a positioning groove 1234 , and a second mounting 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 mounting protrusion 12311 . The second mounting protrusion 12311 is used to mount the landing gear 3 .

[0135] Preferably, the mounting frame 12 further includes a reinforcing plate 126, which is arranged parallel to the front end plate 121, and whose ends are connected to the first side plate portion 1231. The reinforcing plate 126 is adapted to cooperate 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.

[0136] Preferably, refer to Figure 3 and Figure 10 The inner walls of the two side panels 123 are further provided with a battery guide module 127 and a liquid storage container guide module 128. 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, dampen, and fix the battery 6 and the liquid storage container 5.

[0137] Reference Figure 1-Figure 5 and Figure 13-14 The two arms 2 are rotatably connected to the two pivoting portions 112 of the connecting beam 11 . Each arm 2 includes a pivoting member 21 and an arm rod 22 .

[0138] Reference Figure 14 and 15 The pivot member 21 includes a sleeve portion 211 and two pivot protrusions 212 extending from the sleeve portion 211. The sleeve portion 211 includes a first outer wall 2111 and a second outer wall 2112, which are coaxial. The first outer wall 2111 and the second outer wall 2112 of the sleeve portion 211 jointly define a sleeve hole 2110, which is suitable for mating with one end of the arm rod 22. A second retaining groove 2113 is also defined on the circumference 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-to-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.

[0139] One end of the arm rod 22 is fixedly secured to the sleeve hole 2110, and the other end of the arm rod 22 is used to secure 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.

[0140] Reference Figure 13 and Figure 16 The connecting member 231 includes a mounting base 2311 and a transition portion 2312 extending perpendicularly to the mounting base 2311. The connecting member 231 is fixed to the transition portion 1233 via the mounting base 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 connecting member 231 via the pivot member 2322. The other end of the support arm 232 is pivotally connected to the locking assembly 233 via the pivot member 2322.

[0141] Reference Figures 17-20 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 member 2331 includes a first circular portion 23311, two first pivoting protrusions 23312 extending outwardly from the outer circumference of the first circular portion 23311, a pivot block 23313, and a first locking portion 23314. The two first pivoting protrusions 23312 are pivotally connected to the end of the support arm 232 away from the connecting member 231 via a pivot member 2322. A locking slot 23315 is formed on the side wall of the first locking portion 23314.

[0143] Reference Figure 17-Figure 19 The second locking member 2332 includes a second circular portion 23321, two second pivoting protrusions 23322 extending outwardly from the outer circumference of the second circular portion 23321, and a second locking portion 23323. A third retaining groove 23324 is also defined on the inner circumference of the second circular portion 23321. The two second pivoting protrusions 23322 are pivotally connected to the pivot block 23313, allowing the first circular portion 23311 and the second circular portion 23321 to be located on the same circumference.

[0144] Reference Figure 17 and Figure 20 The locking member 2333 is connected to the second locking portion 23323 via a pivot rod 2334. The locking member 2333 includes a locking body 23331, a locking wrench 23332 extending outwardly from a first end surface of the locking body 23331, and a locking connecting rod 23333 (which can be a separate component) extending from a second end surface of the locking body 23331. Furthermore, a locking protrusion 23334 is formed on the second end surface.

[0145] The following describes the deployment process of the arm 2 in detail:

[0146] First, rotate the arm 2 to fit the first outer wall 2111 of the pivot member 21 into the third fitting groove 1130 of the fitting portion 113. This ensures that the fitting portion 113 and the second outer wall 2112 are located on the same circumference, forming a complete cylindrical tube. At the same time, the first retaining groove 1131 on the retaining portion 113 and the second retaining groove 2113 on the circumference of the second outer wall 2112 together form a complete annular groove.

[0147] Next, the support arm 232 is rotated to engage the first annular portion 23311 of the first locking member 2331 and the second annular portion 23321 of the second locking member 2332 with 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 engages with the third limiting groove 23324 on the inner circumference of the second annular portion 23321, preventing the second annular portion 23321 from rotating relative to the bottom wall of the first limiting groove 1131.

[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 collar coaxially arranged with the cylindrical tube formed by the mating 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 mating portion 113 of the pivot member 21. The locking protrusion 23334 on the second end surface of the locking member 2333 and the locking groove 23315 on the side wall of the first locking portion 23312 cooperate to squeeze the first annular portion 23311 and the second annular portion 23321 against the outer circumference 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, and will not be described here.

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

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

[0152] Reference Figure 12 and 21 -23, the supporting section 3113 of the tripod supporting leg 31 is engaged with the positioning groove 1234 and connected to the second mounting protrusion 12311 via 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 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] 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 extension 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 into the fitting hole 4110.

[0157] Mounting assembly 42 includes a mounting post 421, a bearing 422, a connecting sleeve 423, a fixed support 424, and a rotating member 425. The mounting post 421 is rotatably fixed to the extension 412 at both ends via the bearings 422. The connecting sleeve 423 and the fixed support 424 are interconnected and fixed to the mounting post 421. The rotating member 425 is connected to the mounting post 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 Figure 31 and Figure 32The drive device 44 includes a steering gear 441, a transmission device, a transmission shaft 442, and a connecting rod assembly 443. 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] Reference Figure 26 and Figure 27 The liquid storage container 5 includes a container body 51 having a liquid storage cavity 50 for containing 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. 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 Figure 26 The 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 bracket 13. The mounting bracket 13 is connected to the first beam 111. The communication module 71 and the flight control module 72 are mounted on the mounting bracket 13. The connecting wires between the electronic control module 7 and the power assembly 4 can pass through the wire hole 1118, enter the first mating slot 1110, and then pass through the second mating slot 1120 and the arm rod 22.

[0163] Preferably, the fuselage 1 further includes a protective frame 14, which is disposed outside the mounting frame 13 and includes two protective rods 141, one end of each of which is fixed to the mating hole 11171 of the connecting column 1117. The other end of each of the protective rods 141 is fixed to the lower end wall 1112 via 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 structures and operations of the aircraft 100 according to the embodiment of the present invention are well known to those skilled in the art and will not be described in detail here.

[0166] Throughout this specification, reference to terms such as "one embodiment," "some embodiments," "illustrative embodiments," "examples," "specific examples," or "some examples" means that a specific feature, structure, material, or characteristic described in conjunction with that embodiment or example is included in at least one embodiment or example of the present invention. In this specification, illustrative uses of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.

[0167] While 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 invention, and that the scope of the invention is defined by the claims and their equivalents.

Claims

1. An aircraft fuselage assembly, characterized in that: include: body; a plurality of arms, the plurality of arms being distributed along the circumference of the fuselage, and one end of each arm being rotatably connected to the fuselage; a plurality of support arms, the number of the support arms being the same as the number of the aircraft arms and corresponding one to one, each support arm being adjacent to a corresponding aircraft arm, one end of each support arm being rotatably connected to the aircraft body, and each support arm being provided with a locking assembly at one end away from the aircraft body, wherein the support arm engages with the corresponding aircraft arm via the locking assembly; Each of the arms has an extended position and a folded position, and the locking assembly has a locked state and an unlocked state. In the locked state, the locking assembly locks the arm in the extended position, and in the unlocked state, the locking assembly is disengaged from the arm, and the arm can be rotated to the folded position. The fuselage includes a connecting beam and a mounting frame, wherein the connecting beam is fixedly connected to the mounting frame, and one end of each of the arms is rotatably connected to the connecting beam. Each of the arms includes a pivot member and an arm rod, one end of the arm rod is fixed to the pivot member, the pivot member is rotatably connected to the connecting beam, and in the locked state, the locking assembly cooperates with the connecting beam and the pivot member respectively to lock the arm in the deployed position. A mating groove is formed on the connecting beam, and pivot holes are respectively provided on two opposite side walls of the mating groove. The pivot holes on different side walls are opposite and coaxially arranged. A portion of the pivot member is located in the mating groove, and a mating hole is provided on the portion of the pivot member located in the mating groove. There are multiple mating holes and they correspond one-to-one to the pivot holes on the connecting beam and are coaxially arranged.

2. The fuselage assembly of an aircraft according to claim 1, wherein: A first limiting groove is provided on the outer side wall of the mating groove and is recessed toward the mating groove. A second limiting groove is provided on the portion of the pivot member that is not provided with the mating groove and is recessed toward the mating groove. The second limiting groove is connected to the first limiting groove to form an annular groove. In the locked state, the locking assembly is sleeved on the annular groove formed by the second limiting groove and the first limiting groove to lock the machine arm in the extended position.

3. The fuselage assembly of an aircraft according to claim 2, wherein: The locking assembly includes: a first lock component, a second lock component and a locking piece, wherein the first lock component is pivotally connected to the corresponding support arm, the first end of the first lock component is pivotally connected to the first end of the second lock component, and the second end of the first lock component is detachably connected to the second end of the second lock component via the locking piece. In the locked state, the second end of the first lock accessory and the second end of the second lock accessory are connected by the locking piece to be sleeved on the first limiting groove and the second limiting groove to lock the arm in the deployed position; in the unlocked state, the locking piece is disengaged from the first lock accessory so that the second end of the first lock accessory and the second end of the second lock accessory can be separated.

4. The fuselage assembly of an aircraft according to claim 3, wherein: A limiting protrusion is provided on one of the bottom wall of the first limiting groove and the inner side wall of the second lock accessory, and a third limiting groove is provided on the other of the bottom wall of the first limiting groove and the inner side wall of the second lock accessory, and the limiting protrusion is suitable for extending into the third limiting groove.

5. The fuselage assembly of an aircraft according to claim 3, wherein: The second end of the first lock component is provided with two first locking parts spaced apart from each other, the second end of the second lock component is provided with two second locking parts spaced apart from each other, a rotatable pivot rod is provided between the two second locking parts, the pivot rod is provided with a locking hole, and at least one of the two first locking parts is provided with a locking slot on a side away from the second locking part. The locking piece includes a locking body, a locking wrench and a locking connecting rod. The locking connecting rod is arranged on the locking body. The locking wrench is arranged on the locking body and is located on the side of the locking body away from the locking connecting rod. A locking protrusion is also provided on the side of the locking body where the locking connecting rod is arranged. A part of the locking connecting rod passes through the space defined by the two first locking parts to extend into the locking hole. In the locked state, the locking protrusion is clamped in the locking slot.

6. The fuselage assembly of an aircraft according to claim 5, characterized in that The locking connecting rod is movably arranged in the locking hole along the axial direction. In the unlocked state, the locking connecting rod moves in a direction away from the locking hole to enable the locking protrusion to disengage from the locking slot.

7. The fuselage assembly of an aircraft according to any one of claims 2 to 6, characterized in that: The support arm is connected to the mounting frame through a connecting piece, and the connecting piece includes a mounting base and a transition portion. The mounting base is fixedly connected to the mounting frame, and the transition portion is provided on a side of the mounting base away from the mounting frame. A pivot piece is provided on the support arm, and the pivot piece is pivotally connected to the transition portion.

8. An aircraft, characterized in that: The invention comprises a fuselage assembly according to any one of claims 1 to 7.

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