Aircraft

Abstract

The present invention discloses an aircraft, comprising a fuselage and a fixing device. The fixing device includes: a mounting frame for connecting to the fuselage. The mounting frame has a mounting space extending in a direction from the front end to the rear end of the fuselage. The mounting space is located at the rear end of the fuselage or behind the fuselage, and the mounting space is used for mounting at least one of a battery and a storage box. According to the aircraft of the embodiment of the present invention, the above design enables the center of gravity of the aircraft to be close to the plane where the lift force of the aircraft is located in the vertical direction, thereby facilitating the flight of the aircraft. At the same time, such a design also facilitates taking out or loading items from the mounting space of the fixing device.

Description

[0001] This application is a divisional application of the invention patent application with the application date of August 12, 2016, the earliest priority date of April 7, 2016, the invention title of "Aircraft", and the application number of 201610663394.8. Technical Field

[0002] The present invention relates to the technical field of aircraft, and in particular to an aircraft. Background Art

[0003] In the materials disclosed in the related art, when installing the battery and the storage box (such as a medicine box) on the aircraft, usually the battery is arranged in the fuselage and the storage box is arranged under the fuselage. Such a structure results in the center of gravity of the entire aircraft being too low relative to the rotation plane of the propeller, which is not conducive to the flight of the aircraft. Summary of the Invention

[0004] The present invention aims to at least solve one of the technical problems in the related art to some extent. For this reason, the object of the present invention is to provide an aircraft that is convenient to fly.

[0005] The aircraft according to the present invention includes a fuselage and a fixing device. The fixing device includes: a mounting frame for connecting to the fuselage and a fixing frame connected to the rear end of the fuselage. The mounting frame is connected to the fixing frame. The mounting frame has a mounting space extending in the direction from the front end to the rear end of the fuselage. The mounting space is located at the rear end of the fuselage or behind the fuselage. The mounting space is used for mounting at least one of a battery and a storage box;

[0006] The fixing frame includes two opposite extension plates for connecting to the fuselage;

[0007] The aircraft further includes a clamping mechanism. The clamping mechanism includes a clamping member for clamping the arm of the aircraft. The clamping member is used for connecting to the fuselage. The clamping member has a side surface for connecting to the corresponding extension plate.

[0008] For the aircraft according to the embodiments of the present invention, by horizontally suspending the mounting space of the fixing device outside the fuselage, the center of gravity of the aircraft is close to the plane where the lift of the aircraft is located in the vertical direction, so as to facilitate the flight of the aircraft. At the same time, such a design also facilitates taking out or loading items from the mounting space of the fixing device. Using such a clamping mechanism to clamp the arm on the fuselage, the assembly process of the arm is simple and easy to operate.

[0009] In some embodiments, the clamping mechanism further includes a fixing member and a cooperating member. The fuselage includes a bottom plate. The mounting frame includes two opposite side plates;

[0010] The fixing member is fixed to the bottom plate, and the fixing member is connected to the side plate of the mounting bracket;

[0011] The arm is mounted between the fixing member and the mating member.

[0012] In some embodiments, the fixing member includes a base portion and a clamping portion extending from one side of the base portion;

[0013] One side of the clamping portion away from the base portion is recessed inward to form a first clamping surface, and two through holes are provided at both ends of the clamping portion adjacent to the first clamping surface;

[0014] One side of the mating member is recessed inward to form a second clamping surface, and two fixing holes are provided at both ends of the mating member adjacent to the second clamping surface;

[0015] The fastener passes through the through hole of the clamping portion of the fixing member and is connected to the fixing hole of the mating member.

[0016] In some embodiments, the clamping mechanism further includes a pressing block;

[0017] The pressing block includes a locking portion and two connecting portions located on both sides of the locking portion, and a through hole is provided on each connecting portion;

[0018] The clamping member is provided with a mounting groove and a through hole communicating with the mounting groove. Two convex platforms extend from the inner surface of the clamping member toward the center of the through hole at the connection of the mounting groove and the through hole, and a fixing hole is provided on each convex platform;

[0019] The arm passes through the clamping member, the pressing block is fitted in the mounting groove of the corresponding clamping member, and the fastener passes through the through holes of the two connecting portions of the pressing block and is connected to the fixing holes of the two convex platforms of the clamping member.

[0020] In some embodiments, the clamping mechanism further includes a collar. The collar includes a second collar, and the fuselage includes a bottom plate;

[0021] The second collar is sleeved on the arm, and a stop block extends outward from one end of the second collar;

[0022] The arm passes through the clamping member until the stop block of the second collar abuts against the surface of the clamping member far from the center of the bottom plate.

[0023] In some embodiments, the fuselage includes a bottom plate. The bottom plate is provided with a positioning hole and a through hole; the clamping member has a bottom surface, and a positioning convex column and a fixing hole are provided on the bottom surface;

[0024] The bottom surface of the clamping member is in contact with the upper surface of the bottom plate. The clamping member is positioned on the positioning holes on the bottom plate through the positioning convex posts. Fasteners pass through the corresponding through holes on the bottom plate and are connected to the fixing holes on the bottom surface of the corresponding clamping member.

[0025] In some embodiments, the installation space includes a first installation space and a second installation space adjacent to the first installation space. The first installation space is away from the fixing frame, and the second installation space is adjacent to the fixing frame. The first installation space is for installing the battery, and the second installation space is for installing the packing box.

[0026] In some embodiments, the mounting frame includes opposite side plates and end plates connected between the two side plates. One end of each side plate away from the end plate is connected to the corresponding extension plate. The first installation space is adjacent to the end plate, and the second installation space is away from the end plate.

[0027] In some embodiments, the two extension plates are arranged in a V shape.

[0028] In some embodiments, the fixing frame further includes a base plate for connecting to the fuselage. The two extension plates extend from opposite sides of the base plate. The base plate is provided with through holes for the liquid pipes connected to the packing box to pass through.

[0029] In some embodiments, the fixing device further includes a partition beam for connecting between the two side plates. The first installation space and the second installation space are respectively located on both sides of the partition beam.

[0030] In some embodiments, the aircraft further includes the battery. The battery includes opposite first sides and a bottom connecting the bottoms of the two first sides. Each first side is respectively provided with a guiding groove penetrating through the bottom of the battery. Inside each side plate, a guiding block is provided near the first installation space. Each guiding block is pivotally installed with a first guiding slide column along a direction parallel to the side plate. The first guiding slide column is used for slidably abutting against the guiding groove.

[0031] In some embodiments, one side of the guiding block facing away from the side plate has an inclined guiding surface.

[0032] In some embodiments, a convex block is provided in the guiding groove of the battery. A slotted hole is provided on the guiding surface. An elastic support block for abutting against the convex block of the battery is provided at the bottom of the slotted hole.

[0033] In some embodiments, the first guiding slide column is a rubber column.

[0034] In some embodiments, the battery further includes a top connected to the tops of the two first sides. A battery interface is provided on the top of the battery. A battery socket is mounted on the end plate, and a connection terminal for electrically connecting to the battery interface is provided on the top of the battery socket.

[0035] In some embodiments, the aircraft further includes the storage box, which includes an upper box body and a lower box body vertically connected to the bottom of the upper box body. The upper box body includes two opposite second sides. Each second side of the upper box body is provided with a side bump. A guide slider is provided on the inner side of each side plate adjacent to the second installation space. A second guide sliding column is pivotally mounted on the side of the guide slider facing away from the side plate in a direction parallel to the side plate. The second guide sliding column is used for slidably abutting against the side bump of the storage box.

[0036] In some embodiments, each second side of the upper box body is provided with a clamping groove. The fixing device includes a clamping block for being arranged on the fuselage and a limiting member. The clamping block is used for abutting against the clamping groove of the storage box, and the limiting member is used for abutting against the side of the lower box body of the storage box facing the upper box body.

[0037] In some embodiments, the lower box body further includes a rear wall connected to the rear ends of the two second sides. A rear bump is provided on the rear wall of the lower box body. The partition beam is used for abutting against the rear bump of the lower box body.

[0038] The aircraft according to the present invention includes: a fuselage; the fixing device according to the present invention; a battery; and a storage box.

[0039] The additional aspects and advantages of the present invention will be partly given in the following description, partly will become obvious from the following description, or will be understood through the practice of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0040] The above and / or additional aspects and advantages of the present invention will become obvious and easy to understand from the description of the embodiments in conjunction with the following drawings, in which:

[0041] Figure 1 is a three-dimensional assembly view of an aircraft according to an embodiment of the present invention;

[0042] Figure 2 is Figure 1 a top view of the aircraft (excluding the battery, the storage box and the top plate of the fuselage) in

[0043] Figure 3 is Figure 2 an enlarged view of the assembled state of the arm and the clamping member at the second collar in

[0044] Figure 4 is Figure 2The three-dimensional assembly drawing of the robotic arm and the collar in;

[0045] Figure 5 is Figure 4 The three-dimensional view of the first collar in;

[0046] Figure 6 is Figure 5 The side view of the first collar of;

[0047] Figure 7 is Figure 4 The three-dimensional view of the second collar in;

[0048] Figure 8 is Figure 2 The side view of the clamping member in;

[0049] Figure 9 is Figure 8 The three-dimensional view of the clamping member of;

[0050] Figure 10 is Figure 2 The three-dimensional view of the pressing block in;

[0051] Figure 11 The side view of the clamping member according to another embodiment of the present invention;

[0052] Figure 12 is Figure 2 The three-dimensional view of the fixing member in;

[0053] Figure 13 is Figure 2 The three-dimensional view of the mating member in;

[0054] Figure 14 is according to Figure 1 The three-dimensional assembly drawing of the aircraft (removing the shipping container, robotic arm, power device and battery) in;

[0055] Figure 15 is according to Figure 1 The three-dimensional assembly drawing of the aircraft (removing the shipping container and battery) in;

[0056] Figure 16 is Figure 14 The bottom view of the aircraft (removing the shipping container, robotic arm, power device and battery) in;

[0057] Figure 17 is Figure 14 The three-dimensional view of the fixing device in;

[0058] Figure 18 is Figure 14 The three-dimensional view of the box limiting member in;

[0059] Figure 19 isFigure 17 Stereogram of the battery socket in

[0060] Figure 20 is Figure 17 Stereogram of the guiding block in

[0061] Figure 21 is Figure 17 Side view of the guiding block in

[0062] Figure 22 is Figure 15 Stereogram of the clamping block in

[0063] Figure 23 is according to Figure 17 Stereogram of the guiding slider in

[0064] Figure 24 is Figure 1 Stereogram of the battery in

[0065] Figure 25 Side view of the battery and the fixing device in the assembled state according to an embodiment of the present invention;

[0066] Figure 26 is Figure 25 Cross-sectional view along the A-A direction in

[0067] Figure 27 is according to Figure 1 Stereogram of the storage box in

[0068] Figure 28 is according to Figure 1 Stereogram of the landing gear in

[0069] Reference numerals:

[0070] Aircraft 100,

[0071] Fixing holes 1011, fixing holes 1012, fixing holes 1013, fixing holes 1014, fixing holes 1015, fixing holes 1016, fixing holes 1017,

[0072] Perforations 1021, perforations 1023, perforations 1024, perforations 1025, perforations 1026,

[0073] Fasteners 1031, fasteners 1032, fasteners 1033, fasteners 1034, fasteners 1035, fasteners 1036, fasteners 1037, fasteners 1038, positioning hole 104,

[0074] Fuselage 1, bottom plate 11, top plate 12, connecting frame 14, first frame 141, second frame 142, through hole 17, liquid nozzle 18, arm 2, rod body 21,

[0075] Clamping mechanism 3, arc segment 301, flat segment 302, transition segment 303, clamping member 31, first surface 311, second surface 312, side surface 313, top surface 314, bottom surface 315, through hole 316, mounting groove 317, positioning boss 318, boss 319, pressing block 32, locking portion 321, connecting portion 322, abutting surface 323, fixing member 33, base portion 331, clamping portion 332, first clamping surface 333, mating member 34, second clamping surface 341, collar 39, arc segment 3901, flat segment 3902, transition segment 3903, glue receiving groove 3904, first collar 391, second collar 392, stopping block 3921

[0076] Landing gear 6, support leg 60, front support leg 601, rear support leg 602, bottom support leg 603, horizontal connecting portion 611, vertical connecting portion 612

[0077] Battery 7, first side 703, bottom 702, top 701, rear side 704, battery connector 71, guiding groove 72, bump 73, handle 74, buckling member 75, connecting plate 751, pivot 752, buckling portion 753, pressing plate 7531, buckling plate 7532, hook 7533

[0078] Containment box 8, upper box body 81, second side 811, side bump 8111, positioning groove 8112, bottom wall 812, top wall 813, rear wall 814, rear bump 8141, lower box body 82, liquid nozzle 84, handle 86, ventilation opening 87

[0079] Fixing device 9, installation space 900, first installation space 901, second installation space 902, fixing frame 91, extension plate 911, base plate 912, through hole 9121, mounting frame 92, side plate 921, end plate 922, partition beam 93, guiding block 94, first guiding slide post 941, guiding surface 942, slotted opening 943, elastic support block 944, roller mounting groove 945, through slot 946, guiding slide block 95, second guiding slide post 951, battery socket 96, connecting terminal 961, clamping shaft 962, clamping block 97, elastic strengthening hole 971, box body limiting member 98, limiting portion 981, connecting portion 982, strengthening rib 983 Detailed implementation manners

[0080] The embodiments of the present invention will be described in detail below. Examples of the embodiments are shown in the drawings, wherein 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 intended to explain the present invention and should not be construed as a limitation to the present invention.

[0081] Refer below to Figures 1 - 28Describe an aircraft 100 according to an embodiment of the present invention. The aircraft 100 includes a fuselage 1 and a fixing device 9. The fixing device 9 is used to fix at least one of the battery 7 and the storage box 8 of the aircraft 100. The storage box 8 is adapted to contain items to be sprayed or transported.

[0082] As Figure 14 , Figure 15 and Figure 17 shown, the fixing device 9 includes a mounting bracket 92 for connecting to the fuselage 1. The mounting bracket 92 has a mounting space 900 extending in the direction from the front end to the rear end of the fuselage 1. The mounting space 900 is located at the rear end or behind the fuselage 1, and the mounting space 900 is used to mount at least one of the battery 7 and the storage box 8.

[0083] By horizontally suspending the mounting space 900 of the fixing device 9 outside the fuselage 1, the center of gravity of the aircraft 100 is close to the plane where the lift of the aircraft 100 is located in the vertical direction, which is beneficial to the flight of the aircraft 100. At the same time, such a design also facilitates the removal or loading of items from the mounting space 900 of the fixing device 9.

[0084] For easy understanding, the aircraft 100 according to the embodiment of the present invention will be described below in conjunction with Figures 1 - 28 description.

[0085] As Figure 1 and Figure 2 shown, the aircraft 100 includes a fuselage 1, landing gears 6, arms 2, a clamping mechanism 3, a power device, and a fixing device 9. As Figure 1 , Figures 24 - 27 shown, the aircraft 100 further includes a battery 7 and a storage box 8. The storage box 8 is adapted to contain items to be sprayed or transported. In this embodiment, the aircraft 100 is a quadrotor aircraft, and the number of both the arms 2 and the power device is four.

[0086] Please refer to Figure 1 , Figure 14 and Figure 15 , the fuselage 1 includes a bottom plate 11 and a top plate 12 oppositely arranged in the up-down direction, and a connecting frame 14 connected to the bottom plate 11. As Figure 16 shown, positioning holes 104 and through holes 1021 are provided on the bottom plate 11.

[0087] As Figure 14 and 15 shown, a through hole 17 is further provided near one side of the bottom plate 11, and a liquid nozzle 18 is provided at the through hole 17. Through holes are provided on the top plate 12.

[0088] Please refer toFigure 14 , the connecting frame 14 includes a first frame 141 and a second frame 142 vertically connected to the first frame 141. The second frame 142 is connected to the bottom of the first frame 141 through a fastener 1032 (such as Figure 16 shown), such as a screw, to the bottom plate 11 of the fuselage 1, and fixing holes 1017 are provided at the top of the second frame 142 and the first frame 141.

[0089] such as Figure 14 and Figure 17 shown, the fixing device 9 is connected to the connecting frame 14. As Figures 17 - 23 shown, the fixing device 9 includes: a fixing frame 91 connected to the connecting frame 14, a mounting frame 92 connected to the fixing frame 91, and a partition beam 93 connected to the mounting frame 92. As Figure 15 shown, the fixing device 9 further includes a clamping block 97 and a box body limiting member 98. The fixing frame 91 and the mounting frame 92 can be integrally formed.

[0090] The fixing frame 91 includes a base plate 912 and two extension plates 911 obliquely extending from opposite sides of the base plate 912. The base plate 912 is fixed to one end of the first frame 141 away from the second frame 142 through a fastener, such as a screw. A through hole 9121 is provided on the base plate 912. The two extension plates 911 are arranged in a V shape, and a through hole 1023 is provided on each extension plate 911.

[0091] The mounting frame 92 includes opposite side plates 921 and end plates 922 connecting the two side plates 921. One end of each side plate 921 away from the end plate 922 is connected to the corresponding extension plate 911. A through hole 1024 is provided on the side plate 921. The mounting frame 92 has a mounting space 900, and the partition beam 93 is connected between the two side plates 921 to divide the mounting space 900 into a first mounting space 901 and a second mounting space 902.

[0092] Please refer to Figure 17 and Figures 20 - 23, on the inner side of each side plate 921, a guiding block 94 is provided adjacent to the first installation space 901. On the top of the side of the guiding block 94 facing away from the side plate 921, there is a guiding surface 942. The guiding surface 942 is inclined such that the thickness of the guiding block 94 increases in the direction from the top to the bottom. A slotted groove 943 is provided on the guiding surface 942, and an elastic support block 944 is provided at the bottom of the slotted groove 943. In the middle and at the bottom of the side of the guiding block 94 facing away from the side plate 921, a roller installation groove 945 and a through groove 946 adjacent to the roller installation groove 945 are provided along the direction parallel to the side plate 921. The roller installation groove 945 is used for pivotally installing a first guiding slide column 941. The two through grooves 946 are used for allowing the first guiding slide column 941 to rotate. The material of the first guiding slide column 941 is a material with damping characteristics such as rubber.

[0093] On the inner side of each side plate 921, a guiding slider 95 is provided adjacent to the second installation space 902. At the top and bottom of the side of the guiding slider 95 facing away from the side plate 921, two second guiding slide columns 951 are pivotally installed along the direction parallel to the side plate 921.

[0094] On the inner side of the end plate 922, a battery socket 96 is provided. At the top of the battery socket 96, a connection terminal 961 is provided. Around the connection terminal 961 of the battery socket 96, a clamping shaft 962 is pivotally provided. The clamping shaft 962 is parallel to and adjacent to the end plate 922.

[0095] As Figure 15 and Figure 22 shown, the clamping block 97 is provided on the top plate 12, and an elastic strengthening hole 971 is provided on the clamping block 97.

[0096] As Figure 15 and Figure 18 shown, the box body limiting member 98 is provided on the bottom plate 11. The box body limiting member 98 includes a limiting portion 981, a connecting portion 982 extending from the middle of the limiting portion 981, and a reinforcing rib 983 connecting the lower part on one side of the limiting portion 981 and the connecting portion 982. The connecting portion 982 is connected to the lower surface of the bottom plate 11 by a fastener 1033 such as a screw.

[0097] As Figures 24 - 26As shown, the battery 7 is generally rectangular parallelepiped-shaped. The battery 7 includes two opposite first sides 703, a bottom 702 connected to the bottoms of the two first sides 703, a top 701 connected to the tops of the two first sides 703, and a rear side 704 connected to the rears of the two first sides 703. At the top of the rear side 704 of the battery 7, there are a buckle member 75 and a battery interface 71 adjacent to the buckle member 75. The buckle member 75 includes two oppositely arranged connecting plates 751, a pivot 752 connected between the two connecting plates 751, and a buckle portion 753 pivotally connected to the pivot 752 at the middle. The buckle portion 753 includes pressing plates 7531 and buckle plates 7532 located on both sides of the pivot 752. The buckle plates 7532 are bent and connected to the pressing plates 7531. The buckle plates 7532 have hooks 7533. On the two first sides 703 of the battery 7, there are respectively two guiding grooves 72 penetrating the bottom of the battery 7. A convex block 73 is provided downward on the top wall of each guiding groove 72. A handle 74 is provided on the top of the battery 7.

[0098] As Figure 27 shown, the storage box 8 includes an upper box body 81 and a lower box body 82 connected to the bottom of the upper box body 81 substantially vertically. The lower box body 82 and the upper box body 81 are generally rectangular parallelepiped-shaped. The upper box body 81 includes two opposite second sides 811, a bottom wall 812 connected to the bottoms of the two second sides, a top wall 813 connected to the tops of the two second sides, and a rear wall 814 connected to the rears of the two second sides. A liquid nozzle 84 is provided on the bottom wall 812 of the upper box body 81 adjacent to the lower box body 82. On each second side 811 of the upper box body 81, there are a side convex block 8111 and a clamping groove 8112. A rear convex block 8141 is provided on the rear wall 814 of the upper box body 81. A handle 86 and a ventilation opening 87 are provided on the top wall 812 of the upper box body 81.

[0099] As Figure 16 and Figure 28 shown, the landing gear 6 includes two support legs 60. Each support leg 60 includes a bottom support leg 603 and a front support leg 601 and a rear support leg 602 extending from both sides of the bottom support leg 603. At one end of the front support leg 601 away from the bottom support leg 603, there is a horizontal connecting portion 611. As Figure 16 shown, the horizontal connecting portion 611 is connected to the bottom plate 11 of the fuselage 1 through a fastener 1034 (such as a screw). At one end of the rear support leg 602 away from the bottom support leg 603, there is a vertical connecting portion 612. As Figure 15 shown, the vertical connecting portion 612 is connected to the end plate 922 and the corresponding side plate 921 of the fixing device 9 through a fastener 1035 (such as a screw).

[0100] As shown Figure 2 in the figure, the arm 2 is cylindrical, and a corresponding power device is installed at one end thereof. The power device can provide power for the aircraft 100.

[0101] Please refer to Figure 2 and Figures 8 - 13 . The clamping mechanism 3 includes two first clamping mechanisms and two second clamping mechanisms. Each first clamping mechanism includes two clamping members 31, two pressing blocks 32, a fixing member 33, a mating member 34, and a collar 39. Each second clamping mechanism includes two clamping members 31, two pressing blocks 32, and a collar 39.

[0102] As shown Figure 8 in Figure 9 the figure, each clamping member 31 has opposite first surface 311 and second surface 312, a top surface 314 connected between the top of the first surface 311 and the top of the second surface 312, a bottom surface 315 connected between the bottom of the first surface 311 and the bottom of the second surface 312, and two side surfaces 313 connected between the two ends of the first surface 311 and the two ends of the second surface 312 and connected to the top surface 314 and the bottom surface 315. A through hole 316 penetrating the first surface 311 and the second surface 312 is provided on the clamping member 31. A plurality of grooves are provided around the through hole 316 on the first surface 311 and the first surface 312 to reduce the mass of the clamping member 31. The inner circumferential surface of the through hole 316 includes two arc segments 301 arranged oppositely, two plane segments 302 located between the two arc segments 301 and arranged relatively and parallelly, and two transition segments 303 located between the two arc segments 301 and the two plane segments 302 and arranged oppositely. Wherein, each plane segment 302 is perpendicular to the bottom surface 315 of the clamping member 31, and each transition segment 303 can be composed of a plurality of small planes, or the transition segment 303 can be composed of an arc surface. An installation groove 317 penetrating the top surface 314 and the arc segment 301 adjacent to the top surface 314 is further provided on the clamping member 32, and the installation groove 317 communicates with the through hole 316. Two fixing holes 1011 are provided at both ends of the top surface 314 adjacent to the installation groove 317. Two bosses 319 extending towards the center of the through hole 316 are provided on the inner surface of the clamping member 31 adjacent to the connection of the installation groove 317 and the through hole 316, and a fixing hole is provided on each boss 319. Two positioning convex columns 318 and two fixing holes facing away from the top surface 314 are provided on the bottom surface 315. A fixing hole 1012 is provided on one of the two side surfaces 313.

[0103] Each pressing block 32 includes a locking portion 321 and two connecting portions 322 located on both sides of the locking portion 321. A middle portion of the locking portion 321 is recessed to form a resisting surface 323. Each connecting portion 322 is provided with a perforation 1025.

[0104] The fixing member 33 includes a base portion 331 and a clamping portion 332 extending from one side of the base portion 331. A fixing hole 1013, a fixing hole 1014, and a fixing hole 1015 are respectively provided at the top, bottom, and the side of the base portion 331 away from the clamping portion 332. One side of the clamping portion 332 away from the base portion 331 is recessed inward to form a first clamping surface 333. Two perforations 1026 are provided at two ends of the clamping portion 332 adjacent to the first clamping surface 333.

[0105] One side of the fitting member 34 is recessed inward to form a second clamping surface 341. Two fixing holes 1016 are provided at two ends of the fitting member 34 adjacent to the second clamping surface 341.

[0106] Please refer to Figures 4 - 7 , each collar 39 includes a first collar 391 and a second collar 392.

[0107] The outer surface of the first collar 391 includes two relatively arranged arc segments 3901, two plane segments 3902 that are relatively and parallelly arranged between the two arc segments 3901, and two transition segments 3903 that are relatively arranged between the two arc segments 3901 and the two plane segments 3902. A glue receiving groove 3904 is provided on the inner surface of the first collar 391.

[0108] One end of the second collar 392 extends outward to form a stop block 3921. The outer surface of the second collar 392 includes two relatively arranged arc segments 3901, two plane segments 3902 that are relatively and parallelly arranged between the two arc segments 3901, and two transition segments 3903 that are relatively arranged between the two arc segments 3901 and the two plane segments 3902. A glue receiving groove 3904 is provided on the inner surface of the second collar 392.

[0109] During assembly, some components of the clamping mechanism 3 are first fixed to the bottom plate 11 of the fuselage 1. Below, the installation process of a first clamping mechanism and the bottom plate 11 of the fuselage 1 will be taken as an example for illustration.

[0110] Please refer to Figure 14 , the two clamping members 31 and the fixing member 33 are fixed to the bottom plate 11. Specifically, the bottom surface 315 of each clamping member 31 is in contact with the upper surface of the bottom plate 11. The clamping member 31 is positioned on the positioning hole 104 on the bottom plate 11 through the positioning convex column 318. Two fasteners 1036 (referring to Figure 16The screws at [location] respectively pass through two corresponding perforations 1021 on the bottom plate 11 and are connected to two fixing holes on the bottom surface 315 of the corresponding clamping member 31. Use two fasteners 1038 (referring to the Figure 16 screws at [location]) pass through two corresponding perforations 1021 on the bottom plate 11 and are connected to the fixing holes 1014 at the bottom of the base 331 of the fixing member 33.

[0111] Connect the two clamping members 31 and the fixing member 33 to the fixing device 9, such that the fixing frame 91 of the fixing device 9 is connected to the rear end of the bottom plate 11 of the fuselage 1, and further such that the installation space 900 of the mounting frame 92 of the fixing device 9 is located at the rear end of the fuselage 1 or behind the fuselage 1, and the installation space 900 extends along the direction from the front end to the rear end of the fuselage 1. Specifically, pass fasteners such as screws through the perforations 1023 of the extension plate 911 of the fixing frame 91 of the fixing device 9 and connect them to the fixing holes 1013 on the side surface 313 of the corresponding clamping member 31. Pass fasteners such as screws through the perforations 1024 of the side plate 921 of the mounting frame 92 of the fixing device 9 and connect them to the fixing holes 1014 on the side of the base 331 of the fixing member 33 away from the clamping portion 332.

[0112] Thus, fix the clamping mechanism 3 to the bottom plate 11 of the fuselage 1.

[0113] Please refer to Figures 2 - 4 , and install the arm 2 on the clamping mechanism 3. Below, the installation process of one arm 2 and one first clamping mechanism will be described.

[0114] Slip the collar 39 over the arm 2. Specifically, slip the first collar 391 and the second collar 392 over the arm 2 respectively. Strengthen the connection strength between the first collar 391 and the second collar 392 and the arm 2 by applying glue at the glue-receiving grooves 3904 of the first collar 391 and the second collar 392.

[0115] Install the arm 2 between the two clamping members 31 and the two pressing blocks 32. Specifically, pass the assembled arm 2 through the two clamping members 31 until the abutting block 3921 of the second collar 392 abuts against the surface of the clamping member 31 away from the center of the bottom plate 11. Fit the pressing block 32 into the installation groove 317 of the corresponding clamping member 31. Pass fasteners such as screws through the perforations 1025 of the two connecting portions 322 of the pressing block 32 and connect them to the fixing holes on the two bosses 319 of the clamping member 31.

[0116] Mount the robotic arm 2 between the fixing member 33 and the mating member 34. Specifically, pass a fastener such as a screw through the perforation 1026 of the clamping portion 332 of the fixing member 33 and connect it to the fixing hole 1016 on the top surface 314 of the clamping member 34.

[0117] Thus, mount the robotic arm 2 on the clamping mechanism 3.

[0118] Please refer to Figure 15 , connect the top plate 12 to the bottom plate 11. Specifically, place the top plate 12 above the bottom plate 11, and pass fasteners 1031, 1037 (such as screws) through the perforations on the top plate 12 and connect them to the fixing holes 1011 on the top surface 314 of the clamping member 31 and the fixing holes 1017 at the top of the connecting frame 14.

[0119] Please refer to Figure 1 , mount the storage box 8 on the fixing device 9. Specifically, insert the side bump 8111 on the outer side of the upper box body 81 of the storage box 8 along the guide slider 95 into the second installation space 902, so that the clamping block 97 is inserted into the clamping groove 83 of the storage box 8, the box body limiting member 98 abuts against the front side of the lower box body 82 of the storage box 8, the front end of the upper box body 81 of the storage box 8 is supported on the top plate 12, the liquid nozzle 84 is connected to the liquid nozzle 18 on the bottom plate 11, and the rear bump 8141 on the rear wall of the upper box body 81 of the storage box 8 abuts against the top of the partition beam 93. Pass the liquid pipe connected to the liquid nozzle 18 through the through hole 9121 on the substrate 912.

[0120] Please continue to refer to Figure 1 , mount the battery 7 on the fixing device 9. Specifically, insert the two guide grooves 72 of the battery 7 along the guide surface 942 of the guide block 94 into the first installation space 901 of the fixing device 9, and continue to insert along the first guide slide post 941 into the first installation space 901. The material of the first guide slide post 941 is a material with damping characteristics such as rubber, so that the battery 7 slowly enters the first installation space 901. When inserting the battery 7, press the pressing plate 7531 so that the snap plate 7532 moves away from the battery 7. Continue to insert the battery 7 so that the battery interface 71 of the battery 7 is electrically connected to the connection terminal 961 of the battery socket 96, the hook 7533 of the snap plate 7532 hooks on the clamping shaft 962, and the bump 73 of the battery 7 abuts against the elastic support block 944 of the guide block 94. Stop pressing the pressing plate 7531.

[0121] In this embodiment, the fixing device 9 is selected to fix the battery 7 and the packing case 8. The battery 7 and the packing case 8 can be supported on the fixing frame 91 by gravity and utilize this gravity during installation, making the operation more labor-saving.

[0122] A guiding block 94 is arranged inside the fixing device 9, which can guide the disassembly and assembly of the battery 7, making the installation of the battery 7 faster and more accurate, and improving the installation efficiency. Specifically, when the battery 7 is being inserted into the second installation space 902, the guiding block 94 can cooperate with the guiding groove 72 on the battery 7. The guiding block 94 plays a role in positioning and guiding the movement of the guiding groove 72, so that the installation of the battery 7 is faster and more accurate. At the same time, it can also limit the installed battery 7, making the installation of the battery 7 more firm.

[0123] A first guiding slide column 941 is arranged on the fixing device 9. A rolling motion is formed between the first guiding slide column 941 and the battery 7, playing a protective role on the surface of the battery 7.

[0124] The battery socket 96 on the fixing device 9 is arranged on the fixing frame 91, which can remove the electromagnetic interference effect of the large current of the battery 7 on the body head module.

[0125] The battery interface 71 of the battery 7 and the battery socket 96 on the fixing device 9 are inserted in a position corresponding to each other in the up-down direction. Thus, due to the action of the gravity of the battery 7 itself, the battery interface 71 and the battery socket 96 can be firmly contacted to achieve a stable electrical connection.

[0126] The handle 74 on the battery 7 can extend in the left-right direction. The pressing plate 7531 can be located at the rear side of the handle 74. The buckle plate 7532 can be connected below the pressing plate 7531 to open or close under the drive of the pressing plate 7531. Thus, it is more convenient to press the pressing plate 7531 when holding the handle 74, and single-handed operation can be achieved, making the operation more convenient.

[0127] When assembling the aircraft 100, one can hold the handle 74 with one hand and place the battery 7 vertically downward. The guiding groove 72 on the battery 7 moves down along the guiding block 94. Among them, the first guiding slide column 941 rolls closely along the inner wall surface of the guiding groove 72, serving the purpose of slowing down the descending speed of the battery 7. When the battery 7 is about to move into place downward, the pressing plate 7531 of the battery 7 can be slightly pressed, and the buckle plate 7532 can automatically open and be hooked on the clamping shaft 962, playing a role in fixing the battery 7. At this time, the battery connector 71 of the battery 7 and the connection terminal 961 of the battery socket 96 can be inserted, and the electrical connection is firm. During this operation process, the gravity of the battery 7 itself can be effectively utilized, the installation of the battery 7 is convenient and firm, and the operation is labor-saving.

[0128] In this embodiment, by extending a part of the fixing device 9 between the top plate 12 and the bottom plate 11, it is beneficial to control the overall size and weight of the fuselage 1. Connecting the two ends of at least part of the support legs of the landing gear 6 to the bottom plate 11 and the fixing device 9 respectively can improve the structural reliability of the fixing device 9 and prevent the fixing device 9 from deforming due to suspension.

[0129] In this embodiment, such a clamping mechanism 3 is used to clamp the arm 2 on the fuselage 1. On the one hand, the assembly process of the arm 2 and the power device is simple and easy to operate; on the other hand, the connection between the arm 2 and the fuselage 1 is stable and reliable. Since the flat section 302 of the through hole 316 is perpendicular to the bottom surface 315 of the clamping member 31, and both flat sections 302 are perpendicular to the top surface 314 and the bottom surface 315 of the clamping member 31, and the outer peripheral surface of the collar 39 is adapted to the shape of the through hole 316 of the clamping mechanism 3. When the arm 2 is inserted into the through hole 316 of the clamping mechanism 3, the central axis of the rotating shaft of the motor of the power device can be kept perpendicular to the horizontal plane, that is, perpendicular to the plane where the bottom plate 11 of the fuselage 1 is located, so as to provide a vertically upward lift force for the aircraft 100.

[0130] Of course, the aircraft 100 of the embodiment of the present invention is not limited to the structure described in the above embodiment.

[0131] In other embodiments, the first installation space 901 can be used to install the storage box 8. The second installation space 902 can be used to install the battery 7. Correspondingly, the guide slider 95 can be arranged on the inner side of each side plate 921 near the first installation space 901. The guide block 94 can be arranged on the inner side of each side plate 921 near the second installation space 902, and the battery socket 96 can be arranged on the partition beam 93.

[0132] In other embodiments, the partition beam 93 can be connected between the base plate 912 of the fixing frame 91 and the end plate 922 of the mounting frame 92. The two guide sliders 95 can be arranged on the side plate 921 and the partition beam 93 on the side near the first installation space 901. The guide block 94 can be arranged on the side plate 921 and the partition beam 93 near the second installation space 902. The battery socket 96 can be arranged on the end plate 922 of the mounting frame 92 near the second installation space 902.

[0133] For example, in other embodiments, the aircraft 100 can also be a six-rotor aircraft, an eight-rotor aircraft, or an aircraft with more rotors. Correspondingly, the numbers of the arms 2, the clamping mechanisms 3, and the power devices of different rotor aircraft will also be different, and can be analogized in turn according to the four-rotor aircraft, as long as the numbers of the arms 2, the clamping mechanisms 3, and the power devices on the aircraft 100 are the same.

[0134] For example, in some embodiments, the installation space 900 has two inner wall surfaces opposite to each other, and at least one of the inner wall surfaces is provided with a battery guiding structure for guiding the insertion and extraction of the battery 7. The battery guiding structure can be formed in various forms. In the above embodiments, one battery guiding structure in the form of a guiding block 94 is listed, and the battery guiding structure can also adopt a ball structure.

[0135] In other embodiments, the shape of the through hole 316 of the clamping mechanism 3 can be adaptively changed, and the collar 39 on the machine arm 2 will also be adaptively changed.

[0136] In other embodiments, for example, as Figure 11 In, among the inner peripheral surfaces of the through hole 316 of the clamping mechanism 3, at least one of the plane segments 302 and the bottom surface 315 is provided with an acute angle. That is, the vertical central axis of the through hole 316 and the top surface 314 and the bottom surface 315 of the clamping member 31 form an acute angle. As Figure 11 In, the vertical central axis of the through hole 316 can form an 88-degree angle with the top surface 314 and the bottom surface 315 of the clamping member 31, that is, the plane segment 302 of the through hole 316 is inclined by 2 degrees relative to the vertical central axis of the clamping mechanism 3. Since the outer peripheral surface of the collar 39 is adapted to the shape of the through hole 316 of the clamping mechanism 3, when the machine arm 2 is inserted into the through hole 316 of the clamping mechanism 3, the central axis of the rotating shaft of the motor of the power device can be maintained at an angle of 2 degrees with the horizontal plane, that is, at an angle of 2 degrees with the plane where the bottom plate 11 of the fuselage 1 is located; by adjusting the angle between the vertical central axis of the through hole 316 and the vertical central axis of the clamping mechanism 3, the angle between the central axis of the rotating shaft of the motor and the horizontal plane can be adjusted, so as to ensure the stable and reliable connection between the machine arm 2 and the fuselage 1 while obtaining more flight parameters of the aircraft 100. For example, when it is necessary to meet the flight requirements and the spiral central axis of the propeller connected to the machine arm 2 needs to have a certain angle with the vertical line, it can be completed by adjusting the angle between the vertical central axis of the through hole 316 and the vertical central axis of the clamping mechanism 3.

[0137] 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 therefore should not be construed as a limitation to the present invention.

[0138] In addition, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the quantity of the indicated technical features. Thus, features defined with "first" and "second" may explicitly or implicitly include one or more of such features. In the description of the present invention, unless otherwise specified, the meaning of "a plurality of" is two or more.

[0139] In the description of the present invention, unless otherwise clearly specified and defined, the terms "mounted", "connected", "coupled", and "fixed" shall be construed broadly. For example, it may be a fixed connection, a detachable connection, or integrated; it may be a mechanical connection or an electrical connection; it may be directly connected or indirectly connected through an intermediate medium, and it may be the internal communication of two components or the interaction relationship between two components. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention may be understood according to specific circumstances.

[0140] In the description of this specification, the description with reference to terms such as "embodiment", "example", etc. means that the specific features, structures, materials, or characteristics described in connection with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representations of the above terms do 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.

[0141] Although the embodiments of the present invention have been shown and described, those of ordinary skill in the art can understand that various changes, modifications, substitutions, and variations can be made to these embodiments without departing from the principles and spirit of the present invention. The scope of the present invention is defined by the claims and their equivalents.

Claims

1. An aircraft, comprising a fuselage and a fixing device, characterized in that, The fixing device includes: a mounting frame for connecting to the fuselage and a fixing frame connected to the rear end of the fuselage. The mounting frame is connected to the fixing frame. The mounting frame has a mounting space extending in the direction from the front end to the rear end of the fuselage. The mounting space is located at the rear end of the fuselage or behind the fuselage. The mounting space includes a first mounting space and a second mounting space. The first mounting space is for mounting one of the battery and the storage box, and the second mounting space is for mounting the other of the battery and the storage box; the fixing frame includes two opposite extending plates for connecting to the fuselage; the aircraft further includes a clamping mechanism. The clamping mechanism includes a clamping member for clamping the arm of the aircraft. The clamping member is connected to the fuselage. The clamping member has a side surface connected to the corresponding extending plate.

2. The aircraft according to claim 1, wherein The clamping mechanism further includes a fixing member and a cooperating member. The fuselage includes a bottom plate, and the mounting frame includes two opposite side plates; the fixing member is fixed to the bottom plate and is connected to the side plate of the mounting frame; the arm is mounted between the fixing member and the cooperating member.

3. The aircraft according to claim 2, wherein, The fixing member includes a base portion and a clamping portion extending from one side of the base portion; one side of the clamping portion away from the base portion is recessed inward to form a first clamping surface. Two through holes are provided at both ends of the clamping portion adjacent to the first clamping surface; one side of the cooperating member is recessed inward to form a second clamping surface. Two fixing holes are provided at both ends of the cooperating member adjacent to the second clamping surface; A fastener passes through the through hole of the clamping portion of the fixing member and is connected to the fixing hole of the cooperating member.

4. The aircraft according to claim 1, characterized in that, The clamping mechanism further includes a pressing block; the pressing block includes a locking portion and two connecting portions located on both sides of the locking portion. Each connecting portion is provided with a through hole; the clamping member is provided with a mounting groove and a through hole communicating with the mounting groove. On the inner surface of the clamping member, two protrusions extend toward the center of the through hole at the connection of the mounting groove and the through hole. Each protrusion is provided with a fixing hole; the arm passes through the clamping member, the pressing block is fitted in the mounting groove of the corresponding clamping member, and a fastener passes through the through holes of the two connecting portions of the pressing block and is connected to the fixing holes of the two protrusions of the clamping member.

5. The aircraft according to claim 4, characterized in that, The clamping mechanism further includes a collar. The collar includes a second collar, and the fuselage includes a bottom plate; the second collar is sleeved on the arm, and a stop block extends outward from one end of the second collar; the arm passes through the clamping member until the stop block of the second collar abuts against the surface of the clamping member away from the center of the bottom plate.

6. The aircraft according to claim 1, wherein The fuselage includes a bottom plate. The bottom plate is provided with a positioning hole and a through hole; the clamping member has a bottom surface provided with a positioning protrusion and a fixing hole; the bottom surface of the clamping member is in contact with the upper surface of the bottom plate. The clamping member is positioned on the positioning hole on the bottom plate by the positioning protrusion, and is connected to the fixing hole on the bottom surface of the corresponding clamping member by a fastener passing through the corresponding through hole on the bottom plate.

7. The aircraft according to claim 1, characterized in that, The first installation space is adjacent to the second installation space. The first installation space is away from the fixing frame, and the second installation space is adjacent to the fixing frame. The first installation space is for installing the battery, and the second installation space is for installing the storage box.

8. The aircraft according to claim 7, wherein The mounting frame includes two opposite side plates and an end plate connected between the two side plates. One end of each side plate away from the end plate is connected to the corresponding extension plate. The first installation space is adjacent to the end plate, and the second installation space is away from the end plate.

9. The aircraft according to claim 1, wherein, The two extension plates are arranged in a V shape.

10. The aircraft according to claim 1, characterized in that, The fixing frame further includes a base plate for connecting to the fuselage. The two extension plates extend from opposite sides of the base plate. The base plate is provided with a through hole for a liquid pipe connected to the storage box to pass through.

11. The aircraft according to claim 8, characterized in that The fixing device further includes a partition beam connected between the two side plates. The first installation space and the second installation space are respectively located on both sides of the partition beam.

12. The aircraft according to claim 8, wherein, It further includes the battery. The battery includes two opposite first sides and a bottom connected to the bottoms of the two first sides. Each first side is respectively provided with a guiding groove penetrating through the bottom of the battery. Inside each side plate, a guiding block is provided adjacent to the first installation space. Each guiding block is pivotally mounted with a first guiding slide column in a direction parallel to the side plate. The first guiding slide column is for slidably abutting against the guiding groove.

13. The aircraft according to claim 12, wherein The side of the guiding block facing away from the side plate has an inclined guiding surface.

14. The aircraft according to claim 13, characterized in that, A convex block is provided in the guiding groove of the battery. A slotted groove is provided on the guiding surface. An elastic support block for abutting against the convex block of the battery is provided at the bottom of the slotted groove.

15. The aircraft according to claim 12, wherein, The first guiding slide column is a rubber column.

16. The aircraft according to claim 12, wherein The battery further includes a top connected to the tops of the two first sides. A battery interface is provided on the top of the battery. A battery socket is mounted on the end plate. A connection terminal for electrically connecting to the battery interface is provided on the top of the battery socket.

17. The aircraft according to claim 11, characterized in that, It further includes the storage box. The storage box includes an upper box body and a lower box body vertically connected to the bottom of the upper box body. The upper box body includes two opposite second sides. Each second side of the upper box body is provided with a side convex block. Inside each side plate, a guiding slider is provided adjacent to the second installation space. The side of the guiding slider facing away from the side plate is pivotally mounted with a second guiding slide column in a direction parallel to the side plate. The second guiding slide column is for slidably abutting against the side convex block of the storage box.

18. The aircraft according to claim 17, wherein Each second side of the upper box body is provided with a clamping groove. The fixing device includes a clamping block and a limiting member provided on the fuselage. The clamping block is for abutting against the clamping groove of the storage box, and the limiting member is for abutting against the side of the lower box body of the storage box facing the upper box body.

19. The aircraft according to claim 17, wherein, The lower box body further includes a rear wall connected to the rear ends of the two second sides. A rear convex block is provided on the rear wall of the lower box body. The partition beam is for abutting against the rear convex block of the lower box body.

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