aircraft

Abstract

The present invention discloses an aircraft, comprising a fuselage and a fixture, the fixture comprising: a mounting bracket for connecting to the fuselage, the mounting bracket having an installation space extending from the front end of the fuselage to the rear end of the fuselage, the installation space being located at the rear end of the fuselage or behind the fuselage, and the installation space being used to install at least one of a battery and a container. According to an embodiment of the aircraft of the present invention, the above-mentioned design enables the center of gravity of the aircraft to be vertically close to the plane where the lift of the aircraft is located, thereby facilitating the flight of the aircraft. At the same time, such a design also facilitates the removal or insertion of items from the installation space of the fixture.

Description

[0001] This application is a divisional application of the invention patent application filed on August 12, 2016, with the earliest priority date being April 7, 2016, the invention name being “Aircraft” and the application number being 201610663394.8. Technical Field

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

[0003] Related art disclosures show that when batteries and containers (such as medicine boxes) are installed on aircraft, the batteries are typically placed inside the fuselage, with the containers located below. This arrangement places the center of gravity of the aircraft too low relative to the propeller's rotation plane, hindering flight. Summary of the Invention

[0004] The present invention aims to solve one of the technical problems in the related art at least to a certain extent. To this end, the present invention aims to provide an aircraft that is easy to fly.

[0005] An aircraft according to the present invention includes a fuselage and a fixing device, the fixing device including: a mounting frame for connecting to the fuselage, the mounting frame having a mounting space extending from a front end of the fuselage to a rear end of the fuselage, the mounting space being located at the rear end of the fuselage or behind the fuselage, the mounting space including a first mounting space;

[0006] The mounting frame includes two opposite side plates, and a guide block is provided on the inner side of each side plate adjacent to the first mounting space;

[0007] The aircraft further includes the battery, the battery including two opposite first sides and a bottom portion connected to the bottom ends of the two first sides, each first side being provided with a guide groove penetrating the bottom portion of the battery;

[0008] When the battery is inserted downward into the first installation space, the guide block can cooperate with the guide groove to position and guide the movement of the guide groove.

[0009] In the aircraft according to an embodiment of the present invention, by horizontally cantilevering the mounting space of the fixture from the fuselage, the center of gravity of the aircraft is vertically aligned with the plane of lift, thereby facilitating flight. This design also facilitates the removal and insertion of items from the mounting space of the fixture. Furthermore, as the battery is inserted downward into the first mounting space, the guide block can position and guide the movement of the guide slot.

[0010] In some embodiments, the guide block has an inclined guide surface on a side facing away from the side plate; the two guide grooves of the battery can be inserted into the first installation space along the guide surface.

[0011] In some embodiments, the guide surface is provided at the top of the guide block on a side facing away from the side plate, and the thickness of the guide block increases gradually from the top to the bottom.

[0012] In some embodiments, a protrusion is provided in the guide groove of the battery, a groove is provided on the guide surface, and an elastic support block for abutting against the protrusion of the battery is provided at the bottom of the groove.

[0013] In some embodiments, a first guide slide column is pivotally mounted on a middle portion and a bottom portion of the guide block on a side facing away from the side plate in a direction parallel to the side plate.

[0014] In some embodiments, the mounting frame also includes an end plate connected between the two side plates, the battery also includes a top connected to the top ends of the two first sides, a battery interface is provided at the top of the battery, a battery socket is installed on the end plate, and a connection terminal for electrically connecting to the battery interface is provided at the top of the battery socket.

[0015] In some embodiments, the battery is provided with a latch, which includes two connecting plates arranged opposite to each other, a pivot connected between the two connecting plates, and a latch portion pivotally connected to the pivot in the middle, and the latch portion has a hook; the battery socket is pivotally provided with a latch shaft around the connecting terminal; during the process of inserting the battery into the first installation space, the hook is hooked on the latch shaft.

[0016] In some embodiments, the snap portion includes a pressing plate and a snap plate located on both sides of the pivot; the snap plate is connected to the pressing plate in a bending manner, and the snap plate is provided with the hook.

[0017] In some embodiments, each guide block is pivotally mounted with a first guide slide column, and the first guide slide column is used to slidably abut the guide groove.

[0018] In some embodiments, each of the guide blocks is pivotally mounted with the first guide slide column in a direction parallel to the side plate.

[0019] In some embodiments, the first guide column is a rubber column.

[0020] In some embodiments, a roller mounting groove and a through groove adjacent to the roller mounting groove are provided on the side of the guide block facing away from the side plate in a direction parallel to the side plate; the roller mounting groove is used to pivotally mount the first guide column, and the through groove is used for allowing the first guide column to rotate.

[0021] In some embodiments, the fixing device also includes a fixing bracket connected to the rear end of the fuselage, the mounting bracket is connected to the fixing bracket, and the installation space also includes a second installation space adjacent to the first installation space, the first installation space is away from the fixing bracket, and the second installation space is adjacent to the fixing bracket. The first installation space is used to install the battery, and the second installation space is used to install the container.

[0022] In some embodiments, the fixing frame includes two opposite extension plates, which are used to be connected to the fuselage. The mounting frame also includes an end plate connected between the two side plates, and an end of each side plate away from the end plate is connected to the corresponding extension plate. The first mounting space is adjacent to the end plate, and the second mounting space is away from the end plate.

[0023] In some embodiments, the two extension plates are arranged in a V shape, and the aircraft also includes a clamping mechanism, which includes a clamping member for clamping the arm of the aircraft, and the clamping member is used to be connected to the fuselage. The clamping member has a side, and the side is used to be connected to the corresponding extension plate.

[0024] 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, and the base plate is provided with a through hole for a liquid pipe connected to the container to pass through.

[0025] In some embodiments, the fixing device further includes a partition beam, which is used to be connected between the two side plates, and the first installation space and the second installation space are respectively located on both sides of the partition beam.

[0026] In some embodiments, the aircraft also includes the container, 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 protrusion, and the inner side of each side panel is provided with a guide slide block adjacent to the second installation space, and the side of the guide slide block facing away from the side panel is pivotally mounted with a second guide slide column in a direction parallel to the side panel, and the second guide slide column is used to slidably abut the side protrusion of the container.

[0027] In some embodiments, each second side of the upper box body is provided with a locking groove, and the fixing device includes a clamping block and a limiting member for being set on the fuselage, the clamping block is used to abut the locking groove of the container box, and the limiting member is used to abut the side of the lower box body of the container box facing the upper box body.

[0028] In some embodiments, the lower box body further includes a rear wall connected to the rear ends of the two second sides, the rear wall of the lower box body is provided with a rear protrusion, and the partition beam is used to abut the rear protrusion of the lower box body.

[0029] The aircraft according to the present invention comprises: a fuselage; a fixing device according to the present invention; a battery; and a container.

[0030] 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

[0031] 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:

[0032] Figure 1 is a three-dimensional assembly diagram of an aircraft according to an embodiment of the present invention;

[0033] Figure 2 yes Figure 1 A top view of the aircraft (excluding the battery, container, and top panel);

[0034] Figure 3 yes Figure 2 An enlarged view of the machine arm in an assembled state with the clamping member at the second collar;

[0035] Figure 4 yes Figure 2 The three-dimensional assembly diagram of the machine arm and the ring;

[0036] Figure 5 yes Figure 4 A perspective view of the first set of rings in FIG;

[0037] Figure 6 yes Figure 5 a side view of the first set of rings;

[0038] Figure 7 yes Figure 4 A perspective view of the second ring in FIG;

[0039] Figure 8 yes Figure 2 A side view of the clamping member in FIG.

[0040] Figure 9 yes Figure 8 A three-dimensional view of a clamping member;

[0041] Figure 10 yes Figure 2 A three-dimensional view of the compression block in FIG.

[0042] Figure 11is a side view of a clamping member according to another embodiment of the present invention;

[0043] Figure 12 yes Figure 2 A perspective view of a fixing member in FIG;

[0044] Figure 13 yes Figure 2 A three-dimensional diagram of the mating parts in FIG.

[0045] Figure 14 is based on Figure 1 A three-dimensional assembly drawing of the aircraft (excluding the container, arms, power unit and batteries);

[0046] Figure 15 is based on Figure 1 A three-dimensional assembly drawing of the aircraft (excluding the container and batteries);

[0047] Figure 16 yes Figure 14 Bottom view of the aircraft (minus the container, arms, power unit, and batteries);

[0048] Figure 17 yes Figure 14 A perspective view of the fixing device in FIG.

[0049] Figure 18 yes Figure 14 A three-dimensional diagram of the box limiter in FIG.

[0050] Figure 19 yes Figure 17 A perspective view of the battery socket in FIG.

[0051] Figure 20 yes Figure 17 A perspective view of the guide block in FIG.

[0052] Figure 21 yes Figure 17 A side view of the guide block in FIG.

[0053] Figure 22 yes Figure 15 A three-dimensional diagram of the clamping block in FIG;

[0054] Figure 23 is based on Figure 17 A three-dimensional view of the guide slider in FIG.

[0055] Figure 24 yes Figure 1 A perspective view of the battery in FIG;

[0056] Figure 25 is a side view of a battery and a fixing device in an assembled state according to an embodiment of the present invention;

[0057] Figure 26 yes Figure 25 Cross-sectional view along AA direction;

[0058] Figure 27 is based on Figure 1 A three-dimensional view of the container in FIG.

[0059] Figure 28 is based on Figure 1 A three-dimensional view of the landing gear.

[0060] Reference numerals:

[0061] Aircraft 100,

[0062] Fixing hole 1011, fixing hole 1012, fixing hole 1013, fixing hole 1014, fixing hole 1015, fixing hole 1016, fixing hole 1017,

[0063] Perforation 1021, perforation 1023, perforation 1024, perforation 1025, perforation 1026,

[0064] Fastener 1031, fastener 1032, fastener 1033, fastener 1034, fastener 1035, fastener 1036, fastener 1037, fastener 1038,

[0065] Positioning hole 104,

[0066] Body 1, bottom plate 11, top plate 12, connecting frame 14, first frame 141, second frame 142, through hole 17, liquid nozzle 18, machine arm 2, rod body 21,

[0067] Clamping mechanism 3, arc segment 301, plane 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 331, clamping portion 332, first clamping surface 333, matching member 34, second clamping surface 341, collar 39, arc segment 3901, plane segment 3902, transition segment 3903, glue-containing groove 3904, first collar 391, second collar 392, stop block 3921,

[0068] Landing gear 6, support leg 60, front support leg 601, rear support leg 602, bottom support leg 603, horizontal connection part 611, vertical connection part 612,

[0069] Battery 7, first side 703, bottom 702, top 701, back side 704, battery connector 71, guide groove 72, protrusion 73, handle 74, fastener 75, connecting plate 751, pivot 752, fastening portion 753, pressing plate 7531, fastening plate 7532, hook 7533,

[0070] Container 8, upper box body 81, second side 811, side protrusion 8111, positioning groove 8112, bottom wall 812, top wall 813, rear wall 814, rear protrusion 8141, lower box body 82, liquid nozzle 84, handle 86, vent 87,

[0071] 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, installation frame 92, side plate 921, end plate 922, partition beam 93, guide block 94, first guide slide 941, guide surface 942, slot 943, elastic support block 944, roller installation slot 945, through slot 946, guide slider 95, second guide slide 951, battery socket 96, connecting terminal 961, clamping shaft 962, clamping block 97, elastic reinforcement hole 971, box limiter 98, limiting portion 981, connecting portion 982, reinforcing rib 983. DETAILED DESCRIPTION

[0072] The following describes embodiments of the present invention in detail, examples of which are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are intended to be used to explain the present invention, and are not to be construed as limiting the present invention.

[0073] Reference below Figure 1-Figure 28 An aircraft 100 according to an embodiment of the present invention is described. The aircraft 100 includes a fuselage 1 and a fixing device 9. The fixing device 9 is used to fix at least one of a battery 7 and a container 8 of the aircraft 100. The container 8 is suitable for containing items to be sprayed or transported.

[0074] like Figure 14 、 Figure 15 and Figure 17 As shown, the fixing device 9 includes: a mounting bracket 92 for connecting to the fuselage 1, the mounting bracket 92 has an installation space 900 extending from the front end of the fuselage 1 to the rear end of the fuselage 1, and the installation space 900 is located at the rear end of the fuselage 1 or behind the fuselage 1, and the installation space 900 is used to install at least one of the battery 7 and the container 8.

[0075] By horizontally suspending the installation space 900 of the fixing device 9 from the fuselage 1, the center of gravity of the aircraft 100 is vertically close to the plane where the lift of the aircraft 100 is located, thereby facilitating the flight of the aircraft 100. This design also facilitates the removal or insertion of items from the installation space 900 of the fixing device 9.

[0076] For ease of understanding, the following Figure 1-Figure 28 An aircraft 100 according to an embodiment of the present invention is described.

[0077] like Figure 1 and Figure 2 As shown, the aircraft 100 includes a fuselage 1, a landing gear 6, an arm 2, a clamping mechanism 3, a power unit and a fixing device 9. Figure 1 、 Figure 24-27 As shown, the aircraft 100 further includes a battery 7 and a container 8, wherein the container 8 is suitable for containing items to be sprayed or transported. In this embodiment, the aircraft 100 is a quadcopter, and the number of the arms 2 and the number of the power devices are both four.

[0078] See also Figure 1 、 Figure 14 and Figure 15 The fuselage 1 includes a bottom plate 11 and a top plate 12 arranged opposite to each other in the vertical direction, and a connecting frame 14 connected to the bottom plate 11. Figure 16 As shown, the bottom plate 11 is provided with a positioning hole 104 and a through hole 1021 .

[0079] like Figure 14 and 15 As shown, the bottom plate 11 is provided with a through hole 17 adjacent to one side thereof, and a liquid nozzle 18 is provided at the through hole 17. The top plate 12 is provided with a through hole.

[0080] See also Figure 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 and the bottom of the first frame 141 are connected by fasteners 1032 (such as Figure 16 As shown) the second frame 142 is connected to the bottom plate 11 of the fuselage 1 by screws, and fixing holes 1017 are provided on the tops of the second frame 142 and the first frame 141.

[0081] like Figure 14 and Figure 17 As shown, the fixing device 9 is connected to the connecting frame 14. Figures 17-23 As 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. Figure 15As shown, the fixing device 9 further includes a clamping block 97 and a box limiting member 98. The fixing frame 91 and the mounting frame 92 can be integrally formed.

[0082] The fixing frame 91 includes a base plate 912 and two extension plates 911 extending obliquely from opposite sides of the base plate 912. The base plate 912 is secured to the end of the first frame 141 away from the second frame 142 via fasteners, such as screws. A through hole 9121 is defined in the base plate 912. The two extension plates 911 are arranged in a V-shape, each having a through hole 1023.

[0083] The mounting frame 92 includes two opposing side panels 921 and end panels 922 connected to the side panels 921. Each side panel 921 is connected to a corresponding extension panel 911 at one end away from the end panel 922. The side panels 921 are provided with through-holes 1024. The mounting frame 92 defines an installation space 900. The partition beam 93 is connected between the side panels 921, dividing the installation space 900 into a first installation space 901 and a second installation space 902.

[0084] Please also refer to Figure 17 and Figure 20-23 A guide block 94 is provided on the inner side of each side panel 921 adjacent to the first installation space 901. The guide block 94 has a guide surface 942 at the top of the side facing away from the side panel 921. The guide surface 942 is tilted so that the thickness of the guide block 94 increases gradually from the top to the bottom. A slot 943 is provided on the guide surface 942, and an elastic support block 944 is provided at the bottom of the slot 943. A roller mounting slot 945 and a through slot 946 adjacent to the roller mounting slot 945 are provided at the middle and bottom of the side facing away from the side panel 921 in a direction parallel to the side panel 921. The roller mounting slot 945 is used to pivotally mount the first guide column 941. The two through slots 946 are used for allowing the first guide column 941 to rotate. The material of the first guide column 941 is a material with damping properties such as rubber.

[0085] A guide slide 95 is provided on the inner side of each side plate 921 adjacent to the second installation space 902. Two second guide slide posts 951 are pivotally mounted on the top and bottom of the guide slide 95 on the side facing away from the side plate 921 in a direction parallel to the side plate 921.

[0086] A battery socket 96 is provided on the inner side of the end plate 922. A connection terminal 961 is provided on the top of the battery socket 96. A clamping shaft 962 is pivotally provided around the battery socket 96 and is parallel to and adjacent to the end plate 922.

[0087] like Figure 15 and Figure 22 As shown, the clamping block 97 is disposed on the top plate 12 , and an elastic reinforcement hole 971 is provided on the clamping block 97 .

[0088] like Figure 15 and Figure 18 As shown, the box stopper 98 is disposed on the bottom plate 11. The box stopper 98 includes a stopper portion 981, a connecting portion 982 extending from the middle of the stopper portion 981, and a reinforcing rib 983 connected between the lower portion of one side of the stopper portion 981 and the connecting portion 982. The connecting portion 982 is connected to the lower surface of the bottom plate 11 via a fastener 1033, such as a screw.

[0089] like Figure 24-26 As shown, the battery 7 is roughly rectangular. The battery 7 includes two opposing first sides 703, a bottom 702 connected to the bottom ends of the two first sides 703, a top 701 connected to the top ends of the two first sides 703, and a rear side 704 connected to the rear ends of the two first sides 703. A latch 75 and a battery interface 71 adjacent to the latch 75 are provided at the top of the rear side 704 of the battery 7. The latch 75 includes two opposing connecting plates 751, a pivot 752 connected between the two connecting plates 751, and a latch portion 753 pivotally connected to the pivot 752 in the middle. The latch portion 753 includes a pressing plate 7531 and a latch plate 7532 located on either side of the pivot 752. The latch plate 7532 is bent and connected to the pressing plate 7531. The latch plate 7532 has a hook 7533. The two first sides 703 of the battery 7 are respectively provided with two guide grooves 72 that pass through the bottom of the battery 7. The top wall of each guide groove 72 is provided with a downward projection 73. The top of the battery 7 is provided with a handle 74.

[0090] like Figure 27 As shown, the container box 8 includes an upper box body 81 and a lower box body 82 connected to the bottom of the upper box body 81 approximately vertically. The lower box body 82 and the upper box body 81 are approximately rectangular. The upper box body 81 includes two opposite second sides 811, a bottom wall 812 connected to the bottom ends of the two second sides, a top wall 813 connected to the top ends of the two second sides, and a rear wall 814 connected to the rear ends 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. Each second side 811 of the upper box body 81 is provided with a side protrusion 8111 and a locking groove 8112. A rear protrusion 8141 is provided on the rear wall 814 of the upper box body 81. A handle 86 and a vent 87 are provided on the top wall 812 of the upper box body 81.

[0091] like Figure 16 and Figure 28As 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. A horizontal connecting portion 611 is provided at one end of the front support leg 601 away from the bottom support leg 603. Figure 16 As shown, the horizontal connection portion 611 is connected to the bottom plate 11 of the fuselage 1 through a fastener 1034 (such as a screw). The end of the rear support leg 602 away from the bottom support leg 603 is provided with a vertical connection portion 612. Figure 15 As shown, the vertical connection portion 612 is connected to the end plate 922 and the corresponding side plate 921 of the fixing device 9 through fasteners 1035 (such as screws).

[0092] like Figure 2 As shown, 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.

[0093] See also 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 fitting member 34, and a collar 39. Each second clamping mechanism includes two clamping members 31, two pressing blocks 32, and a collar 39.

[0094] like Figure 8 and Figure 9As shown, each clamping member 31 has a first surface 311 and a second surface 312 facing each other, 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 ends of the first surface 311 and the ends of the second surface 312 and connected to the top surface 314 and the bottom surface 315. The clamping member 31 is provided with a through hole 316 that passes through the first surface 311 and the second surface 312. The first surface 311 and the first surface 312 are provided with a plurality of grooves around the through hole 316 to reduce the weight of the clamping member 31. The inner circumference of the through hole 316 includes two opposing arc segments 301, two opposing and parallel planar segments 302 located between the two arc segments 301, and two opposing transition segments 303 located between the two arc segments 301 and the two planar segments 302. Each planar segment 302 is perpendicular to the bottom surface 315 of the clamping member 31, and each transition segment 303 may be composed of multiple small planes or an arcuate surface. The clamping member 32 also has a mounting groove 317 extending through the top surface 314 and the arc segment 301 adjacent to the top surface 314. The mounting groove 317 communicates with the through hole 316. Two fixing holes 1011 are provided on the top surface 314 at both ends adjacent to the mounting groove 317. The inner surface of the clamping member 31 has two bosses 319 extending toward the center of the through hole 316, near the junction of the mounting groove 317 and the through hole 316. Each boss 319 has a fixing hole. The bottom surface 315 is provided with two positioning bosses 318 and two fixing holes, facing away from the top surface 314. One of the two side surfaces 313 has a fixing hole 1012.

[0095] Each pressing block 32 includes a locking portion 321 and two connecting portions 322 located on both sides of the locking portion 321. The middle of the locking portion 321 is recessed to form a supporting surface 323. Each connecting portion 322 is provided with a through hole 1025.

[0096] The fixing member 33 includes a base 331 and a retaining portion 332 extending from one side of the base 331. The top, bottom, and side of the base 331 away from the retaining portion 332 are respectively provided with a retaining hole 1013, a retaining hole 1014, and a retaining hole 1015. The side of the retaining portion 332 away from the base 331 is recessed inward to form a first retaining surface 333. The retaining portion 332 is provided with two through-holes 1026 at both ends adjacent to the first retaining surface 333.

[0097] One side of the fitting member 34 is recessed inward to form a second retaining surface 341 . The fitting member 34 defines two fixing holes 1016 at two ends adjacent to the second retaining surface 341 .

[0098] Please refer to Figure 4-Figure 7 Each ring 39 includes a first ring 391 and a second ring 392 .

[0099] The outer surface of the first collar 391 includes two opposing arc segments 3901, two opposing and parallel planar segments 3902 located between the two arc segments 3901, and two opposing transition segments 3903 located between the two arc segments 3901 and the two planar segments 3902. A glue-receiving groove 3904 is defined on the inner surface of the first collar 391.

[0100] A stop block 3921 extends outward from one end of the second collar 392. The outer surface of the second collar 392 includes two opposing arc segments 3901, two opposing and parallel planar segments 3902 located between the two arc segments 3901, and two opposing transition segments 3903 located between the two arc segments 3901 and the two planar segments 3902. A glue-receiving groove 3904 is defined on the inner surface of the second collar 392.

[0101] During assembly, some components of the clamping mechanism 3 are first fixed to the bottom plate 11 of the fuselage 1. The following will take the installation process of a first clamping mechanism and the bottom plate 11 of the fuselage 1 as an example for description.

[0102] See also Figure 14 , fix the two clamping members 31 and the fixing member 33 to the base plate 11. Specifically, the bottom surface 315 of each clamping member 31 contacts the upper surface of the base plate 11. The clamping member 31 is positioned on the positioning hole 104 on the base plate 11 through the positioning boss 318. Figure 16 The screws at the bottom of the clamp 31 are respectively passed through the corresponding two through holes 1021 on the bottom plate 11 and connected to the two fixing holes on the bottom surface 315 of the corresponding clamp 31. Figure 16 The screws at the bottom (in the slots) pass through the corresponding two through-holes 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.

[0103] The two clamping members 31 and the fixing member 33 are connected 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. Furthermore, the installation space 900 of the mounting frame 92 of the fixing device 9 is located at the rear end or behind the fuselage 1, and the installation space 900 extends from the front end to the rear end of the fuselage 1. Specifically, fasteners such as screws are passed through the through-holes 1023 of the extension plate 911 of the fixing frame 91 of the fixing device 9 and connected to the corresponding fixing holes 1013 on the side 313 of the clamping member 31. Fasteners such as screws are passed through the through-holes 1024 of the side plate 921 of the mounting frame 92 of the fixing device 9 and connected to the fixing holes 1014 on the side of the base 331 of the fixing member 33, away from the clamping portion 332.

[0104] Thus, the clamping mechanism 3 is fixed to the bottom plate 11 of the body 1 .

[0105] See also Figure 2-Figure 4 , 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.

[0106] The collar 39 is mounted on the arm 2. Specifically, the first collar 391 and the second collar 392 are mounted on the arm 2. Glue is applied to the glue grooves 3904 of the first collar 391 and the second collar 392 to strengthen the connection between the first collar 391 and the second collar 392 and the arm 2.

[0107] Install the arm 2 between the two clamps 31 and the two pressure blocks 32. Specifically, pass the assembled arm 2 through the two clamps 31 until the stop block 3921 of the second collar 392 abuts against the surface of the clamp 31 away from the center of the base plate 11. Fit the pressure blocks 32 into the corresponding mounting slots 317 of the clamp 31. Insert fasteners, such as screws, through the through-holes 1025 of the two connecting portions 322 of the pressure block 32 and connect them to the fixing holes of the two bosses 319 of the clamp 31.

[0108] The arm 2 is mounted between the fixing member 33 and the matching member 34 . Specifically, a fastener such as a screw is passed through the through hole 1026 of the clamping portion 332 of the fixing member 33 and connected to the fixing hole 1016 of the matching member 34 .

[0109] In this way, the arm 2 is mounted on the clamping mechanism 3 .

[0110] See also Figure 15, connect the top plate 12 to the bottom plate 11. Specifically, place the top plate 12 above the bottom plate 11, and use fasteners 1031 and 1037 (such as screws) to pass through the through holes on the top plate 12 and connect them to the fixing holes 1011 on the top surface 314 of the clamp 31 and the fixing holes 1017 on the top of the connecting frame 14.

[0111] See also Figure 1 The container 8 is mounted on the fixing device 9. Specifically, the outer side protrusion 8111 of the upper box body 81 of the container 8 is inserted into the second installation space 902 along the guide slider 95, so that the clamping block 97 is inserted into the locking groove 83 of the container 8. The box body stopper 98 abuts the front side of the lower box body 82 of the container 8. The front end of the upper box body 81 of the container 8 is supported by the top plate 12. The liquid nozzle 84 is connected to the liquid nozzle 18 on the bottom plate 11. The rear protrusion 8141 of the rear wall of the upper box body 81 of the container 8 abuts the top of the partition beam 93. The liquid pipe connected to the liquid nozzle 18 is passed through the through hole 9121 in the base plate 912.

[0112] Please continue reading Figure 1 , install the battery 7 in the fixture 9. Specifically, insert the two guide slots 72 of the battery 7 into the first installation space 901 of the fixture 9 along the guide surfaces 942 of the guide block 94. Continue inserting the battery 7 into the first installation space 901 along the first guide posts 941. The first guide posts 941 are made of a material with damping properties, such as rubber, to allow the battery 7 to slowly enter the first installation space 901. While inserting the battery 7, press the pressing plate 7531, causing the latch plate 7532 to move away from the battery 7. Continue inserting the battery 7 until the battery connector 71 of the battery 7 is electrically connected to the connection terminal 961 of the battery receptacle 96. The hook 7533 of the latch plate 7532 engages the coupling shaft 962, and the protrusion 73 of the battery 7 abuts the elastic support block 944 of the guide block 94. Stop pressing the pressing plate 7531.

[0113] In this embodiment, a fixing device 9 is selected to fix the battery 7 and the container 8. The battery 7 and the container 8 can be supported on the fixing frame 91 by gravity and the gravity can be used during installation, which saves more effort.

[0114] A guide block 94 is provided within the fixture 9 to guide the assembly and removal of the battery 7, enabling faster and more accurate installation of the battery 7 and improving installation efficiency. Specifically, when the battery 7 is inserted into the second installation space 902, the guide block 94 can engage with the guide groove 72 on the battery 7. The guide block 94 positions and guides the movement of the guide groove 72, thereby enabling faster and more accurate installation of the battery 7. It also acts as a limiter on the installed battery 7, ensuring a more secure installation of the battery 7.

[0115] A first guide slide 941 is provided on the fixing device 9 , and a rolling motion is formed between the first guide slide 941 and the battery 7 , thereby protecting the surface of the battery 7 .

[0116] The battery socket 96 on the fixing device 9 is arranged on the fixing frame 91, which can eliminate the electromagnetic interference effect of the large current of the battery 7 on the fuselage head module.

[0117] The battery interface 71 of the battery 7 is plugged into the battery socket 96 on the fixing device 9 in corresponding positions in the vertical direction. Therefore, the battery interface 71 and the battery socket 96 can be firmly contacted by the action of the battery 7's own gravity to achieve a stable electrical connection.

[0118] The handle 74 on the battery 7 can extend in the left-right direction, the pressing plate 7531 can be located on the rear side of the handle 74, and the snap plate 7532 can be connected below the pressing plate 7531 to open or close under the influence of the pressing plate 7531. This makes it easier to press the pressing plate 7531 while holding the handle 74, allowing for one-handed operation and more convenient operation.

[0119] When assembling the aircraft 100, one can grasp the handle 74 with one hand and place the battery 7 vertically downward. The guide groove 72 on the battery 7 moves downward along the guide block 94. The first guide slide 941 rolls against the inner wall of the guide groove 72 to slow down the descent of the battery 7. When the battery 7 is about to move downward into position, the pressing plate 7531 of the battery 7 can be slightly pressed. The snap plate 7532 can automatically open and be hooked on the snap shaft 962 to fix 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 plugged in, and the electrical connection is firm. During this operation, the gravity of the battery 7 can be effectively utilized, and the battery 7 is easy and firm to install, and the operation is labor-saving.

[0120] In this embodiment, by extending a portion of the fixing device 9 from between the top plate 12 and the bottom plate 11, it is beneficial to control the overall size and weight of the fuselage 1. By connecting the two ends of at least part of the supporting legs of the landing gear 6 to the bottom plate 11 and the fixing device 9 respectively, the structural reliability of the fixing device 9 can be improved and the deformation of the fixing device 9 due to being suspended in the air can be avoided.

[0121] In this embodiment, the 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 unit 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 planar section 302 of the through hole 316 is perpendicular to the bottom surface 315 of the clamping member 31, and the two planar 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 ring 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 unit 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, thereby providing vertical upward lift for the aircraft 100.

[0122] Of course, the aircraft 100 according to the embodiment of the present invention is not limited to the structure described in the above embodiment.

[0123] In other embodiments, the first installation space 901 can be used to install the container 8. The second installation space 902 can be used to install the battery 7. Accordingly, the guide slider 95 can be disposed on the inner side of each side plate 921 adjacent to the first installation space 901. The guide block 94 can be disposed on the inner side of each side plate 921 adjacent to the second installation space 902, and the battery socket 96 can be disposed on the partition beam 93.

[0124] In other embodiments, the partition beam 93 may 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 slides 95 may be disposed on the side plate 921 and the partition beam 93 adjacent to the first installation space 901. The guide block 94 may be disposed on the side plate 921 and the partition beam 93 adjacent to the second installation space 902. The battery socket 96 may be disposed on the end plate 922 of the mounting frame 92 adjacent to the second installation space 902.

[0125] For example, in other embodiments, the aircraft 100 can also be a six-rotor aircraft, an eight-rotor aircraft, or a larger aircraft. Correspondingly, the number of arms 2, clamping mechanisms 3, and power units of different rotorcraft will also be different. The same can be applied to the four-rotor aircraft, as long as the number of arms 2, the number of clamping mechanisms 3, and the number of power units on the aircraft 100 are the same.

[0126] For example, in some embodiments, the installation space 900 has two inner wall surfaces facing each other, and at least one of the inner wall surfaces is provided with a battery guide structure for guiding the insertion and extraction of the battery 7. The battery guide structure can be formed in various forms. The above embodiment lists a battery guide structure in the form of a guide block 94. The battery guide structure can also adopt a ball bearing structure.

[0127] In other embodiments, the shape of the through hole 316 of the clamping mechanism 3 may be adaptively changed, and the ring 39 on the arm 2 may also be adaptively changed.

[0128] In other embodiments, for example, Figure 11 In the inner circumference of the through hole 316 of the clamping mechanism 3, an acute angle is formed between at least one of the plane sections 302 and the bottom surface 315. That is, the vertical center axis of the through hole 316 forms an acute angle with the top surface 314 and the bottom surface 315 of the clamping member 31. Figure 11 In the embodiment, the vertical center axis of the through hole 316 can be at an angle of 88 degrees to the top surface 314 and the bottom surface 315 of the clamping member 31, that is, the plane section 302 of the through hole 316 is inclined at an angle of 2 degrees relative to the vertical center 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 arm 2 is inserted into the through hole 316 of the clamping mechanism 3, the center axis of the rotating shaft of the motor of the power unit can be kept at an angle of 2 degrees to the horizontal plane, that is, at an angle of 2 degrees to the plane where the bottom plate 11 of the fuselage 1 is located; by adjusting the angle between the vertical center axis of the through hole 316 and the vertical center axis of the clamping mechanism 3, the angle between the center axis of the rotating shaft of the motor and the horizontal plane can be adjusted, so as to ensure a stable and secure connection between the arm 2 and the fuselage 1 while obtaining more flight parameters of the aircraft 100. For example, when the spiral center axis of the blade connected to the arm 2 needs to have a certain angle with the vertical line to meet flight requirements, this can be achieved by adjusting the angle between the vertical center axis of the through hole 316 and the vertical center axis of the clamping mechanism 3.

[0129] 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 to 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 should not be understood as limiting the present invention.

[0130] Furthermore, 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 number of the technical features being referred to. Thus, a feature specified as "first" or "second" may explicitly or implicitly include one or more of the features. In the description of the present invention, unless otherwise specified, "plurality" means two or more.

[0131] In the description of the present invention, unless otherwise expressly specified or limited, the terms "mounted," "connected," "connected," and "fixed" should be understood in a broad sense. For example, they may refer to fixed connection, detachable connection, or integration; mechanical connection or electrical connection; direct connection or indirect connection through an intermediate medium; and internal communication between two components or interaction between two components. Those skilled in the art will understand the specific meanings of the above terms in the present invention in specific circumstances.

[0132] Throughout this specification, reference to terms such as "embodiment" or "example" indicates that the specific features, structures, materials, or characteristics described in conjunction with that embodiment or example are included in at least one embodiment or example of the present invention. In this specification, schematic representations of these 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.

[0133] 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 comprising a fuselage and a fixing device, characterized in that: The fixing device comprises: a mounting bracket for connecting to the fuselage, the mounting bracket having an installation space extending from the front end of the fuselage to the rear end of the fuselage, the installation space being located at the rear end of the fuselage or behind the fuselage, the installation space being used to install a battery and a container; the installation space including a first installation space; The mounting frame includes two opposite side plates, and a guide block is provided on the inner side of each side plate adjacent to the first mounting space; The aircraft further includes the battery, the battery including two opposing first sides and a bottom portion connected to the bottom ends of the two first sides, each first side being provided with a guide groove extending through the bottom portion of the battery; each guide block being pivotally mounted with a first guide post, the first guide post being configured to rollably abut against the guide groove; When the battery is inserted downward into the first installation space, the guide block can cooperate with the guide groove to position and guide the movement of the guide groove, and the battery interface of the battery is plugged into the battery socket on the fixing device in corresponding positions in the upper and lower directions.

2. The aircraft according to claim 1, characterized in that The guide block has an inclined guide surface on a side facing away from the side plate; the two guide grooves of the battery can be inserted into the first installation space along the guide surface.

3. The aircraft according to claim 2, characterized in that The guide surface is arranged at the top of the guide block on a side facing away from the side plate, and the thickness of the guide block increases gradually from the top to the bottom.

4. The aircraft according to claim 2, characterized in that A convex block is provided in the guide groove of the battery, a slot is provided on the guide surface, and an elastic supporting block for abutting against the convex block of the battery is provided at the bottom of the slot.

5. The aircraft according to claim 1, characterized in that A first guide slide column is pivotally mounted on the middle and bottom of the guide block on a side facing away from the side plate in a direction parallel to the side plate.

6. The aircraft according to claim 1, characterized in that The mounting frame also includes an end plate connected between the two side plates, and the battery also includes a top connected to the top ends of the two first sides. A battery interface is provided on the top of the battery, and a battery socket is installed on the end plate. The top of the battery socket is provided with a connection terminal for electrically connecting to the battery interface.

7. The aircraft according to claim 6, characterized in that The battery is provided with a latch, which includes two connecting plates arranged opposite to each other, a pivot connected between the two connecting plates and a latch portion pivotally connected to the pivot in the middle, and the latch portion has a hook; the battery socket is pivotally provided with a latch shaft around the connecting terminal; during the process of inserting the battery into the first installation space, the latch hooks on the latch shaft.

8. The aircraft according to claim 7, characterized in that The buckle portion includes a pressing plate and a buckle plate located on both sides of the pivot; the buckle plate is connected to the pressing plate in a bending manner, and the buckle plate is provided with the hook.

9. The aircraft according to claim 1, characterized in that Each of the guide blocks is pivotally mounted with the first guide slide column in a direction parallel to the side plate.

10. The aircraft according to claim 1, characterized in that The first guide slide column is a rubber column.

11. The aircraft according to claim 1, characterized in that A roller mounting groove and a through groove adjacent to the roller mounting groove are provided on the side of the guide block away from the side plate in a direction parallel to the side plate; the roller mounting groove is used to pivotally mount the first guide slide column, and the through groove is used for allowing the first guide slide column to rotate.

12. The aircraft according to claim 1, wherein: The fixing device also includes a fixing bracket connected to the rear end of the fuselage, the mounting bracket is connected to the fixing bracket, and the installation space also includes a second installation space adjacent to the first installation space, the first installation space is far away from the fixing bracket, and the second installation space is adjacent to the fixing bracket. The first installation space is used to install the battery, and the second installation space is used to install the packaging box.

13. The aircraft according to claim 12, characterized in that The fixing frame includes two opposite extension plates, which are used to be connected to the fuselage. The mounting frame also includes an end plate connected between the two side plates, and an end of each side plate away from the end plate is connected to the corresponding extension plate. The first mounting space is adjacent to the end plate, and the second mounting space is away from the end plate.

14. The aircraft according to claim 13, characterized in that It also includes a clamping mechanism, which includes a clamping member for clamping the arm of the aircraft, the clamping member is used to be connected to the fuselage, the clamping member has a side surface, the two extension plates are arranged in a V shape, and the side surface is used to be connected to the corresponding extension plate.

15. The aircraft according to claim 13, characterized in that The fixing frame further comprises a base plate for connecting to the fuselage, the two extension plates extend from opposite sides of the base plate, and the base plate is provided with a through hole for allowing a liquid pipe connected to the container to pass through.

16. The aircraft according to claim 13, characterized in that The fixing device further includes a partition beam, which is used to be connected between the two side plates, and the first installation space and the second installation space are respectively located on both sides of the partition beam.

17. The aircraft according to claim 13, characterized in that It also includes the containing 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 protrusion, the inner side of each side plate is provided with a guide sliding block adjacent to the second installation space, and the side of the guide sliding block facing away from the side plate is pivotally mounted with a second guide sliding column in a direction parallel to the side plate, and the second guide sliding column is used to slidably abut the side protrusion of the containing box.

18. The aircraft according to claim 17, characterized in that A positioning groove is provided on each second side of the upper box body, and the fixing device includes a clamping block and a limiting member for being set on the fuselage, the clamping block is used to abut the positioning groove of the container box, and the limiting member is used to abut the side of the lower box body of the container box facing the upper box body.

19. The aircraft according to claim 17, characterized in that The fixing device also includes a partition beam, which is used to connect between the two side plates. The lower box body also includes a rear wall connected to the rear ends of the two second sides. The rear wall of the lower box body is provided with a rear protrusion, and the partition beam is used to abut the rear protrusion of the lower box body.

20. The aircraft according to claim 1, wherein: The first guide column is made of a material having damping properties.

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