CN117719669A - Aircraft with a plurality of aircraft body - Google Patents

Abstract

The invention discloses an aircraft, which comprises a fuselage and a fixing device, wherein the fixing device comprises: the mounting frame is used for being connected to the fuselage, the mounting frame is provided with a mounting space which extends along the direction from the front end of the fuselage to the rear end of the fuselage, the mounting space is positioned at the rear end of the fuselage or at the rear of the fuselage, and the mounting space is used for mounting at least one of a battery and a container. According to the aircraft provided by the embodiment of the invention, the gravity center of the aircraft is close to the plane of the lifting force of the aircraft in the vertical direction, so that the aircraft can fly conveniently. At the same time, such a design also allows for the removal or insertion of items from or into the installation space of the fastening device.

Description

Aircraft with a plurality of aircraft body

The present application is a divisional application of patent application of the invention, which is filed 8/12/2016, and whose earliest priority date is 04/07/2016, and whose name is "aircraft" and whose application number is 201610663394.8.

Technical Field

The invention relates to the technical field of aircrafts, in particular to an aircraft.

Background

In the materials disclosed in the related art, when a battery and a container (such as a medicine box) on an aircraft are installed, the battery is usually arranged in a machine body, and the container is arranged below the machine body. Such a construction results in a centre of gravity of the whole aircraft being too low with respect to the plane of rotation of the propeller, which is detrimental to the flight of the aircraft.

Disclosure of Invention

The present invention aims to solve at least one of the technical problems in the related art to some extent. To this end, the invention aims to provide an aircraft with convenient flight.

An aircraft according to the invention comprises a fuselage and a fastening device, which comprises: a mounting bracket for connection to the fuselage, the mounting bracket having a mounting space extending in a direction 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;

the mounting frame comprises two opposite side plates, and a guide block is arranged on the inner side of each side plate and adjacent to the first mounting space;

the aircraft further comprises the battery, wherein the battery comprises two opposite first sides and bottoms connected to the bottom ends of the two first sides, and each first side is provided with a guide groove penetrating through the bottom of the battery;

when the battery is inserted into the first installation space downwards, the guide block can be matched with the guide groove, so that the movement of the guide groove is positioned and guided.

According to the aircraft provided by the embodiment of the invention, the installation space of the fixing device is horizontally suspended outside the aircraft body, so that the gravity center of the aircraft is close to the plane where the lift force of the aircraft is located in the vertical direction, and the aircraft can fly conveniently. At the same time, such a design also allows for the removal or insertion of items from or into the installation space of the fastening device. In addition, the guide block can play a role in positioning and guiding the movement of the guide groove in the process of inserting the battery downwards into the first installation space.

In some embodiments, a side of the guide block facing away from the side plate is provided with a guide surface which is obliquely arranged; the two guide grooves of the battery may be inserted into the first installation space along the guide surfaces.

In some embodiments, the guide surface is disposed on top of a side of the guide block facing away from the side plate, the thickness of the guide block increasing in a top-to-bottom direction.

In some embodiments, the guiding groove of the battery is provided with a bump, the guiding surface is provided with a slot, and the bottom of the slot is provided with an elastic supporting block for abutting against the bump of the battery.

In some embodiments, the middle and bottom of the side of the guide block facing away from the side plate are pivotally mounted with a first guide strut in a direction parallel to the side plate.

In some embodiments, the mounting frame further comprises an end plate connected between the two side plates, the battery further comprises a top connected to the top ends of the two first sides, a battery interface is arranged at the top of the battery, a battery socket is mounted on the end plate, and a connection terminal for being electrically connected to the battery interface is arranged at the top of the battery socket.

In some embodiments, the battery is provided with a buckle piece, the buckle piece comprises two connecting plates which are oppositely arranged, a pivot shaft connected between the two connecting plates, and a buckle part with a clamping hook, wherein the middle part of the buckle part is pivotally connected with the pivot shaft; the battery socket is pivotally provided with a clamping shaft around the connecting terminal; in the process of inserting the battery into the first installation space, the clamping hook is hooked on the clamping shaft.

In some embodiments, the catch includes a pressing plate and a catch plate on either side of the pivot; the clamping plate is connected with the pressing plate in a bending mode, and the clamping hooks are arranged on the clamping plate.

In some embodiments, each guide block is pivotally mounted with a first guide strut for slidably abutting the guide slot.

In some embodiments, each of the guide blocks is pivotally mounted with the first guide strut in a direction parallel to the side plates.

In some embodiments, the first strut is a rubber strut.

In some embodiments, a side of the guide block facing away from the side plate is provided with a roller mounting groove and a through groove adjacent to the roller mounting groove in a direction parallel to the side plate; the roller mounting groove is used for pivotally mounting the first guide strut, and the penetrating groove is used for enabling the first guide strut to rotate.

In some embodiments, the fixing device further comprises a fixing frame connected to the rear end of the body, the mounting frame is connected to the fixing frame, the mounting space further comprises a second mounting space adjacent to the first mounting space, the first mounting space is far away from the fixing frame, the second mounting space is adjacent to the fixing frame, the first mounting space is used for mounting the battery, and the second mounting space is used for mounting the containing box.

In some embodiments, the mount includes two opposing extension plates for connection to the fuselage, the mount further includes an end plate connected between the two side plates, one end of each side plate distal 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 distal from the end plate.

In some embodiments, the two extension plates are arranged in a V-shape, the aircraft further comprising a clamping mechanism comprising a clamping member for clamping the horn of the aircraft, the clamping member being for connection to the fuselage, the clamping member having a side for connection to a corresponding extension plate.

In some embodiments, the fixing frame further comprises a base plate connected to the machine body, the two extending plates extend from two opposite sides of the base plate, and a through hole for a liquid pipe connected to the containing box to pass through is formed in the base plate.

In some embodiments, the fixing device further comprises a spacer for connecting between the two side plates, and the first installation space and the second installation space are respectively located at two sides of the spacer.

In some embodiments, the aircraft further comprises the container, the container comprises an upper case and a lower case vertically connected to the bottom of the upper case, the upper case comprises two opposite second sides, each second side of the upper case is provided with a side bump, the inner side of each side plate is provided with a guide slide block adjacent to the second installation space, one side of the guide slide block facing away from the side plate is pivotally provided with a second guide slide column along a direction parallel to the side plate, and the second guide slide column is used for being in sliding abutting connection with the side bumps of the container.

In some embodiments, each second side of the upper case is provided with a clamping groove, and the fixing device comprises a clamping block and a limiting piece, wherein the clamping block is used for being abutted to the clamping groove of the containing case, and the limiting piece is used for being abutted to one side, facing the upper case, of the lower case of the containing case.

In some embodiments, the lower case further includes a rear wall connected to rear ends of the two second sides, the rear wall of the lower case is provided with a rear projection, and the spacer is configured to abut the rear projection of the lower case.

An aircraft according to the invention comprises: a body; the fixing device according to the invention; a battery; and a containing box.

Additional aspects and advantages of the invention will be set forth in part in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention.

Drawings

The foregoing and/or additional aspects and advantages of the invention will become apparent and may be better understood from the following description of embodiments taken in conjunction with the accompanying drawings in which:

FIG. 1 is a perspective assembly view of an aircraft according to an embodiment of the invention;

FIG. 2 is a top view of the aircraft of FIG. 1 (with the battery, container and fuselage roof removed);

FIG. 3 is an enlarged view of the horn of FIG. 2 in an assembled state with the clip at the second collar;

FIG. 4 is a perspective assembly view of the horn and collar of FIG. 2;

FIG. 5 is a perspective view of the first collar of FIG. 4;

FIG. 6 is a side view of the first collar of FIG. 5;

FIG. 7 is a perspective view of the second collar of FIG. 4;

FIG. 8 is a side view of the clamp of FIG. 2;

FIG. 9 is a perspective view of the clamp of FIG. 8;

FIG. 10 is a perspective view of the compression block of FIG. 2;

FIG. 11 is a side view of a clamp according to another embodiment of the invention;

FIG. 12 is a perspective view of the mount of FIG. 2;

FIG. 13 is a perspective view of the fitting of FIG. 2;

FIG. 14 is a perspective assembly view of the aircraft of FIG. 1 (with the storage bin, horn, power plant and battery removed);

FIG. 15 is a perspective assembly view of the aircraft (with the storage bin and battery removed) according to FIG. 1;

FIG. 16 is a bottom view of the aircraft of FIG. 14 (with the carrying case, horn, power plant, and battery removed);

FIG. 17 is a perspective view of the fixture of FIG. 14;

FIG. 18 is a perspective view of the case limiter of FIG. 14;

fig. 19 is a perspective view of the battery receptacle of fig. 17;

FIG. 20 is a perspective view of the guide block of FIG. 17;

FIG. 21 is a side view of the guide block of FIG. 17;

FIG. 22 is a perspective view of the clamp block of FIG. 15;

FIG. 23 is a perspective view of the guide shoe according to FIG. 17;

fig. 24 is a perspective view of the battery of fig. 1;

fig. 25 is a side view of a battery and a fixture in an assembled state according to an embodiment of the present invention;

FIG. 26 is a cross-sectional view taken along the direction A-A in FIG. 25;

FIG. 27 is a perspective view of the container according to FIG. 1;

fig. 28 is a perspective view of the landing gear according to fig. 1.

Reference numerals:

aircraft 100,

Fixing hole 1011, fixing hole 1012, fixing hole 1013, fixing hole 1014, fixing hole 1015, fixing hole 1016, fixing hole 1017,

Perforations 1021, 1023, 1024, 1025, 1026,

Fastener 1031, fastener 1032, fastener 1033, fastener 1034, fastener 1035, fastener 1036, fastener 1037, fastener 1038, and fastener,

A positioning hole 104,

Fuselage 1, bottom plate 11, roof 12, link 14, first frame 141, second frame 142, via hole 17, liquid nozzle 18, horn 2, rod 21,

Clamping mechanism 3, arc segment 301, planar segment 302, transition segment 303, clamping piece 31, first surface 311, second surface 312, side 313, top surface 314, bottom surface 315, through hole 316, mounting slot 317, positioning boss 318, boss 319, compression block 32, locking portion 321, connecting portion 322, holding surface 323, fixing piece 33, base 331, holding portion 332, first holding surface 333, mating piece 34, second holding surface 341, collar 39, arc segment 3901, planar segment 3902, transition segment 3903, glue receiving slot 3904, first collar 39, second collar 392, stop block 3921, and,

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

Battery 7, first side 703, bottom 702, top 701, rear side 704, battery tab 71, guide slot 72, tab 73, handle 74, clasp 75, connection plate 751, pivot 752, clasp 753, push plate 7531, clasp plate 7532, clasp 7533, and,

Containing box 8, upper box 81, second side 811, side projection 8111, detent 8112, bottom wall 812, top wall 813, rear wall 814, rear projection 8141, lower box 82, spout 84, handle 86, ventilation opening 87,

The fixing device 9, the installation space 900, the first installation space 901, the second installation space 902, the fixing frame 91, the extension plate 911, the base plate 912, the through hole 9121, the installation frame 92, the side plate 921, the end plate 922, the spacer beam 93, the guide block 94, the first guide strut 941, the guide surface 942, the slot 943, the elastic support block 944, the roller installation groove 945, the through slot 946, the guide slide 95, the second guide strut 951, the battery socket 96, the connection terminal 961, the clamping shaft 962, the clamping block 97, the elastic reinforcing hole 971, the case stopper 98, the stopper 981, the connection 982, and the reinforcing rib 983.

Detailed Description

Embodiments of the present invention are described in detail below, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to like or similar elements or elements having like or similar functions throughout. The embodiments described below by referring to the drawings are illustrative and intended to explain the present invention and should not be construed as limiting the invention.

An aircraft 100 according to an embodiment of the invention is described below with reference to fig. 1-28, the aircraft 100 comprising a fuselage 1 and a fixing device 9, the fixing device 9 being for fixing at least one of a battery 7 of the aircraft 100 and a holding tank 8, the holding tank 8 being adapted to hold items to be sprayed or transported.

As shown in fig. 14, 15 and 17, the fixing device 9 includes: a mounting frame 92 for connection to the body 1, the mounting frame 92 having a mounting space 900 extending in a direction from a front end of the body 1 to a rear end of the body 1, the mounting space 900 being located at the rear end of the body 1 or at the rear of the body 1, the mounting space 900 being for mounting at least one of the battery 7 and the container 8.

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 made to be close to the plane of the lift of the aircraft 100 in the vertical direction, so that the aircraft 100 can fly advantageously. At the same time, such a design also allows for the removal or insertion of items from or into the installation space 900 of the fastening device 9.

For ease of understanding, an aircraft 100 in accordance with an embodiment of the present invention is described below in connection with FIGS. 1-28.

As shown in fig. 1 and 2, the aircraft 100 comprises a fuselage 1, landing gear 6, a horn 2, a clamping mechanism 3, a power unit and a fastening device 9. As shown in fig. 1, 24-27, the aircraft 100 further comprises a battery 7 and a container 8, the container 8 being adapted to contain items to be sprayed or transported. In this embodiment, the aircraft 100 is a quad-rotor aircraft, and the number of the horn 2 and the number of the power devices are four.

Referring to fig. 1, 14 and 15, the body 1 includes a bottom plate 11 and a top plate 12 disposed opposite to each other in the up-down direction, and a connecting frame 14 connected to the bottom plate 11, and as shown in fig. 16, the bottom plate 11 is provided with positioning holes 104 and perforations 1021.

As shown in fig. 14 and 15, a through hole 17 is further formed on one side of the bottom plate 11 adjacent to the bottom plate, and a liquid nozzle 18 is formed on the through hole 17. The top plate 12 is provided with perforations.

Referring to fig. 14, the connecting frame 14 includes a first frame 141 and a second frame 142 vertically connected to the first frame 141. The bottom of the second frame 142 and the bottom of the first frame 141 are connected to the bottom plate 11 of the body 1 by fasteners 1032 (shown in fig. 16) such as screws, and fixing holes 1017 are provided at the top of the second frame 142 and the first frame 141.

As shown in fig. 14 and 17, the fixing device 9 is connected to the connection frame 14. As shown in fig. 17 to 23, 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 separation beam 93 connected to the mounting frame 92. As shown in fig. 15, the fixing device 9 further includes a clamping block 97 and a box limiter 98. The fixing frame 91 and the mounting frame 92 may be integrally formed.

The fixing frame 91 includes a base plate 912 and two extending plates 911 extending obliquely from opposite sides of the base plate 912. The base plate 912 is secured to an end of the first frame 141 remote from the second frame 142 by fasteners, such as screws. The substrate 912 is provided with a via 9121. The two extending plates 911 are V-shaped, and each extending plate 911 is provided with a through hole 1023.

The mounting frame 92 includes two opposite side plates 921 and an end plate 922 connected to the two side plates 921. One end of each side plate 921, remote from the end plate 922, is connected to a corresponding extension plate 911. The side plate 921 is provided with a through hole 1024. The mounting frame 92 has a mounting space 900, and the spacer 93 is connected between the side plates 921 to partition the mounting space 900 into a first mounting space 901 and a second mounting space 902.

Referring to fig. 17 and fig. 20-23, a guide block 94 is disposed on the inner side of each side plate 921 adjacent to the first mounting space 901. The top of the side of the guide block 94 facing away from the side plate 921 has a guide surface 942. The guide surface 942 is inclined such that the thickness of the guide block 94 increases in a top-to-bottom direction. The guiding surface 942 is provided with a slot 943, and the bottom of the slot 943 is provided with an elastic supporting block 944. The middle and bottom of the side of the guide block 94 facing away from the side plate 921 are provided with a roller mounting groove 945 and a through groove 946 adjacent to the roller mounting groove 945 in a direction parallel to the side plate 921. The roller mounting groove 945 is used to pivotally mount the first guide strut 941. The two through slots 946 are used for the first slide guiding column 941 to rotate. The material of the first strut 941 is a material having damping characteristics such as rubber.

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

The inner side of the end plate 922 is provided with a battery receptacle 96. The top of the battery receptacle 96 is provided with a connection terminal 961. The battery receptacle 96 is pivotally provided with a locking shaft 962 around the connection terminal 961. The snap-in shaft 962 is parallel to and adjacent to the end plate 922.

As shown in fig. 15 and 22, the clamping block 97 is disposed on the top plate 12, and an elastic reinforcing hole 971 is provided on the clamping block 97.

As shown in fig. 15 and 18, the case stopper 98 is provided on the base plate 11. The box body limiting member 98 includes a limiting portion 981, a connecting portion 982 extending from a middle portion of the limiting portion 981, and a reinforcing rib 983 connected between a lower portion of one side of the limiting portion 981 and the connecting portion 982. The connection portion 982 is attached to the lower surface of the base plate 11 by fasteners 1033, such as screws.

As shown in fig. 24 to 26, the battery 7 has a substantially rectangular parallelepiped shape. The battery 7 includes two opposite first sides 703, a bottom 702 connected to bottom ends of the two first sides 703, a top 701 connected to top ends of the two first sides 703, and a rear side 704 connected to rear ends of the two first sides 703. The top of the rear side 704 of the battery 7 is provided with a catch 75 and a battery interface 71 adjacent to the catch 75. The catching member 75 includes two connection plates 751 disposed opposite to each other, a pivot 752 connected between the connection plates 751, and a catching portion 753 having a middle portion pivotally connected to the pivot 752. The catching part 753 includes a pressing plate 7531 and a catching plate 7532 at both sides of the pivot 752. The buckle plate 7532 is connected to the pressing plate 7531 in a bending manner. The fastening plate 7532 is provided with a fastening hook 7533. The two first sides 703 of the battery 7 are respectively provided with two guide grooves 72 penetrating the bottom of the battery 7. The top wall of each guide groove 72 is provided with a projection 73 downward. A handle 74 is arranged at the top of the battery 7.

As shown in fig. 27, the holding case 8 includes an upper case 81 and a lower case 82 connected substantially vertically to the bottom of the upper case 81. The lower case 82 and the upper case 81 are substantially rectangular parallelepiped. The upper case 81 includes opposite second sides 811, a bottom wall 812 connected to bottom ends of the second sides, a top wall 813 connected to top ends of the second sides, and a rear wall 814 connected to rear ends of the second sides. The bottom wall 812 of the upper housing 81 is provided with a spout 84 adjacent the lower housing 82. Each second side 811 of the upper case 81 is provided with a side protrusion 8111 and a locking groove 8112. The rear wall 814 of the upper case 81 is provided with a rear protrusion 8141. The top wall 812 of the upper case 81 is provided with a handle 86 and an air vent 87.

As shown in fig. 16 and 28, the landing gear 6 includes two support legs 60. Each support leg 60 includes a bottom support leg 603 and front and rear support legs 601 and 602 extending from both sides of the bottom support leg 603. The end of the front support leg 601 remote from the bottom support leg 603 is provided with a horizontal connection 611. As shown in fig. 16, the horizontal connection 611 is connected to the bottom plate 11 of the body 1 by a fastener 1034 (e.g., a screw). The end of the rear support leg 602 remote from the bottom support leg 603 is provided with a vertical connection 612. As shown in fig. 15, the vertical connection 612 is connected to the end plate 922 and the corresponding side plate 921 of the fixing device 9 by fasteners 1035 (e.g., screws).

As shown in fig. 2, the arm 2 is cylindrical, and one end of the arm is provided with a corresponding power device. The power plant is capable of powering the aircraft 100.

Referring to fig. 2 and 8-13, the clamping mechanism 3 includes two first clamping mechanisms and two second clamping mechanisms. Each first clamping mechanism comprises two clamping members 31, two pressing blocks 32, a fixing member 33, a matching member 34 and a collar 39. Each second clamping mechanism comprises two clamping members 31, two compression blocks 32 and a collar 39.

As shown in fig. 8 and 9, each clip 31 has opposite first and second surfaces 311 and 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. The clamping member 31 is provided with a through hole 316 penetrating 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 mass of the clamping member 31. The inner circumferential surface of the through hole 316 includes two arc sections 301 disposed opposite to each other, two plane sections 302 disposed between the two arc sections 301 and disposed opposite to each other in parallel, and two transition sections 303 disposed between the two arc sections 301 and the two plane sections 302 and disposed opposite to each other, where each plane section 302 is perpendicular to the bottom surface 315 of the clamping member 31, each transition section 303 may be formed by a plurality of facets, and each transition section 303 may also be formed by an arc surface. The clamping member 32 is further provided with a mounting groove 317 penetrating the top surface 314 and the circular arc section 301 adjacent to the top surface 314, and the mounting groove 317 is communicated with the through hole 316. Two fixing holes 1011 are provided at two ends of the top surface 314 adjacent to the mounting groove 317. The inner surface of the clamping member 31 extends toward the center of the through hole 316 near the connection between the mounting groove 317 and the through hole 316, and each boss 319 is provided with a fixing hole. The bottom surface 315 is provided with two positioning posts 318 and two fixing holes facing away from the top surface 314. One side 313 of the two side 313 is provided with a fixing hole 1012.

Each pressing block 32 comprises a locking portion 321 and two connecting portions 322 located on two sides of the locking portion 321, and 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.

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

One side of the mating member 34 is recessed inward to form a second clamping surface 341, and two fixing holes 1016 are formed at two ends of the mating member 34 adjacent to the second clamping surface 341.

Referring to fig. 4-7, each collar 39 includes a first collar 391 and a second collar 392.

The outer surface of the first collar 391 includes two opposite arc segments 3901, two opposite and parallel plane segments 3902 between the two arc segments 3901, and two opposite transition segments 3903 between the two arc segments 3901 and the two plane segments 3902. The inner surface of the first collar 391 is provided with a glue groove 3904.

An end of the second collar 392 extends outward to form a stop 3921. The outer surface of the second collar 392 includes two opposite circular arc segments 3901, two opposite parallel plane segments 3902 between the two circular arc segments 3901, and two opposite transition segments 3903 between the two circular arc segments 3901 and the two plane segments 3902. The inner surface of the second collar 392 is provided with a glue groove 3904.

In assembly, part of the components of the clamping mechanism 3 are first fixed to the base plate 11 of the fuselage 1. In the following, an installation process of one first clamping mechanism with the bottom plate 11 of the body 1 will be described as an example.

Referring to fig. 14, the two clamping members 31 and the fixing member 33 are fixed to the base plate 11. Specifically, the bottom surface 315 of each clip 31 is in contact with 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. Two fasteners 1036 (referring to screws at fig. 16) are respectively inserted through corresponding two through holes 1021 in the base plate 11 and connected to corresponding two fixing holes in the bottom surface 315 of the clip 31. Two fasteners 1038 (referring to screws in fig. 16) are inserted through corresponding two bores 1021 in the base plate 11 and attached to the attachment holes 1014 in the bottom of the base 331 of the attachment member 33.

The two clamping pieces 31 and the fixing piece 33 are connected to the fixing device 9, so that the fixing frame 91 of the fixing device 9 is connected to the rear end of the bottom plate 11 of the body 1, and further, the installation space 900 of the installation frame 92 of the fixing device 9 is located at the rear end of the body 1 or at the rear of the body 1, and the installation space 900 extends from the front end of the body 1 to the rear end of the body 1. Specifically, fasteners such as screws are inserted through the through holes 1023 of the extension plate 911 of the fixing frame 91 of the fixing device 9 and are coupled to the fixing holes 1013 of the side 313 of the corresponding clamp 31. Fasteners, such as screws, are passed through the perforations 1024 of the side plates 921 of the mounting bracket 92 of the fixture 9 and attached to the attachment holes 1014 on the side of the base 331 of the fixture 33 remote from the catch 332.

Thereby, the clamping mechanism 3 is fixed to the bottom plate 11 of the body 1.

Referring to fig. 2-4, the arm 2 is mounted to the clamping mechanism 3. Next, the mounting process of one horn 2 and one first clamping mechanism will be described.

The collar 39 is sleeved on the horn 2. Specifically, the first collar 391 and the second collar 392 are respectively fitted over the arm 2. By dispensing glue in the glue receiving groove 3904 of the first collar 391 and the glue receiving groove 3904 of the second collar 392, the connection strength between the first collar 391 and the second collar 392 and the arm 2 is enhanced.

The arm 2 is mounted between the two clamping members 31 and the two pressing blocks 32. Specifically, the assembled horn 2 is passed through the two clamps 31 until the stop block 3921 of the second collar 392 is stopped against the surface of the clamp 31 away from the center of the base plate 11. The pressing blocks 32 are fitted into the mounting grooves 317 of the respective holders 31. Fasteners such as screws are inserted through the through holes 1025 of the two connection portions 322 of the pressing block 32, and are connected to the fixing holes of the two bosses 319 of the clamping member 31.

The horn 2 is mounted between the fixing member 33 and the mating member 34. Specifically, a fastener such as a screw is inserted through the aperture 1026 of the catch 332 of the securing member 33 and attached to the securing aperture 1016 of the mating member 34.

Thereby, the horn 2 is attached to the clamping mechanism 3.

Referring to fig. 15, the top plate 12 is connected to the bottom plate 11. Specifically, the top plate 12 is placed above the bottom plate 11, and the fastening members 1031, 1037 (such as screws) are inserted through the through holes in the top plate 12, and are connected to the fixing holes 1011 in the top surface 314 of the clamping member 31 and the fixing holes 1017 in the top of the connecting frame 14.

Referring to fig. 1, the container 8 is mounted to the fixing device 9. Specifically, the lateral protruding block 8111 on the outer side of the upper case 81 of the containing case 8 is inserted into the second installation space 902 along the guide sliding block 95, so that the clamping block 97 is inserted into the clamping groove 83 of the containing case 8, the case limiting member 98 abuts against the front side of the lower case 82 of the containing case 8, the front end of the upper case 81 of the containing case 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 protruding block 8141 on the rear wall of the upper case 81 of the containing case 8 abuts against the top of the separation beam 93. A liquid tube connected to the liquid nozzle 18 is passed through the via 9121 on the substrate 912.

With continued reference to fig. 1, the battery 7 is mounted to the fixture 9. Specifically, the two guide grooves 72 of the battery 7 are inserted into the first installation space 901 of the fixing device 9 along the guide surfaces 942 of the guide blocks 94, and then are continuously inserted into the first installation space 901 along the first guide strut 941, and the material of the first guide strut 941 is a material having damping characteristics such as rubber, so that the battery 7 slowly enters the first installation space 901. When the battery 7 is inserted, the pressing plate 7531 is pressed, so that the click plate 7532 moves in a direction away from the battery 7. The battery 7 is further inserted, 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 fastening plate 7532 is hooked on the fastening shaft 962, and the bump 73 of the battery 7 abuts against the elastic supporting block 944 of the guiding block 94. Pressing the pressing plate 7531 is stopped.

In this embodiment, the fixing device 9 is selected to fix the battery 7 and the containing box 8, and the battery 7 and the containing box 8 can be supported on the fixing frame 91 by gravity and can be operated with more effort in installation.

The guide block 94 is arranged in the fixing device 9, so that the battery 7 can be guided to be disassembled and assembled, the battery 7 can be installed more quickly and accurately, and the installation efficiency is improved. Specifically, when the battery 7 is inserted into the second installation space 902, the guide block 94 may be matched with the guide groove 72 on the battery 7, and the guide block 94 plays a role in positioning and guiding the movement of the guide groove 72, so that the installation of the battery 7 is quicker and more accurate, and meanwhile, the battery 7 installed in place may also have a limiting effect, so that the installation of the battery 7 is more firm.

The fixing device 9 is provided with a first guide slide column 941, rolling motion is formed between the first guide slide column 941 and the battery 7, and a protection effect is formed on the surface of the battery 7.

The battery socket 96 on the fixing device 9 is arranged on the fixing frame 91, so that the electromagnetic interference influence of the large current of the battery 7 on the head module of the machine body can be removed.

The battery interface 71 of the battery 7 is correspondingly inserted into the battery socket 96 of the fixing device 9 in the vertical direction, so that the battery interface 71 and the battery socket 96 can be firmly contacted under the action of the gravity of the battery 7, and stable electric connection is realized.

The handle 74 on the battery 7 can extend along the left-right direction, the pressing plate 7531 can be located at the rear side of the handle 74, and the buckling plate 7532 can be connected below the pressing plate 7531 so as to be opened or closed under the driving of the pressing plate 7531. Therefore, the pressing of the pressing plate 7531 is more convenient to realize when the handle 74 is held, single-hand operation can be realized, and the operation is more convenient.

When the aircraft 100 is assembled, the lifting handle 74 can be grasped by one hand, the battery 7 is placed vertically downwards, the guide groove 72 on the battery 7 moves downwards along the guide block 94, the first guide slide column 941 rolls tightly against the inner wall surface of the guide groove 72, the purpose of slowing down the descending speed of the battery 7 is achieved, when the battery 7 moves downwards in place, the pressing plate 7531 of the battery 7 can be slightly pressed, the buckling plate 7532 can be automatically opened and is hung on the clamping shaft 962, the effect of fixing the battery 7 is achieved, at the moment, the battery connector 71 of the battery 7 and the connecting terminal 961 of the battery socket 96 can be spliced, and the electric connection is firm. In the operation process, the gravity of the battery 7 can be effectively utilized, the battery 7 is convenient and firm to install, and the operation is labor-saving.

In this embodiment, by extending a portion of the fixing device 9 from between the top plate 12 and the bottom plate 11, which is advantageous for controlling the overall size and weight of the fuselage 1, and connecting the bottom plate 11 and the fixing device 9 to both ends of at least a portion of the supporting leg of the landing gear 6, respectively, the structural reliability of the fixing device 9 can be improved, and deformation of the fixing device 9 due to suspension can be avoided.

In the embodiment, the clamping mechanism 3 is adopted to clamp the horn 2 on the machine body 1, so that on one hand, the assembly process of the horn 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 firm, because the plane sections 302 of the through holes 316 are perpendicular to the bottom surface 315 of the clamping piece 31, the two plane sections 302 are perpendicular to the top surface 314 and the bottom surface 315 of the clamping piece 31, the outer circumferential surface of the collar 39 is adapted to the shape of the through holes 316 of the clamping mechanism 3, and when the arm 2 is inserted into the through holes 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, namely perpendicular to the plane of the bottom plate 11 of the fuselage 1, so as to provide vertical upward lifting force for the aircraft 100.

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

In other embodiments, the first installation space 901 may be used to install the carrying case 8. The second installation space 902 may be used to install the battery 7. Correspondingly, the guide slider 95 may be disposed inside each side plate 921 adjacent to the first mounting space 901. The guide blocks 94 may be disposed inside each side plate 921 adjacent to the second mounting space 902, and the battery sockets 96 may be disposed on the barrier beams 93.

In other embodiments, the spacer 93 may be connected between the base 912 of the mount 91 and the end plate 922 of the mount 92. The two guide sliders 95 may be disposed at a side plate 921 adjacent to one side of the first installation space 901 and the spacer beam 93. The guide block 94 may be disposed adjacent to the side plate 921 of the second installation space 902 and the spacer 93. The battery receptacle 96 may be disposed on the end plate 922 of the mounting bracket 92 adjacent the second mounting space 902.

For example, in other embodiments, the aircraft 100 may be a six-rotor aircraft, an eight-rotor aircraft, or a more aircraft, and correspondingly, the number of arms 2, gripping mechanisms 3, and power devices of different rotor aircraft may be different, and so on, in accordance with a four-rotor aircraft, so long as the same number of arms 2, gripping mechanisms 3, and power devices on the aircraft 100 is ensured.

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 guide structure for guiding the insertion and withdrawal of the battery 7. The battery guide structure may be formed in various ways, and one of the battery guide structures in the form of the guide blocks 94 is listed in the above embodiment, and the battery guide structure may also be a ball structure.

In other embodiments, the shape of the through hole 316 of the clamping mechanism 3 may be adapted, as may the collar 39 on the horn 2.

In other embodiments, for example, as shown in fig. 11, an acute angle is formed between at least one of the planar segments 302 and the bottom surface 315 in the inner peripheral surface of the through hole 316 of the clamping mechanism 3. I.e. the vertical central axis of the through hole 316 is at an acute angle to the top surface 314 and the bottom surface 315 of the holder 31. As shown in fig. 11, the vertical central axis of the through hole 316 may form an angle of 88 degrees with 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 by 2 degrees with respect to the vertical central axis of the clamping mechanism 3, and since the outer circumferential 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 may be kept at an angle of 2 degrees with respect to the horizontal plane, that is, at an angle of 2 degrees with respect to the plane on which the bottom plate 11 of the body 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 to adjust the angle between the central axis of the rotating shaft of the motor and the horizontal plane, the connection between the horn 2 and the fuselage 1 can be ensured to be stable and firm, and more flight parameters of the aircraft 100 can be obtained. For example, when the central axis of the blade screw connected to the horn 2 needs to have a certain angle with the vertical line in order to meet the flight requirement, this can be accomplished by adjusting the angle between the central vertical axis of the through hole 316 and the central vertical axis of the clamping mechanism 3.

In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings are merely for convenience in describing the present invention and simplifying the description, and do not indicate or imply that the device or element being referred to must have a specific orientation, be configured and operated in a specific orientation, and therefore should not be construed as limiting the present invention.

Furthermore, the terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include one or more such feature. In the description of the present invention, unless otherwise indicated, the meaning of "a plurality" is two or more.

In the description of the present invention, unless explicitly stated and limited otherwise, the terms "mounted," "connected," and "secured" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally formed; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communicated with the inside of two elements or the interaction relationship of the two elements. The specific meaning of the above terms in the present invention will be understood in specific cases by those of ordinary skill in the art.

In the description herein, reference to the term "embodiment," "example," etc., means that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the invention. In this specification, schematic representations of the above terms do not necessarily refer to the same embodiments or examples. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.

While embodiments of the present invention have been shown and described, it will be understood by those of ordinary skill in the art that: many changes, modifications, substitutions and variations may be made to the embodiments without departing from the spirit and principles of the invention, the scope of which is defined by the claims and their equivalents.

Claims (20)

1. An aircraft comprising a fuselage and a fixture, wherein the fixture comprises:

a mounting bracket for connection to the fuselage, the mounting bracket having a mounting space extending in a direction 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;

the mounting frame comprises two opposite side plates, and a guide block is arranged on the inner side of each side plate and adjacent to the first mounting space;

the aircraft further comprises the battery, wherein the battery comprises two opposite first sides and bottoms connected to the bottom ends of the two first sides, and each first side is provided with a guide groove penetrating through the bottom of the battery;

when the battery is inserted into the first installation space downwards, the guide block can be matched with the guide groove, so that the movement of the guide groove is positioned and guided.

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

3. The aircraft of claim 2, wherein the guide surface is disposed on top of a side of the guide block facing away from the side panel, the guide block having a thickness that increases in a top-to-bottom direction.

4. The aircraft according to claim 2, wherein the battery is provided with a projection in the guide groove, the guide surface is provided with a slot, and the bottom of the slot is provided with an elastic support block for abutting against the projection of the battery.

5. The aircraft according to claim 1, characterized in that the middle and bottom of the side of the guide block facing away from the side plate are pivotally mounted with a first guide strut in a direction parallel to the side plate.

6. The aircraft of claim 1 wherein the mounting further comprises an end plate connected between the side plates, the battery further comprises a top connected to the top ends of the two first sides, the top of the battery is provided with a battery interface, the end plate is provided with a battery socket, and the top of the battery socket is provided with a connection terminal for electrically connecting to the battery interface.

7. The aircraft of claim 6, wherein the battery is provided with a snap-fit element comprising two oppositely disposed connection plates, a pivot connected between the connection plates, and a snap-fit portion pivotally connected to the pivot at a middle portion thereof, the snap-fit portion having a catch; the battery socket is pivotally provided with a clamping shaft around the connecting terminal; in the process of inserting the battery into the first installation space, the clamping hook is hooked on the clamping shaft.

8. The aircraft of claim 7, wherein the catch includes a push plate and a catch plate on either side of the pivot; the clamping plate is connected with the pressing plate in a bending mode, and the clamping hooks are arranged on the clamping plate.

9. The aircraft of claim 1, wherein each guide block is pivotally mounted with a first guide strut for slidably abutting the guide slot.

10. The vehicle of claim 9, wherein each of the guide blocks is pivotally mounted with the first guide strut in a direction parallel to the side panels.

11. The aircraft of claim 9, wherein the first runner is a rubber strut.

12. The aircraft according to claim 1, characterized in that a side of the guide block facing away from the side plate is provided with a roller mounting groove and a through groove adjacent to the roller mounting groove in a direction parallel to the side plate; the roller mounting groove is used for pivotally mounting the first guide strut, and the penetrating groove is used for enabling the first guide strut to rotate.

13. The aircraft of claim 1, wherein the fixture further comprises a mount attached to the rear end of the fuselage, the mount being attached to the mount, the mounting space further comprising a second mounting space adjacent the first mounting space, the first mounting space being remote from the mount, the second mounting space being adjacent the mount, the first mounting space being for mounting the battery, the second mounting space being for mounting the carrying case.

14. The aircraft of claim 13 wherein the mount includes two opposing extension panels for connection to the fuselage, the mount further including an end panel connected between the two side panels, an end of each side panel remote from the end panel being connected to the corresponding extension panel, the first mounting space being adjacent the end panel and the second mounting space being remote from the end panel.

15. The aircraft of claim 14 further comprising a clamping mechanism including a clamp for clamping a horn of the aircraft, the clamp for attachment to the fuselage, the clamp having sides, the two extension panels being arranged in a V-shape, the sides for attachment to corresponding extension panels.

16. The vehicle of claim 14, wherein the mounting bracket further comprises a base plate for attachment to the fuselage, the two extension plates extending from opposite sides of the base plate, the base plate having a through hole for a liquid tube attached to the container to pass through.

17. The aircraft of claim 14, wherein the securing device further comprises a bulkhead for connection between the two side panels, the first and second mounting spaces being located on respective sides of the bulkhead.

18. The aircraft of claim 14 further comprising the stowage bin including an upper bin and a lower bin vertically connected to a bottom of the upper bin, the upper bin including opposite second sides, each second side of the upper bin being provided with a side tab, an inner side of each side panel being provided with a guide slide adjacent the second mounting space, a side of the guide slide facing away from the side panel pivotally mounted with a second guide strut in a direction parallel to the side panel, the second guide strut for slidably abutting the side tab of the stowage bin.

19. The aircraft of claim 18, wherein each second side of the upper case is provided with a detent, and the fixing device comprises a clamping block and a limiting member, wherein the clamping block is used for being abutted against the detent of the containing case, and the limiting member is used for being abutted against one side of the lower case of the containing case, which faces the upper case.

20. The vehicle of claim 18, wherein the lower housing further comprises a rear wall connected to the rear ends of the second sides, the rear wall of the lower housing being provided with rear lugs, the spacer being adapted to abut the rear lugs of the lower housing.