CN219832895U

CN219832895U - Quick detach battery fixed latch device and unmanned aerial vehicle

Info

Publication number: CN219832895U
Application number: CN202321256332.7U
Authority: CN
Inventors: 范欣林; 田刚印
Original assignee: Shenzhen Lianhe Airplane Technology Co ltd
Current assignee: Shenzhen Lianhe Airplane Technology Co ltd
Priority date: 2023-05-23
Filing date: 2023-05-23
Publication date: 2023-10-13
Anticipated expiration: 2033-05-23

Abstract

The utility model relates to a quick-release battery fixing locking device and an unmanned aerial vehicle, belongs to the technical field of unmanned aerial vehicle battery installation, and solves the problems of inconvenient battery disassembly and assembly and poor battery installation stability of the existing unmanned aerial vehicle. According to the unmanned aerial vehicle, two battery clamping grooves are formed in two sides of a partition board of an unmanned aerial vehicle body; the battery module is slidably arranged in the battery clamping groove; a battery connector is arranged on the front end face; the battery module is spliced with the battery connector; a battery lock catch module is arranged on the end face of the partition board; the battery lock catch module includes: a knob and a fixing member; the fixing piece is fixedly arranged on the partition board, and the knob is rotationally connected with the fixing piece; can block battery module when knob perpendicular to mounting, restrict battery module and unmanned aerial vehicle organism's relative slip. The utility model realizes the rapid assembly of the battery and the unmanned aerial vehicle body and can ensure the reliability of battery installation.

Description

Quick detach battery fixed latch device and unmanned aerial vehicle

Technical Field

The utility model relates to the technical field of unmanned aerial vehicle battery installation, in particular to a quick-release battery fixing locking device and an unmanned aerial vehicle.

Background

With the continuous development of scientific technology, unmanned aerial vehicle technology has been greatly improved in recent years, and many intelligent multifunctional unmanned aerial vehicles appear, and batteries are indispensable parts of unmanned aerial vehicles, and battery loading and unloading convenience and stability are particularly important.

The current common battery mounting design is to use two elastic hooks on the battery to hook on the unmanned aerial vehicle.

The existing battery fixing structure has the defects that the battery is inconvenient to take out, the battery can not be judged to be installed in place during installation, when the unmanned aerial vehicle flies and vibrates, the elastic hook is easy to separate when receiving impact force, the connection of the battery and the unmanned aerial vehicle is loose, power failure and ignition are caused, and the like, the stability of the unmanned aerial vehicle is greatly influenced, and meanwhile the safety performance of the unmanned aerial vehicle is influenced.

Therefore, in order to improve reliability of battery fixing, convenience of battery assembly and disassembly, in-place accuracy of battery installation, and safety during flight, it is necessary to provide a new battery fixing device.

Disclosure of Invention

In view of the above analysis, the present utility model aims to provide a quick-release battery fixing and locking device and an unmanned aerial vehicle, which are used for solving the problems of inconvenient battery disassembly and poor battery installation stability of the existing unmanned aerial vehicle.

The aim of the utility model is mainly realized by the following technical scheme:

a quick release battery securing latch apparatus comprising: the device comprises a knob, a knob screw, a fixing piece and a nut; the fixing piece is strip-shaped and is fixedly arranged on the partition board of the unmanned aerial vehicle body, and the knob is rotationally connected with the fixing piece through a knob screw; the knob screw rod passes through a fixing piece round hole on the fixing piece and is screwed with the nut through threads;

the knob is strip-shaped and is arranged in a way that the knob is perpendicular to the fixing piece, and can limit the battery module of the unmanned aerial vehicle and limit the relative sliding of the battery module and the unmanned aerial vehicle body along the screw direction of the knob; and the knob can release the limit of the battery module along the screw direction of the knob at the position where the knob is parallel to the fixing piece.

Further, the anti-abrasion gasket is sleeved on the knob screw rod through an anti-abrasion gasket round hole and can rotate relative to the knob screw rod.

Further, four anti-abrasion gasket grooves are formed in the anti-abrasion gasket, and the four anti-abrasion gasket grooves are uniformly distributed along the circumferential direction of the round hole of the anti-abrasion gasket; the rotating piece is provided with a rotating piece limiting protrusion; when the rotating piece and the anti-abrasion gasket rotate relatively, the limiting protrusions of the rotating piece can switch different grooves of the anti-abrasion gasket to be clamped.

Further, the knob screw includes: a knob anti-rotation matching part, a rotor anti-rotation matching part and a screw part; the anti-rotation matching part of the rotating piece is a rectangular column section, is sleeved in the limiting hole of the rotating piece and can drive the rotating piece to synchronously rotate; the knob is sleeved outside the knob anti-rotation matching part, and is fixedly connected with the knob through a knob fixing screw; the screw rod part is screwed with the nut through threads.

Further, the wear pad grooving includes: a horizontal slot of the anti-abrasion gasket and a vertical slot of the anti-abrasion gasket;

when the rotating piece limiting bulge of the rotating piece is aligned with the anti-abrasion gasket transverse groove, the knob is perpendicular to the fixing piece and the partition plate;

when the rotating piece limiting bulge of the rotating piece is aligned with the vertical groove of the anti-abrasion gasket, the knob is parallel to the fixing piece and the partition plate;

when the limiting bulge of the rotating piece is aligned with the transverse groove or the vertical groove of the anti-abrasion gasket, the elastic force of the spring gasket can press the limiting bulge of the rotating piece into the transverse groove or the vertical groove of the anti-abrasion gasket.

An unmanned aerial vehicle comprises an unmanned aerial vehicle body, a quick-release battery fixing locking device and a battery module;

two battery clamping grooves for installing battery modules are formed in the unmanned aerial vehicle body; a partition board is arranged between the two battery clamping grooves; an upper sliding rail and a lower sliding rail are respectively arranged on the upper side and the lower side of the battery clamping groove; the upper side and the lower side of the battery module are respectively provided with a battery upper chute and a battery lower chute; the upper sliding rail can be in sliding fit with the upper sliding groove of the battery; the battery lower sliding groove can be in sliding fit with the lower sliding rail; the direction of the knob screw is consistent with the extending direction of the upper sliding rail and the lower sliding rail.

Further, a lock catch chute is arranged at the end part of the battery module; and the knob is in sliding contact with the lock catch sliding groove when rotating.

Further, the two ends of the knob are provided with magnet fixing grooves; a magnet is arranged in the magnet fixing groove; and a Hall sensor is further arranged on the end face of the partition board.

Further, when the knob is parallel to the fixing piece and the partition board, the magnet is in contact with the Hall sensor, and the Hall sensor can sense magnetism of the magnet; when the knob is perpendicular to the fixing piece and the partition board, the magnet is far away from the Hall sensor; the Hall sensor can judge whether the knob locks the battery module by sensing the position of the magnet.

Further, a battery connector is arranged on the front end face of the unmanned aerial vehicle body; when the battery module is matched with the battery clamping groove, the battery module and the battery connector can be electrically connected through plugging.

The technical scheme of the utility model at least can realize the following effects:

according to the quick-release battery fixing locking device, the limit and the release limit of the battery module are realized by setting the relative rotation of the knob and the fixing piece, so that the battery module is locked and unlocked, and the operation is simple and reliable.

In the utility model, the technical schemes can be mutually combined to realize more preferable combination schemes. Additional features and advantages of the utility model will be set forth in the description which follows, and in part will be obvious from the description, or may be learned by practice of the utility model. The objectives and other advantages of the utility model may be realized and attained by the structure particularly pointed out in the written description and drawings.

Drawings

The drawings are only for purposes of illustrating particular embodiments and are not to be construed as limiting the utility model, like reference numerals being used to refer to like parts throughout the several views.

Fig. 1 is a unmanned aerial vehicle with a quick-release battery fixing latch device according to embodiment 2 of the present utility model;

fig. 2 is a mounting state of a unmanned aerial vehicle body and a battery according to embodiment 2 of the present utility model;

FIG. 3 is an exploded view of a battery lock module of a quick release battery lock device according to embodiment 1 of the present utility model;

fig. 4 is a rear view of the battery lock module of embodiment 1 in a locked state;

fig. 5 is a front view of the battery lock module of embodiment 1 in a locked state;

FIG. 6 is an unlocked state of the quick release battery securing latch of the present utility model;

fig. 7 is a locked state of the quick release battery fixing locker of the present utility model.

Reference numerals:

1-an unmanned aerial vehicle body; 2-an upper slide rail; 3-front end face; a 4-battery connector; 5-a lower slide rail; a 6-hall sensor; 7-a battery latch module; 8-a chute on the battery; 9-a locking chute; 10-a battery lower chute; 11-a battery module; 12-knob limiting holes; 13-a magnet fixing groove; 14-a decorative sheet; 15-knob set screw; 16-a knob; 17-magnet; 18-a knob screw; 19-a fastener screw; 20-fixing parts; 21-an anti-wear pad; 22-a rotating piece; 23-spring washers; 24-nut; 25-a rotating piece limiting hole; 26-a rotating piece limiting protrusion; 27-a round hole of an anti-abrasion gasket; 28-grooving the anti-abrasion gasket; 29-an anti-abrasion gasket fixing groove; 30-a round hole of the fixing piece; 31-a rotation-preventing mating part of the rotating piece; 32-a knob anti-rotation mating portion.

Detailed Description

The following detailed description of preferred embodiments of the utility model is made in connection with the accompanying drawings, which form a part hereof, and together with the description of the embodiments of the utility model, are used to explain the principles of the utility model and are not intended to limit the scope of the utility model.

Example 1

In one embodiment of the present utility model, a quick-release battery fixing latch device is provided, as shown in fig. 3, 4 and 5, including: knob 16, knob stem 18, mount 20, and nut 24; the fixing piece 20 is strip-shaped and fixedly arranged on a partition board of the unmanned aerial vehicle body 1, and the knob 16 is rotationally connected with the fixing piece 20 through a knob screw 18; the knob screw 18 passes through a fixing piece round hole 30 on the fixing piece 20 and is screwed with the nut 24 through threads;

the fixing member 20 and the nut 24 are sequentially provided with: a wear pad 21, a rotor 22 and a spring pad 23; the anti-wear gasket 21 is arranged in an anti-wear gasket fixing groove 29 on the back surface of the fixing piece 20 and cannot rotate relatively through shape limitation; the rotating piece 22 is matched with the knob screw 18 through a rectangular rotating piece limiting hole 25 and can synchronously rotate; the spring washer 23 is used for providing a pressing force between the wear-preventing washer 21 and the rotating plate 22;

as shown in fig. 3, the knob 16 is strip-shaped, and is configured such that the knob 16 is at a position perpendicular to the fixing member 20, and the knob 16 is capable of limiting the battery module 11 of the unmanned aerial vehicle, and limiting the relative sliding movement of the battery module 11 and the unmanned aerial vehicle body 1 along the direction of the knob screw 18; and the knob 16 can release the restriction of the battery module 11 in the direction of the knob screw 18 at a position where the knob 16 is parallel to the fixing member 20.

Specifically, the anti-wear gasket 21 is provided with an anti-wear gasket round hole 27 and an anti-wear gasket slot 28; the rotating plate 22 is provided with a rectangular rotating plate limiting hole 25 and a rotating plate limiting protrusion 26; the rotor plate retention tabs 26 are able to snap into the wear pad slots 28.

Further, the anti-wear pad 21 is sleeved on the knob screw 18 through an anti-wear pad round hole 27, and can rotate relative to the knob screw 18.

Further, four anti-wear gasket grooves 28 are formed in the anti-wear gasket 21, and the four anti-wear gasket grooves 28 are uniformly distributed along the circumferential direction of the anti-wear gasket round hole 27; the rotating plate 22 is provided with a rotating plate limiting protrusion 26; when the rotating piece 22 and the anti-wear pad 21 rotate relatively, the rotating piece limiting protrusion 26 can switch different anti-wear pad slots 28 to be engaged.

Further, the knob 16 is fixedly connected with the knob screw 18 through a knob fixing screw 15; the fixing piece 20 is provided with a fixing piece round hole 30, and the knob screw 18 passes through the fixing piece round hole 30 and is screwed with the nut 24 through threads.

Specifically, as shown in fig. 3 and 4, the back of the fixing member 20 is provided with a concave movement space; the anti-wear pad 21, the rotating plate 22, the spring pad 23 and the nut 24 are all arranged on the back surface of the fixing piece 20 and sleeved on the knob screw 18.

Specifically, as shown in fig. 3, the fixing members 20 are fixedly mounted on the end surfaces of the partition walls of the unmanned aerial vehicle body 1 by four fixing member screws 19.

In one embodiment of the present utility model, as shown in fig. 3, the knob screw 18 includes: a knob anti-rotation engagement portion 32, a rotation piece anti-rotation engagement portion 31, and a screw portion; the rotation piece anti-rotation matching part 31 is sleeved in the rotation piece limiting hole 25 of the rotation piece 22, and the rotation piece anti-rotation matching part 31 is a rectangular column section and can drive the rotation piece 22 to synchronously rotate; the knob 16 is sleeved outside the knob anti-rotation matching part 32 and fixedly connected with the knob 16 through a knob fixing screw 15; the screw portion is screwed with the nut 24.

Specifically, the rotation piece limiting hole 25 is a rectangular hole, and enables the rotation piece 22 to rotate along with the knob 16 and the knob screw 18.

Specifically, the knob anti-rotation engagement portion 32 of the knob screw 18 is a rectangular block capable of engaging the knob stopper hole 12 of the knob 16. As shown in fig. 5, the knob 16 is fixedly connected to the knob screw 18 by a knob fixing screw 15.

Further, the wear pad slot 28 includes: a horizontal slot of the anti-abrasion gasket and a vertical slot of the anti-abrasion gasket; when the rotor plate limit protrusions 26 of the rotor plate 22 are aligned with the wear pad transverse grooves, the knob 16 is perpendicular to the fixing member 20 and the partition plate; when the rotor plate limit protrusions 26 of the rotor plate 22 are aligned with the vertical grooves of the wear pad, the knob 16 is parallel to the fixing member 20 and the partition plate; when the rotor plate limiting protrusion 26 is aligned with the anti-wear pad slot 28, the elastic force of the spring pad 23 can press the rotor plate limiting protrusion 26 into the anti-wear pad slot 28.

Specifically, as shown in fig. 3, the four slots of the slot 28 of the anti-wear gasket are uniformly distributed along the circumferential direction of the round hole 27 of the anti-wear gasket in turn at an included angle of 90 degrees; wherein, two anti-wear gasket grooves 28 which are opposite from top to bottom are anti-wear gasket vertical grooves, and two anti-wear gasket grooves 28 which are opposite from left to right are anti-wear gasket horizontal grooves.

When the knob 16 is turned, the knob screw 18 can be driven to rotate, the knob screw 18 drives the turning piece 22 to rotate, at the moment, the limiting protrusion 26 of the turning piece leaves the vertical groove of the anti-abrasion gasket, and when the knob 16 is turned to 90 degrees, the limiting protrusion 26 of the turning piece is clamped into the transverse groove of the anti-abrasion gasket, so that locking and self-locking are realized. And similarly, the self-locking in the directions of 0 degree, 90 degrees, 180 degrees and 270 degrees is realized.

Further, as shown in fig. 1 and 2, a latch chute 9 is provided at an end of the battery module 11; the knob 16 is in sliding contact with the lock catch chute 9 when rotated.

Specifically, the knob 16 is integrally sleeved on the knob anti-rotation matching part 32 through the knob limiting hole 12, then the knob 16 is locked on the knob screw 18 through the knob fixing screw 15, finally the decorative sheet 14 is stuck on the knob 16, and finally the fixing piece 20 is locked and installed on the unmanned aerial vehicle body 1 through the four fixing piece screws 19. Specifically, the knob screw 18 is oriented in the same direction as the extension direction of the upper slide rail 2 and the lower slide rail 5.

Specifically, the knob limiting hole 12 is a square hole, and the knob fixing screw 15 is fixedly connected with the knob screw 18 through threads.

In this embodiment, when the battery module 11 is installed into the unmanned aerial vehicle from the tail of the unmanned aerial vehicle body 1, the knob 16 of the battery lock catch module 7 is rotated, and when the knob 16 is rotated into the lock catch chute 9 to 90 °, the knob 16 is self-locked to realize quick assembly and fixed locking of the battery, the battery lock catch module 7 is rotated by 90 °, and the knob 16 is in a locking position, so that the displacement of the battery module 11 can be limited, and the battery module 11 is locked, as shown in fig. 2 and 7.

Conversely, when the knob 16 is turned to 0 ° with respect to the fixing member 20, the battery module 11 can be pulled out backward to realize quick battery replacement, as shown in fig. 1 and 6.

Specifically, the anti-wear gasket 21 is fixed in the anti-wear gasket slot 28 on the back of the fixing piece 20 and cannot rotate, the knob screw 18 is assembled on the fixing piece 20 through the anti-wear gasket round hole 27 and the fixing piece round hole 30, then the rotating piece 22 is sleeved on the rotating piece anti-rotation matching part 31 of the knob screw 18 through the rotating piece limiting hole 25, two spring gaskets 23 are installed on the knob screw 18, the nut 24 is screwed on the knob screw 18 to be integrally fixed, the locking force of the nut 24 is adjusted through screwing the nut 24, the spring gaskets 23 are compressed, the rotating piece 22 and the anti-wear gasket 21 are further mutually extruded, and when the knob 16 drives the rotating piece 22 and the anti-wear gasket 21 to relatively rotate, the extrusion force of the spring gaskets 24 needs to be overcome, so that the rotation torque force of the adjusting knob is realized.

According to the quick-release battery fixing locking device, the anti-abrasion gasket 21 and the rotating piece 22 are arranged, so that the anti-abrasion gasket 21 is clamped and fixed in the anti-abrasion gasket fixing groove of the fixing piece 20, the knob 10 drives the rotating piece 22 to rotate through the knob screw 18, the rotating piece limiting protrusion 26 can be switched to be clamped with the transverse groove of the anti-abrasion gasket or the vertical groove of the anti-abrasion gasket, the rotating piece 22 and the anti-abrasion gasket 21 are pressed through the spring gasket 23, the elasticity of the spring gasket 23 is needed to be overcome when the locking state is guaranteed, and the position stability of the knob 10 is further achieved, so that the battery module 11 is effectively fixed.

Example 2

In one embodiment of the present utility model, a unmanned aerial vehicle is provided, as shown in fig. 1 and 2, including: the unmanned aerial vehicle comprises an unmanned aerial vehicle body 1, a battery module 11 and a battery lock catch module 7.

The unmanned aerial vehicle body 1 is provided with a baffle plate and a front end surface 3; two battery clamping grooves are formed in two sides of a partition board of the unmanned aerial vehicle body 1; the two battery modules 11 are respectively and slidably arranged in the two battery clamping grooves; a battery connector 4 is arranged on the front end face 3; the battery module 11 and the battery connector 4 can be electrically connected through plugging; a battery lock catch module 7 is arranged on the end face of the partition board; the battery lock module 7 employs the quick-release battery fixing lock device in embodiment 1 to lock and unlock the battery module 11.

In a specific embodiment of the present utility model, as shown in fig. 1 and fig. 2, an upper slide rail 2 and a lower slide rail 5 are respectively disposed on the upper and lower sides of the battery clamping groove; the upper side and the lower side of the battery module 11 are respectively provided with a battery upper chute 8 and a battery lower chute 10; the upper slide rail 2 can be in sliding fit with the battery upper slide groove 8; the battery lower chute 10 can be slidably fitted with the lower slide rail 5. The upper sliding groove 8 and the lower sliding groove 10 of the battery respectively realize the up-down, left-right fixing and the front-back sliding of the battery module 11 with the upper sliding rail 2 and the lower sliding rail 5, when the battery module 11 slides into the front end face 3, the front direction of the battery module 11 is fixed, and meanwhile, the battery module 11 supplies power to the airplane through the battery connector 4.

According to the utility model, the battery module 11 slides along the upper slide rail 2 and the lower slide rail 5 and can be placed in a battery clamping groove, and after the battery module 11 is assembled in place, the battery module is electrically connected with the battery connector 4 through plugging.

In one embodiment of the present utility model, as shown in fig. 3, the two ends of the knob 16 are provided with magnet fixing grooves 13; a magnet 17 is arranged in the magnet fixing groove 13; and a Hall sensor 6 is also arranged on the end face of the partition board.

Specifically, the two magnets 17 are fitted into the two magnet fixing grooves 13, respectively.

Specifically, when the knob 16 is parallel to the fixing member 20 and the partition plate, the magnet 17 is in contact with the hall sensor 6; the Hall sensor 6 can sense magnetism of the magnet 17 and judge whether the magnet 17 is in an unlocking state so as to realize battery installation in-place accuracy and flight safety.

When the knob 16 is perpendicular to the fixing member 20 and the partition plate, the magnet 17 is away from the hall sensor 6; the hall sensor 6 can determine whether the knob 16 is locked to the battery module 11 by sensing the position of the magnet 17.

Specifically, when the knob 16 is at the position of 0 ° or 180 ° with the fixing member 20, the hall sensor 6 senses the magnetic force of the magnet 17, and transmits an unlocking signal to the aircraft to prompt the battery to take off stationary in the unlocking state.

Similarly, when the knob 16 is at the position of 90 degrees or 270 degrees with the fixing piece 20, the magnet 17 is far away from the Hall sensor 6, the Hall sensor 6 cannot sense the magnetic force of the magnet 17, and at the moment, a locking signal is transmitted to the airplane to prompt that the battery can take off in a locking state.

The implementation process comprises the following steps:

in order to improve the reliability of battery fixation and the convenience of battery disassembly and assembly, the battery module is installed from the tail part of the unmanned aerial vehicle body 1 through the upper slide rail 2 and the lower slide rail 5, and the limiting fixation is realized through the upper slide rail 2 and the lower slide rail 5, the front end of the battery module 11 is connected with the battery connector 4 and is limited and fixed through the machine body, and the rear end is locked through the battery lock catch module 7; specifically, as shown in fig. 7, when the knob 16 is rotated by plus or minus 90 °, the knob 16 is perpendicular to the fixing member 20, and the knob 16 fixes the dead battery module 11, thereby achieving reliable fixation; when the knob 16 is rotated to 0 ° or 180 ° as shown in fig. 6, the knob 16 is parallel to the fixing member 20, the knob 16 is opened, and the battery mold 11 can be taken out, thereby realizing convenient disassembly and assembly of the battery.

The knob 16 has a self-locking function when rotating to plus or minus 90 degrees, meanwhile, the Hall sensor 6 is arranged in the position of the airplane body, the magnet 17 is arranged on the knob 16, when the knob 16 is at 0 degree or 180 degrees, the Hall sensor 6 receives magnetism of the magnet 17, the airplane battery module 11 is prompted to be unlocked and can not take off, and when the knob 16 is rotated to plus or minus 90 degrees, the Hall sensor 6 can not receive magnetism of the magnet 17, the airplane battery module 11 is prompted to be locked and can take off. The battery module 11 is installed in-place accurately and safely, and further flight safety is achieved.

The unmanned aerial vehicle of this embodiment has the self-locking function when the hasp rotates to plus or minus 90, has hall sensor in fuselage position inside simultaneously, has magnet on the hasp, and the hall sensor 6 is when 0 or 180 when the hasp receives the magnetism of magnet and is suggestion aircraft battery and unblanked can not take off, and hall sensor 6 is received the magnetism of magnet and is suggestion aircraft battery and is locked and can take off when the hasp rotates to plus or minus 90, realizes that the battery is installed in situ accuracy and security.

The present utility model is not limited to the above-mentioned embodiments, and any changes or substitutions that can be easily understood by those skilled in the art within the technical scope of the present utility model are intended to be included in the scope of the present utility model.

Claims

1. A quick release battery securing latch apparatus comprising: a knob (16), a knob screw (18), a fixing member (20) and a nut (24); the fixing piece (20) is strip-shaped and fixedly arranged on a partition board of the unmanned aerial vehicle body (1), and the knob (16) is rotationally connected with the fixing piece (20) through a knob screw (18); the knob screw (18) passes through a fixing piece round hole (30) on the fixing piece (20) and is screwed with the nut (24) through threads;

the knob (16) is strip-shaped and is arranged in a way that the knob (16) is perpendicular to the fixing piece (20), the knob (16) can limit a battery module (11) of the unmanned aerial vehicle, and relative sliding of the battery module (11) and the unmanned aerial vehicle body (1) along the direction of the knob screw (18) is limited; and the knob (16) can release the limit of the battery module (11) along the direction of the knob screw (18) at the position of the knob (16) parallel to the fixing piece (20).

2. The quick-release battery fixing and locking device according to claim 1, wherein a fixing member (20) and a nut (24) are sequentially provided with: an anti-wear pad (21), a rotating plate (22) and a spring pad (23); the anti-wear gasket (21) is arranged in an anti-wear gasket fixing groove (29) on the back of the fixing piece (20) and cannot rotate relatively through shape limitation; the rotating piece (22) is matched with the knob screw (18) through a rectangular rotating piece limiting hole (25) and can synchronously rotate; the spring washer (23) is used for providing a pressing force between the anti-abrasion washer (21) and the rotating piece (22); the anti-abrasion gasket (21) is sleeved on the knob screw (18) through an anti-abrasion gasket round hole (27) and can rotate relative to the knob screw (18).

3. The quick release battery fixing and locking device according to claim 2, wherein four anti-wear gasket grooves (28) are formed in the anti-wear gasket (21), and the four anti-wear gasket grooves (28) are uniformly distributed along the circumferential direction of the anti-wear gasket round hole (27); a rotating piece limiting protrusion (26) is arranged on the rotating piece (22); when the rotating piece (22) and the anti-abrasion gasket (21) rotate relatively, the rotating piece limiting protrusions (26) can switch different anti-abrasion gasket grooves (28) to be clamped.

4. A quick release battery securing latch as claimed in claim 3 wherein the knob screw (18) comprises: a knob anti-rotation matching part (32), a rotating piece anti-rotation matching part (31) and a screw part; the rotating piece anti-rotation matching part (31) is a rectangular column section, and the rotating piece anti-rotation matching part (31) is sleeved in the rotating piece limiting hole (25) and can drive the rotating piece (22) to synchronously rotate; the knob (16) is sleeved outside the knob anti-rotation matching part (32) and fixedly connected with the knob (16) through a knob fixing screw (15); the screw portion is screwed with a nut (24) by threads.

5. The quick release battery securement latch as set forth in claim 4, wherein said wear pad slot (28) includes: a horizontal slot of the anti-abrasion gasket and a vertical slot of the anti-abrasion gasket;

when the rotating piece limiting protrusion (26) of the rotating piece (22) is aligned with the anti-abrasion gasket transverse groove, the knob (16) is perpendicular to the fixing piece (20) and the partition plate;

when the rotating piece limiting bulge (26) of the rotating piece (22) is aligned with the vertical groove of the anti-abrasion gasket, the knob (16) is parallel to the fixing piece (20) and the partition plate;

when the rotating piece limiting bulge (26) is aligned with the anti-abrasion gasket transverse groove or the anti-abrasion gasket vertical groove, the elastic force of the spring gasket (23) can press the rotating piece limiting bulge (26) into the anti-abrasion gasket transverse groove or the anti-abrasion gasket vertical groove.

6. An unmanned aerial vehicle, characterized by comprising an unmanned aerial vehicle body (1), a quick-release battery fixing locker according to any one of claims 1-5 and a battery module (11);

two battery clamping grooves for installing a battery module (11) are formed in the unmanned aerial vehicle body (1); the separator is arranged between the two battery clamping grooves; an upper sliding rail (2) and a lower sliding rail (5) are respectively arranged on the upper side and the lower side of the battery clamping groove; the upper side and the lower side of the battery module (11) are respectively provided with a battery upper chute (8) and a battery lower chute (10); the upper sliding rail (2) can be in sliding fit with the upper battery sliding groove (8); the battery lower sliding groove (10) can be in sliding fit with the lower sliding rail (5);

the direction of the knob screw (18) is consistent with the extending direction of the upper sliding rail (2) and the lower sliding rail (5).

7. The unmanned aerial vehicle according to claim 6, wherein the end of the battery module (11) is provided with a catch chute (9); the knob (16) is in sliding contact with the lock catch sliding groove (9) when rotating.

8. The unmanned aerial vehicle according to claim 7, wherein the two ends of the knob (16) are provided with magnet fixing grooves (13); a magnet (17) is arranged in the magnet fixing groove (13); and a Hall sensor (6) is further arranged on the end face of the partition board.

9. The unmanned aerial vehicle according to claim 8, wherein the magnet (17) is in contact with the hall sensor (6) when the knob (16) is parallel to the fixture (20) and the partition, the hall sensor (6) being able to sense the magnetism of the magnet (17); when the knob (16) is perpendicular to the fixing piece (20) and the partition board, the magnet (17) is far away from the Hall sensor (6); the Hall sensor (6) can judge whether the knob (16) locks the battery module (11) by sensing the position of the magnet (17).

10. The unmanned aerial vehicle according to claim 9, wherein a battery connector (4) is provided on the front face (3) of the unmanned aerial vehicle body (1); when the battery module (11) is matched with the battery clamping groove, the battery module (11) and the battery connector (4) can be electrically connected through plugging.