WO2022041468A1

WO2022041468A1 - Inspection unmanned aerial vehicle

Info

Publication number: WO2022041468A1
Application number: PCT/CN2020/125456
Authority: WO
Inventors: 龚成; 陈辉
Original assignee: 南京拓兴智控科技有限公司
Priority date: 2020-08-31
Filing date: 2020-10-30
Publication date: 2022-03-03
Also published as: CN112193413A

Abstract

An inspection unmanned aerial vehicle, comprising a fuselage, a vehicle arm, a battery device (4), a load control cabin (5) and an inspection device. The bottom part of the fuselage is provided with a support frame; the support frame comprises a bottom part frame (9) having an opening at an upper part, a top cover (10) that seals the opening at the upper part of the bottom part frame (9), and a side baffle (11) that is vertically fixed to one end of the bottom part frame (9); the load control cabin (5) is fixed to one side of the side baffle (11); the battery device (4) is fixed to an upper part of the support frame and is located on a rear side of the load control cabin (5); and the inspection device is fixed at the bottom part of the load control cabin (5).

Description

A patrol drone

technical field

The present disclosure relates to the technical field of drones, for example, to an inspection drone.

Background technique

UAV is an unmanned aerial vehicle controlled by radio remote control equipment or its own program control device. With the rapid development of the UAV industry, more and more UAVs are applied to industries such as agriculture, forestry, electric power, inspection, telemetry and so on.

At present, industrial drones, such as inspection drones, are mostly small quadrotor drones, including fuselage, batteries, arms and inspection devices. There are four arms and are connected to the fuselage in a radial shape. The battery that supports the drone's battery life is fixed in the fuselage, and the equipped inspection device, such as a camera, is fixed at the bottom of the fuselage.

However, the above-mentioned four-rotor inspection drone has the battery fixed in the fuselage. Due to space constraints, the battery is small in size and has a short battery life, and the four arms are radially connected to the fuselage. To a certain extent The flight resistance is increased and the endurance time is further shortened.

SUMMARY OF THE INVENTION

In order to solve the above technical problems, the present disclosure provides an inspection drone with relatively small flight resistance and long endurance.

In order to achieve the above technical effects, the present disclosure adopts the following technical solutions: In the first aspect, the present disclosure provides an inspection drone, including a fuselage, an arm, a battery device, a load control cabin, and an inspection device;

The arm includes a connecting arm, a first arm and a second arm that are parallel and symmetrically arranged on both sides of the fuselage. The connecting arm is horizontally penetrated on the fuselage. The two ends are respectively connected with the first arm and the second arm;

The bottom of the fuselage is provided with a support frame, and the support frame includes a bottom frame with an upper opening, a top cover for sealing the upper opening, and a side baffle vertically fixed at one end of the bottom frame;

The battery device is fixed on the upper part of the support frame and is located on the rear side of the load control cabin; the load control cabin is fixed on one side of the side baffle; the inspection device is fixed on the load control cabin the bottom of the hull.

Optionally, the load control cabin shell includes a first shell and a second shell;

The bottom of the first shell is provided with an opening for the head to pass through, one side is provided with an L-shaped opening, and the other side is fitted and fixed with the side baffle;

the second shell is sealed at the L-shaped opening;

The second shell, the first shell and the side baffles are successively passed through the connecting pieces and then fixed.

Optionally, an accommodating space is formed after the first casing and the second casing are sealed and connected, and a load fixing frame is arranged in the accommodating space;

The load fixing frame is a double-layer frame structure, including two side plates and a partition plate connected between the two side plates, the side plates and the first shell are fixed by connecting pieces, and the partition plate Including upper and lower partitions arranged in parallel up and down;

Load modules are respectively fixed between the upper baffle and the lower baffle and the upper part of the upper baffle.

Optionally, the battery device includes an upper battery case, a lower battery case and a battery, and the upper battery case and the lower battery case form an installation space for accommodating the battery after being butted up and down and fixed.

Optionally, the battery device is fixed to the side baffle through a lock assembly fixed on the side baffle;

The side baffle is provided with an insertion hole, the end of the upper battery case is provided with a first insertion portion, and the end of the lower battery case is provided with a second insertion portion; the first insertion portion and the first insertion portion are provided. Two plug-in parts are inserted into the jack; the first plug-in part is located above the second plug-in part;

A limit groove is formed on the second plug portion, and the limit groove cooperates with the lock assembly to limit the position.

Optionally, the lock assembly includes a fixed seat, a bayonet, a spring and a pusher;

The fixed seat is provided with a sliding groove, the two opposite side walls of the fixed seat are respectively provided with openings communicating with the sliding grooves, and the bayonet pin penetrates through one of the openings and is laterally penetrated through the sliding grooves. In the slot, the middle part of the bayonet pin is connected to a pusher inserted into the sliding slot, the pusher pushes the bayonet to slide along the slide slot, and the spring is used for the pusher to reset.

Optionally, both ends of the connecting arm are respectively connected with the first arm and the second arm through three-way pipe fittings;

The three-way pipe includes a first connecting pipe and a second connecting pipe that are integrally connected, one end of the first connecting pipe is integrally connected to the middle of the second connecting pipe, the other end is for the connecting arm to be inserted, and the second connecting pipe is connected Both ends of the pipe are open for the first arm or the second arm to pass through; the middle part of the second connecting pipe is provided with a mounting surface, and the mounting surface is used to support the RTK or GPS device.

Optionally, it also includes mounting parts;

The mounting piece is fixed in the second connecting pipe below the mounting surface; the bottoms of the two ends of the mounting piece are provided with bosses, the bosses are embedded with a first nut, and the mounting surface corresponds to the first nut A mounting hole is provided at the position, and the mounting member is fixed in the second connecting pipe through a bolt matched with the first nut.

Optionally, the accommodating space is divided into upper and lower parts, the load is fixedly erected on the upper half of the accommodating space, and the inspection device is fixed on the lower half of the accommodating space.

Optionally, the bottom of the side baffle is provided with two hooks, and the corresponding position of the load control cabin is provided with a slot matching the hooks.

The adoption of the above technical solution includes the following beneficial effects: the inspection drone provided by the present disclosure, the whole arm of the drone is "H" shaped, which is conducive to reducing the flight resistance of the drone and reducing the structural weight; the fuselage It is "L-shaped" and the overall layout is reasonable. The battery device is fixed on the upper part of the support frame, the load control cabin for fixing the inspection device is fixed at one end of the support frame, and the inspection device is fixed at the bottom of the load control cabin. The structure is compact, the volume is small, and the battery can support a long battery life, which is conducive to improving the operation efficiency of the inspection drone.

Description of drawings

1 is a schematic structural diagram of an inspection drone provided by the present disclosure;

2 is a schematic diagram of a detached structure of an inspection drone provided by the present disclosure;

Fig. 3 is a partial enlarged view at B in Fig. 2;

4 is a schematic diagram of a detached structure of a load control cabin provided by an embodiment of the present disclosure;

Fig. 5 is a partial enlarged view at D in Fig. 2;

6 is a schematic diagram of the internal structure of a load housing in a load control cabin provided by an embodiment of the present disclosure;

7 is a schematic structural diagram of a load holder provided by an embodiment of the present disclosure;

8 is a schematic structural diagram of an upper battery case and a lower battery case in a battery device provided by an embodiment of the present disclosure;

9 is a schematic structural diagram of a lock assembly provided by an embodiment of the present disclosure;

10 is a cross-sectional view of a latch assembly provided by an embodiment of the present disclosure;

Fig. 11 is the split structure schematic diagram at A place in Fig. 1;

Fig. 12 is a partial enlarged view at A in Fig. 1;

FIG. 13 is a schematic structural diagram of a mounting member according to an embodiment of the present disclosure;

Figure 14 is a sectional view at A in Figure 1;

15 is a schematic diagram of a detached structure of a GPS device provided by the present disclosure;

Fig. 16 is a partial enlarged view at E in Fig. 14;

FIG. 17 is a schematic diagram of the internal structure of the load control cabin provided by the embodiment of the present disclosure;

FIG. 18 is a partial enlarged view of C in FIG. 4 .

In the picture:

1-first arm; 2-second arm; 3-connecting arm; 4-battery device; 41-upper battery shell; 411-first plug-in part; 412-barb; 42-lower battery shell; 421 -Hook groove; 422-Clamping block; 423-Second insertion part; 424-Limiting groove; 43-Lock assembly; 431-Fixing seat; 4311-Sliding groove; - bayonet; 434 - spring; 435 - connecting column; 4351 - card table; 5 - load control cabin; 51 - first casing; 511 - extension plate; 52 - second casing; 53 - load fixing frame; 531-side plate; 532-upper partition; 533-lower partition; 534-vertical limit plate; 535-L-shaped limiter; 6-GPS device; 61-fixed table; 611-first connection hole; 7-RTK; 8-Tee fittings; 81-First connecting pipe; 811-First clamping groove; 82-Second connecting pipe; 821-Second clamping groove; 83-Installation surface; 831-Fixing through hole ;9-bottom frame;10-top cover;11-side baffle;111-socket;112-hook;12-L-shaped limit plate;13-head;14-camera;15-mounting parts;151 -Fixed through hole; 152-Boss; 16-RF connector; 17-Shock absorber plate; 18-Shock-absorbing ball;

detailed description

In order to make the purpose, technical solutions and advantages of the present disclosure clearer, the technical solutions in the embodiments of the present disclosure will be described clearly and completely below with reference to the accompanying drawings in the embodiments of the present disclosure. Obviously, the described embodiments are the Some, but not all, embodiments are disclosed. Based on the embodiments in the present disclosure, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present disclosure.

In this disclosure, the terms "upper", "lower", "left", "right", "front", "rear", "top", "bottom", "inner", "outer", "middle", The orientation or positional relationship indicated by "vertical", "horizontal", "horizontal", "longitudinal", etc. is based on the orientation or positional relationship shown in the drawings. These terms are primarily used to better describe the present disclosure and embodiments thereof, and are not intended to limit the fact that the indicated device, element, or component must have a particular orientation, or be constructed and operated in a particular orientation.

In addition, some of the above-mentioned terms may be used to express other meanings besides orientation or positional relationship. For example, the term "on" may also be used to express a certain attachment or connection relationship in some cases. For those of ordinary skill in the art, the specific meanings of these terms in the present disclosure can be understood according to specific situations.

Furthermore, the terms "installed", "set up", "provided with", "connected", "connected" and "socketed" should be construed broadly. For example, it may be a fixed connection, a detachable connection, or a unitary structure; it may be a mechanical connection, or an electrical connection; it may be directly connected, or indirectly connected through an intermediary, or between two devices, elements, or components. internal communication. For those of ordinary skill in the art, the specific meanings of the above terms in the present disclosure can be understood according to specific situations.

Unless stated otherwise, "plurality" means two or more.

The inspection drone of the present disclosure will be described below through specific embodiments and in conjunction with the accompanying drawings.

1 is a schematic structural diagram of an inspection drone provided by the present disclosure, FIG. 3 is a partial enlarged view of B in FIG. 2 , and FIG. 4 is a separate structural schematic diagram of a load control cabin provided by an embodiment of the present disclosure. FIG. 1 , FIG. 3 and FIG. 4 illustrate an embodiment of the inspection drone of the present disclosure.

In an embodiment of the inspection drone provided by the present disclosure, the inspection drone may include a fuselage, an arm, a battery device 4 , a load control cabin 5 and an inspection device.

Wherein, the arm can be an "H"-shaped structure, including a connecting arm 3 and a first arm 1 and a second arm 2 that are parallel and symmetrically arranged on both sides of the fuselage. The connecting arm 3 is horizontal Wearing on the fuselage, the two ends of the connecting arm 3 are respectively connected with the first arm 1 and the second arm 2. The shape and quantity of the connecting arm 3 are not limited in the embodiments of this application. , and the present application does not limit the connection position or connection method of the connecting arm 3 and the first arm 1 and the second arm 2, and the accompanying drawings only show one of the implementations.

The bottom of the fuselage may be provided with a support frame, and the support frame may include a bottom frame 9 with an upper opening, a top cover 10 sealing the upper opening, and a side baffle 11 vertically fixed at one end of the bottom frame 9 ; The battery device 4 can be a cuboid structure as a whole, and the battery device 4 can be fixed on the upper part of the support frame and located on the rear side of the load control cabin 5; the load control cabin 5 is fixed on the On one side of the side baffle 11 , the load control cabin 5 can be installed with relevant loads for controlling the work of the inspection device. The load control cabin 5 can be located in the direction of the nose. In order to further reduce the flight resistance, the front side of the load control cabin 5 can be tapered, and the inspection device is fixed at the bottom of the load control cabin 5 .

In the inspection drone provided in this embodiment, the shape of the arms can be set as required, and the shape of the arms is not limited in this application. Optionally, the arm can be an H-shaped structure, the body is located between two parallel first arms 1 and second arms 2, and the connecting arm 3 is connected to the first arm The arm 1 and the second arm 2 pass through the fuselage, and the fuselage can be located in the middle of the connecting arm 3. The overall structure of the inspection drone is low in weight. The two arms 2 can both be set along the direction of the nose, which is beneficial to reduce the flight resistance of the drone.

A battery device 4 is fixed on the upper part of the top cover 10 . The battery device 4 can be a rectangular parallelepiped structure matching the bottom frame 9 . The load control compartment 5 is located at the front of the battery device 4 . The body structure layout is reasonable, the flight control system can be fixed in the bottom frame 9 , and the load module that controls the inspection device is fixed in the load control cabin 5 , and the inspection device can include a pan/tilt 13 and a camera 14 . The overall structure of the fuselage is compact and small in size, and the battery life is long.

FIG. 4 is a schematic diagram of a detached structure of a load control cabin provided by an embodiment of the present disclosure. An embodiment of an inspection drone of the present disclosure will be described below with reference to FIG. 4 .

The outer shell of the load control cabin 5 may include a first shell 51 and a second shell 52. The bottom of the first shell 51 is provided with an opening through which the pan/tilt head 13 passes. One side of the body 51 is provided with an L-shaped opening, the other side is fixedly attached to the side baffle 11, and the second housing 52 is sealed and connected to the L-shaped opening of the first housing 51; The second casing 52 , the first casing 51 and the side baffle 11 are successively passed through the connecting piece and then fixed. The connecting piece may be a screw or a bolt, and the connecting piece may be selected as required, and the present application does not limit the connecting piece. Optionally, the cross section of the second housing 52 parallel to the first arm 1 is a right-angled trapezoid, and the front end of the outer shell of the load control cabin 5 is tapered, which is beneficial to reduce flight resistance.

6 is a schematic diagram of the internal structure of the load housing in the load control cabin provided by the embodiment of the present disclosure, and FIG. 7 is a schematic diagram of the structure of the load fixing frame provided by the embodiment of the present disclosure. An example of a machine is described.

The first housing 51 and the second housing 52 are sealed and connected to form an accommodating space, and a load fixing frame 53 is arranged in the accommodating space. The load fixing frame 53 can be a double-layer frame structure, so The load fixing frame 53 may include two side plates 531 and a baffle plate connected between the two side plates 531 , and the baffle plates include an upper baffle plate 532 and a lower baffle plate 533 arranged in parallel up and down.

Load modules are fixed on the upper surface of the lower partition plate 533 and the upper surface of the upper partition plate 532 . Optionally, the load module on the upper partition 532 may be an image transmission module, and a pan/tilt controller and a power module may be fixed between the upper partition 532 and the lower partition 533 . The image transmission module and the power module are respectively electrically connected to the gimbal controller, and the gimbal controller is electrically connected to the flight controller inside the fuselage. The side plate 531 and the first housing 51 are fixed by connecting pieces, and the connecting pieces may be screws or bolts, and the connecting pieces may be selected according to needs, which are not limited in this application.

In order to improve the fixing effect of the upper partition plate 532, a vertical limit plate 534 and an L-shaped limit frame 535 may be provided on each of the two sides of the upper partition plate 532, respectively. The limit plate 534 and the L-shaped limit frame 535 are used to limit the left and right or up and down movement of the load module. The upper baffle 532 and the lower baffle 533 are respectively provided with a plurality of weight-reducing slots. The setting of the weight-reducing slots can reduce the weight of the entire load fixing frame 53 and improve the inspection drone. of endurance.

FIG. 8 is a schematic structural diagram of an upper battery case and a lower battery case in a battery device according to an embodiment of the present disclosure, FIG. 9 is a schematic structural diagram of a latch assembly provided in an embodiment of the disclosure, and FIG. 10 is a latch provided in an embodiment of the disclosure. A cross-sectional view of the assembly, an embodiment of the inspection drone of the present disclosure will be described below with reference to FIG. 1 , FIG. 8 , FIG. 9 and FIG. 10 .

The battery device 4 may include an upper battery case 41 , a lower battery case 42 and a battery, and the upper battery case 41 and the lower battery case 42 are connected up and down to form an installation space for accommodating the battery.

The shape of the battery is not limited in this application. Optionally, the battery has a rectangular parallelepiped structure. After the upper battery case 41 and the lower battery case 42 are docked up and down, a hollow rectangular parallelepiped structure matching the battery is formed. A battery frame is formed with an inner cavity matching the shape of the battery. The upper battery case 41 and the lower battery case 42 may be respectively formed with a plurality of weight-reducing holes to reduce the weight of the entire battery device 4 .

Optionally, the four corners of the upper battery case 41 and the lower battery case 42 are fixed by connecting pieces, and the middle parts of the upper battery case 41 and the lower battery case 42 are connected by snap assemblies; the side parts of the upper battery case 41 Barbs 412 are formed, and hook grooves 421 matching the barbs are provided at corresponding positions on the side of the lower battery case 42. After the upper battery case 41 and the lower battery case 42 are connected up and down, The hook 412 is snapped into the hook groove 421 . The four corners of the ends of the upper battery case 41 and the lower battery case 42 are fixed by connecting pieces, whereby the upper battery case 41 and the lower battery case 42 can be fixed together. The connecting pieces can be bolts or screws, and the connecting pieces can be It is selected according to needs, and the present application does not limit the connector.

The battery device 4 is fixed to the side shield 11 through a locking assembly 43 fixed on the side shield 11 .

An insertion hole 111 is formed on the side baffle 11 , a first insertion portion 411 is formed at the end of the upper battery case 41 , and a second insertion portion 423 is formed at the end of the lower battery case 42 ; An inserting portion 411 and a second inserting portion 423 are inserted into the socket 111 ; the first inserting portion 411 is located above the second inserting portion (423).

A limiting groove 424 is formed on the second plug portion 423, and the limiting groove 424 cooperates with the locking member 43 to limit the position; a limiting groove 424 is formed on the second plug portion 423, and the first A plug portion 411 and a second plug portion 423 are inserted into the socket 111 .

In order to enhance the fixing effect of the battery fixing device, optionally, a plurality of L-shaped limit plates 12 may be formed at intervals on both sides of the top cover 10, and a plurality of the L-shaped limit plates on each side A guide groove is formed on the plate 12 , a plurality of spaced engaging blocks 422 are respectively extended on both sides of the bottom of the lower battery case 42 , and the lower battery case 42 slides along the guide groove and abuts against the side stopper At the plate 11, the clamping block 422 is correspondingly clamped under the L-shaped limiting plate 12, so as to prevent the battery from moving upward.

The battery device 4 is fixed on the upper part of the top cover 10 and the side part is fixed with the side baffle 11 through the locking element 43 . The battery device 4 is fixed on the fuselage through the lock assembly 43 , which is more reliable than the fixing method of the strap. The overall shape of the battery fixing device formed by the docking of the upper battery case 41 and the lower battery case 42 may be a rectangular parallelepiped structure, the battery fixing device is directly fixed on the upper part of the top cover 10, and the battery fixing device is The lower surface is matched with the upper surface of the top cover 10 , which is not only beneficial to save space in the fuselage, but also beneficial to prolong the battery life of the inspection drone.

The locking assembly 43 may include a fixing seat 431 , a bayonet 433 , a spring 434 and a pushing member 432 .

The fixed seat 431 is provided with a sliding groove 4311 , two opposite side walls of the fixed seat 431 are respectively formed with openings 4312 communicating with the sliding grooves 4311 , and the bayonet 433 is penetrated by one of the openings 4312 . The middle part of the locking pin 433 is connected with the pushing member 432 inserted into the sliding groove 4311, and the pushing member 432 pushes the locking pin 433 along the sliding groove 4311. The sliding groove 4311 slides, and the spring 434 is used to reset the pusher 432 .

The fixing process of the battery fixing device using the lock assembly 43 is as follows. When the battery fixing device is installed on the body, the locking pin 433 is correspondingly snapped into the limiting slot 424 to limit the battery The fixing device is moved horizontally to prevent it from disengaging from the side fence 11 .

When the battery fixing device needs to be disassembled, the pusher 432 is pressed, and the pusher 432 drives the bayonet 433 to move along the sliding groove 4311 , and at the same time compresses the spring 434 , and the bayonet 433 disengages The limiting slot 424 further enables the second plug portion 423 to be released from the limiting function of the locking element 43 . Using the lock assembly 43 to fix the battery fixing device is convenient and quick to disassemble.

In this embodiment, the lock assembly 43 may further include a connecting column 435 , the connecting column 435 is fixedly connected to the pushing member 432 after passing through the bayonet 433 , and the connecting column 435 is formed along the peripheral wall. There is a ring of clamping table 4351 , and the clamping pin 433 is limited between the pushing member 432 and the clamping table 4351 .

The shape of the pusher 432 can be selected as required, and the present application does not limit the shape of the pusher 432 . Optionally, the pusher 432 is T-shaped with an inner thread hole formed at the bottom thereof, the surface of the connection post 435 is provided with an outer thread, and after one end of the connection post 435 passes through the bayonet 433, the thread becomes threaded. Connected in the threaded hole, the spring 434 is located in the sliding groove 4311 and connected between the connecting post 435 and the bottom of the sliding groove 4311 . The pushing member 432 and the bayonet 433 are connected by the connecting column 435, and the connecting column 435 and the pushing member 432 can be connected by a screw thread, and the components can be disassembled and replaced, which is convenient for maintenance.

FIG. 11 is a schematic diagram of a detached structure at A in FIG. 1 , and FIG. 12 is a partial enlarged view of A in FIG. 1 . An embodiment of an inspection drone of the present disclosure will be described below with reference to FIGS. 1 , 11 and 12 .

Both ends of the connecting arm 3 are respectively connected with the first arm 1 and the second arm 2 through a three-way pipe 8 .

Optionally, RTK7 and GPS device 6 are respectively fixed on the three-way pipe fittings 8 on both sides of the fuselage. On the one hand, the three-way pipe fittings 8 can be used to connect the first machine arm 1 and the connecting arm respectively. 3. The second arm 2 and the connecting arm 3, on the other hand, can reserve installation positions for both the RTK7 and the GPS device 6, which saves the installation space of the fuselage and simplifies the installation. With the structure, the GPS device 6 and the RTK 7 can be installed in an appropriate position at the same time and can maintain a certain distance, so as to avoid signal interference between each other.

The three-way pipe 8 may include a first connecting pipe 81 and a second connecting pipe 82 that are integrally connected, one end of the first connecting pipe 81 is integrally connected to the middle of the second connecting pipe 82, and the other The connecting arm 3 is plugged in, and both ends of the second connecting pipe 82 are open for the first arm 1 or the second arm 2 to pass through.

Optionally, one end of the first connecting pipe 81 into which the connecting arm 3 is inserted is formed with a first clamping groove 811 on the opposite two side walls along its axial direction, and the first clamping grooves 811 pass through each other. Tighten the bolts and fix the connecting arm 3 in the first connecting pipe 81; the two ends of the second connecting pipe 82 are respectively formed with second clips on the opposite side walls of each end along its axial direction. The clamping groove 821 and the second clamping groove 821 are screwed together to fix the first arm 1 or the second arm 2 in the second connecting pipe 82 .

Optionally, the first arm 1 or the second arm 2 respectively includes two extension arms, and the ends of the two extension arms are respectively inserted into the two extension arms through the openings at both ends of the second connecting pipe 82 . The second connecting pipe 82 is fixed inside. A mounting surface 83 is formed in the middle of the second connecting pipe 82 , and the mounting surface 83 can be used to mount the RTK 7 or the GPS device 6 .

FIG. 13 is a schematic structural diagram of a mounting member according to an embodiment of the present disclosure, FIG. 14 is a cross-sectional view at A in FIG. 1 , FIG. 15 is a separated structural schematic diagram of a GPS device provided in the disclosure, and FIG. 16 is a partial enlarged view of E in FIG. 14 . Fig. 17 is a schematic diagram of the internal structure of the load control cabin provided by the embodiment of the present disclosure, and Fig. 18 is a partial enlarged view of C in Fig. 4 . 17 and FIG. 18 illustrate one embodiment of the inspection drone of the present disclosure.

The inspection drone may further include a mounting member 15, and the mounting member 15 is fixed in the second connecting pipe 82; a boss 152 is formed at the bottom of both ends of the mounting member 15, and the boss 152 is inside A first nut is embedded, and a mounting hole 831 is formed on the mounting surface 83 corresponding to the position of the first nut. The mounting member 15 is fixed in the second connecting pipe 82 by a bolt matching the first nut.

In this embodiment, the RTK 7 and the GPS device 6 are respectively fixed on the two sides of the fuselage, that is, on the three-way pipe fitting 8 where the first machine arm 1 and the second connecting pipe 82 are connected. on the three-way pipe 8 at the connection between the second arm 2 and the second connecting pipe 82 .

Optionally, two fixing platforms 61 are formed at the bottom of the GPS device 6 , and first connecting holes 611 are formed on the fixing platforms 61 . Two second connection holes are formed on the installation surface 83 of the three-way pipe 8, and the GPS device 6 is fixed to the installation by connecting pieces passing through the first connection holes 611 and the second connection holes in sequence. On the surface 83, the connecting piece may be a screw or a bolt, and the connecting piece may be selected as required, and the connecting piece is not limited in this application.

Optionally, the RTK7 is connected with a radio frequency signal line. The radio frequency signal line may include a radio frequency connector 16 and a signal line. One end of the radio frequency connector is connected to the RTK7, and the other end is connected to the signal line. The signal line passes through the second arm 2 and is connected to the flight controller of the inspection drone; a fixing through hole 151 is formed in the middle of the mounting member 15, and the radio frequency connector 16 is connected from the mounting member 15. After the bottom of the component 15 passes through the fixing through hole 151 upward, it is screwed to the bottom of the RTK7. The fixing through hole 151 is a countersunk hole, and the RF signal line further includes a second nut, and the second nut is threadedly connected to the RF connector 16 and is fixed in the fixing through hole 151 .

When the RTK7 is installed, the mounting member 15 can be fixed to the three-way pipe fitting 8 first, and the bolts pass through the mounting holes on the three-way pipe fitting 8 and are screwed into the first nut on the mounting member 15 . Then install the RF signal line, pass the RF connector 16 through the fixing through hole 151 from the lower side of the mounting member 15, and then sleeve the second nut on the RF connector 16, rotate and then tighten it on In the fixing through hole 151, the radio frequency connector 16 is fixed on the three-way pipe 8 and the mounting member 15, and then the RTK7 is threadedly connected with the upper end of the radio frequency connector 16, thereby fixing the RTK7 on the on the three-way pipe fitting 8 .

In the inspection drone provided in this embodiment, the installation surface 83 and the installation member 15 are formed on the three-way pipe 8, which can be suitable for the installation of the RTK 7 and the GPS device 6, and no special design is required. Different installation structures, and the structure for fixing the RTK 7 and the GPS device 6 provided in this embodiment is simple, easy to install, and light in weight.

The accommodating space can be divided into upper and lower parts, the load fixing frame 53 is arranged on the upper half of the accommodating space, and the inspection device can be fixed on the lower half of the accommodating space.

In this embodiment, the gimbal 13 is fixed on the lower half of the accommodating space through a shock-absorbing seat, which can reduce the impact of the vibration generated during the flight of the drone on the gimbal 13, which is beneficial to improve the The stability of the gimbal 13;

The shock-absorbing seat may include a shock-absorbing plate 17 and a shock-absorbing ball 18 , two extending plates 511 are horizontally arranged in the accommodating space, and the shock-absorbing ball 18 is connected between the shock-absorbing plate 17 and the extension plate 18 . Between the plates 511 , an opening is provided at the bottom of the shell of the load control cabin 5 , and the pan/tilt head 13 is fixed to the bottom of the shock-absorbing plate 17 through the opening.

The shock-absorbing plate 17 is formed with a first connection hole, the extension plate 511 is formed with a second connection hole, and the shock-absorbing ball 18 may include an upper clamping portion 181, a lower clamping portion 182 and a The buffer portion 183 between the upper clamping portion 181 and the lower clamping portion 182, the upper clamping portion 181 passes through the first connection hole, and the lower clamping portion 182 passes through the second connection hole , the buffer portion 183 is located between the shock-absorbing plate 17 and the extension plate 511 . The buffer portion 183 of the shock-absorbing ball 18 is a hollow structure, and the shock-absorbing ball 18 can be made of rubber material, which can absorb vibration, greatly reduce the vibration transmitted to the gimbal 13, and improve the stability of the gimbal 13. It is beneficial to improve the shooting effect of the camera 14 .

FIG. 5 is an enlarged view of the part at D in FIG. 2 , and an embodiment of the inspection drone of the present disclosure will be described below with reference to FIGS. 3 , 4 and 5 .

Optionally, two hooks 112 are formed at the bottom of the side baffle 11 , and a slot matching the hooks 112 is formed at the corresponding position of the load control cabin 5 , and the hooks 112 are correspondingly locked into the first hooks 112 . in the slot of the casing 51 .

When assembling the load control cabin 5, the slot of the first housing 51 is clipped on the hook 112, and the hook 112 acts as a limit on the slot, so that the The first shell 51 precisely connects the side baffle 11 while preventing the load control cabin 5 and the side baffle 11 from being misaligned.

The above description is only an embodiment of the present disclosure, and is not intended to limit the present disclosure. For those skilled in the art, the present disclosure may have various modifications and changes. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present disclosure shall be included within the protection scope of the present disclosure.

Claims

An inspection drone, comprising a fuselage, an arm, a battery device, a load control cabin and an inspection device;

The arm includes a connecting arm, a first arm and a second arm that are parallel and symmetrically arranged on both sides of the fuselage. The connecting arm is horizontally penetrated on the fuselage. The two ends are respectively connected with the first arm and the second arm;

The bottom of the fuselage is provided with a support frame, and the support frame includes a bottom frame with an upper opening, a top cover for sealing the upper opening, and a side baffle vertically fixed at one end of the bottom frame;

The battery device is fixed on the upper part of the support frame and is located on the rear side of the load control cabin; the load control cabin is fixed on one side of the side baffle; the inspection device is fixed on the load control cabin the bottom of the hull.
The inspection drone according to claim 1, wherein the load control cabin shell comprises a first shell and a second shell;

The bottom of the first shell is provided with an opening for the head to pass through, one side is provided with an L-shaped opening, and the other side is fitted and fixed with the side baffle;

the second shell is sealed at the L-shaped opening;

The second shell, the first shell and the side baffles are successively passed through the connecting pieces and then fixed.
The inspection drone according to claim 2, wherein an accommodation space is formed after the first casing and the second casing are sealed and connected, and a load fixing frame is arranged in the accommodation space;

The load fixing frame is a double-layer frame structure, including two side plates and a partition plate connected between the two side plates, the side plates and the first shell are fixed by connecting pieces, and the partition plate Including upper and lower partitions arranged in parallel up and down;

Load modules are respectively fixed between the upper baffle and the lower baffle and the upper part of the upper baffle.
The inspection drone according to claim 2, wherein the battery device comprises an upper battery case, a lower battery case and a battery, and the upper battery case and the lower battery case are connected up and down to form an installation space for accommodating the battery .
The inspection drone according to claim 4, wherein the battery device is fixed to the side baffle by a lock assembly fixed on the side baffle;

The side baffle is provided with an insertion hole, the end of the upper battery case is provided with a first insertion portion, and the end of the lower battery case is provided with a second insertion portion; the first insertion portion and the first insertion portion are provided. Two plug-in parts are inserted into the jack; the first plug-in part is located above the second plug-in part;

A limit groove is formed on the second plug portion, and the limit groove cooperates with the lock assembly to limit the position.
The inspection drone according to claim 5, wherein the lock assembly comprises a fixed seat, a bayonet, a spring and a pusher;

The fixed seat is provided with a sliding groove, the two opposite side walls of the fixed seat are respectively provided with openings communicating with the sliding grooves, and the bayonet pin penetrates through one of the openings and is laterally penetrated through the sliding grooves. In the slot, the middle part of the bayonet pin is connected with a pusher inserted into the sliding slot, the pusher pushes the bayonet to slide along the slide slot, and the spring is used for the pusher to reset.
The inspection drone according to claim 1, wherein two ends of the connecting arm are respectively connected with the first arm and the second arm through three-way pipe fittings;

The three-way pipe includes a first connecting pipe and a second connecting pipe that are integrally connected, one end of the first connecting pipe is integrally connected to the middle of the second connecting pipe, the other end is for the connecting arm to be inserted, and the second connecting pipe is connected Both ends of the pipe are open for the first arm or the second arm to pass through; the middle part of the second connecting pipe is provided with a mounting surface, and the mounting surface is used to support the RTK or GPS device.
The inspection drone according to claim 7, further comprising a mounting member;

The mounting piece is fixed in the second connecting pipe below the mounting surface; the bottoms of the two ends of the mounting piece are provided with bosses, the bosses are embedded with a first nut, and the mounting surface corresponds to the first nut A mounting hole is provided at the position, and the mounting member is fixed in the second connecting pipe through a bolt matched with the first nut.
The inspection drone according to claim 3, wherein the accommodating space is divided into upper and lower parts, the load is fixedly erected on the upper half of the accommodating space, and the inspection device is fixed on the accommodating space. the lower half of the space.
The inspection drone according to claim 2, wherein two hooks are provided at the bottom of the side baffle, and a corresponding position of the load control cabin is provided with a slot matching the hooks.