CN217436040U

CN217436040U - Unmanned aerial vehicle and fuselage concatenation subassembly thereof

Info

Publication number: CN217436040U
Application number: CN202221421998.9U
Authority: CN
Inventors: 冯国东; 薛堃
Original assignee: Four Piece Technology Shenzhen Co ltd
Current assignee: Four Piece Technology Shenzhen Co ltd
Priority date: 2022-06-09
Filing date: 2022-06-09
Publication date: 2022-09-16
Anticipated expiration: 2032-06-09

Abstract

The utility model discloses an unmanned aerial vehicle and fuselage concatenation subassembly thereof, this fuselage concatenation subassembly includes: the device comprises a cross beam, a fixing seat and a fixing seat, wherein two ends of the cross beam are respectively provided with the fixing seat; the first support arm is arranged at one end of the cross beam and is rotationally connected to the cross beam through a first fixed seat; the second support arm is arranged at one end of the cross beam far away from the first support arm and is rotationally connected to the cross beam through a second fixed seat; wherein, the first support arm and the second support arm are respectively provided with a motor and a propeller. The utility model discloses an adoption adopts the concatenation subassembly to form unmanned aerial vehicle's fuselage, overcomes the technical problem that the unmanned aerial vehicle that exists the production different grade type among the prior art need develop different fuselages, has realized the unmanned aerial vehicle's fuselage of the mode production different grade type with the standard component. The utility model discloses but wide application in unmanned air vehicle technique field.

Description

Unmanned aerial vehicle and fuselage concatenation subassembly thereof

Technical Field

The utility model belongs to the technical field of the unmanned air vehicle technique and specifically relates to an unmanned aerial vehicle and fuselage concatenation subassembly thereof is related to.

Background

Along with the development of unmanned aerial vehicle technique, unmanned aerial vehicle's kind is more and more, for example, the plant protection unmanned aerial vehicle of forest fire prevention, the unmanned aerial vehicle of rescue on water, the unmanned aerial vehicle of fighting of taking automatic rifle.

To above-mentioned different kinds of unmanned aerial vehicle, all have fuselage structure. At present, a machine body is designed for each machine type, and the problems caused by the method are as follows: and each machine body needs to be opened, so that the cost is high. Therefore, it is necessary to design a universal fuselage splicing assembly that can be applied to different types of unmanned aerial vehicles.

SUMMERY OF THE UTILITY MODEL

The present invention aims at solving at least one of the technical problems in the related art to a certain extent. Therefore, an object of the utility model is to provide an unmanned aerial vehicle and fuselage concatenation subassembly thereof can splice the fuselage that forms unmanned aerial vehicle rapidly through the fuselage concatenation subassembly of standard to the unmanned aerial vehicle of adaptation different grade type, thereby make things convenient for unmanned aerial vehicle's manufacturing.

The utility model adopts the technical proposal that:

in a first aspect, the utility model provides an unmanned aerial vehicle's fuselage concatenation subassembly, wherein, this fuselage concatenation subassembly includes: the beam is provided with two fixed seats at two ends respectively; the first support arm is arranged at one end of the cross beam and is rotationally connected to the cross beam through a first fixed seat; the second support arm is arranged at one end of the cross beam far away from the first support arm and is rotationally connected to the cross beam through a second fixed seat; wherein, the first support arm and the second support arm are respectively provided with a motor and a propeller.

The lower surface of the beam is provided with the first fixing seat, the upper surface of the beam is provided with the second fixing seat, the first support arm is arranged at one end of the lower surface of the beam through the first fixing seat, the second support arm is arranged at one end of the upper surface of the beam through the second fixing seat, the rotating directions of the first support arm and the second support arm are opposite, and the first support arm and the second support arm can be unfolded and folded on the beam respectively.

The first fixing seat and the second fixing seat are fixed on the cross beam through screws respectively, and the fixing seats are provided with hinge pin holes which are arranged on one sides of the fixing seats; the first pin holes matched with the hinge pin holes are formed in the first support arm and the second support arm respectively, the machine body splicing assembly further comprises first pins, the first pins penetrate through the hinge pin holes and the first pin holes, the first pins, the hinge pin holes and the first pin holes form a hinge mechanism, the hinge mechanism is formed, and the first support arm or the second support arm rotates around the fixing base in the direction of 0-90 degrees.

Wherein, the other side of the fixed seat is provided with a fixed pin hole for fixing the support arm, and the first support arm and the second support arm are respectively provided with a second pin hole matched with the fixed pin hole; the splicing assembly of the machine body also comprises a second pin, when the first support arm or the second support arm rotates around the fixed seat to form an angle of 90 degrees with the cross beam, the second pin penetrates through the fixed pin hole and the second pin hole, so that the first support arm or the second support arm is fixed on the cross beam, and the first support arm or the second support arm is unfolded; and pulling the second pin out of the pin hole formed by the fixing pin hole and the second pin hole, and then rotating the first support arm or the second support arm around the fixing seat to form an angle of 0 degree with the cross beam, wherein the first support arm or the second support arm is folded and furled at the moment.

Wherein, this first support arm and this second support arm include horn fixing base, horn and the motor fixing base that end to end respectively, and this first pinhole and this second pinhole are seted up respectively in the both sides of this horn fixing base, are provided with this motor and this screw on this motor fixing base.

Wherein, the inside of this fixing base, this horn and this motor fixing base is empty to set up the electric wire of this motor.

When the elastic piece at the top is pressed downwards, the bulge contracts towards the middle inside the nail body, so that the second pin penetrates through the pin hole, and when the elastic piece at the top is released, the bulge extends out of the nail body, so that the second pin is fixed on the pin hole.

Wherein, the horn fixing base, the horn and the motor fixing base are connected by screw.

The second aspect, the utility model provides an unmanned aerial vehicle, a serial communication port, including left fuselage, right fuselage, equipment cabin and the connecting piece of connecting this left fuselage and this right fuselage, this left fuselage and this right fuselage include as above-mentioned any kind of fuselage concatenation subassembly.

Wherein, the distance between this left fuselage and this right fuselage and the length of this connecting piece set up to this equipment cabin of different sizes is installed in the adaptation.

The utility model has the advantages that:

the utility model discloses an adoption adopts the concatenation subassembly to form unmanned aerial vehicle's fuselage, overcomes the technical problem that the unmanned aerial vehicle that exists the production different grade type among the prior art need develop different fuselages, has realized the unmanned aerial vehicle's fuselage of the mode production different grade type with the standard component.

Thirdly, the utility model discloses set up a rotatable coupling's support arm respectively at the upper surface of crossbeam and lower surface, the horn has expansion and fold condition to conveniently place unmanned aerial vehicle.

Additionally, the utility model discloses a fuselage concatenation subassembly simple structure, convenient production.

The utility model discloses but wide application in unmanned air vehicle technique field.

Drawings

Fig. 1 is a schematic structural diagram of an embodiment of the unmanned aerial vehicle in an unfolded state;

fig. 2 is a schematic structural diagram of an embodiment of the folding state of the unmanned aerial vehicle of the present invention;

fig. 3 is a schematic structural diagram of an embodiment of the unmanned aerial vehicle body in the deployed state of the present invention;

fig. 4 is a schematic structural diagram of an embodiment of the unmanned aerial vehicle body in a folded state;

fig. 5 is the explosion structure schematic diagram of an embodiment of the unmanned aerial vehicle fuselage concatenation subassembly of the utility model.

Detailed Description

It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict.

Example one

Please refer to fig. 1 and fig. 2 together, fig. 1 is a schematic structural diagram of an embodiment of the unmanned aerial vehicle in the unfolded state, and fig. 2 is a schematic structural diagram of an embodiment of the unmanned aerial vehicle in the folded state. As shown in fig. 1 and 2, the unmanned aerial vehicle includes a left body 10, a right body (not shown), a connecting member 20 connecting the left body and the right body, and an equipment bay 30. The equipment bay 30 has installed therein a plurality of onboard equipment of the drone. Wherein, the shape of left fuselage 10 and right fuselage is the same, and the symmetry sets up on unmanned aerial vehicle to all have expansion state and fold condition. Wherein the distance between the left and

right bodies

10 and 20 can be set, and the length of the connection member can be set to suit installation of equipment compartments 30 of different sizes. Like this, form the fuselage of unmanned aerial vehicle of different size sizes to apply to on the unmanned aerial vehicle of various different types.

Please refer to fig. 3 and fig. 4 together, fig. 3 is a schematic structural diagram of an embodiment of the unmanned aerial vehicle body when the unmanned aerial vehicle is in the unfolded state, and fig. 4 is a schematic structural diagram of an embodiment of the unmanned aerial vehicle body when the unmanned aerial vehicle is in the folded state. As shown in fig. 3 and 4, the left body and the right body have the same shape and are formed by splicing the splicing assemblies.

In this embodiment, form unmanned aerial vehicle's left fuselage and right fuselage through the concatenation subassembly, the distance between the fuselage about the rethread setting is installed the connecting piece on left and right fuselage, has just so formed unmanned aerial vehicle's whole fuselage, and the erection equipment cabin on the fuselage again to use on the unmanned aerial vehicle of different grade type.

Example two

Please refer to fig. 5, fig. 5 is a schematic diagram of an explosion structure of an embodiment of the unmanned aerial vehicle body splicing assembly of the present invention. As shown in fig. 5, the fuselage splicing assembly 10 includes a cross beam 11, a first arm 12, a second arm 13, a first fixing seat 14, a second fixing seat 15, a first pin 16, and a second pin 17.

The lower surface of the cross beam 11 is provided with a first fixed seat 14, and the upper surface of the cross beam 11 is provided with a second fixed seat 15. The first arm 12 is disposed at one end of the lower surface of the beam 11, and the first arm 12 is rotatably connected to the beam 11 through a first fixing seat 14. The second arm 13 is disposed on an end of the upper surface of the beam 11 away from the first arm 12, and the second arm 13 is rotatably connected to the beam 11 through a second fixing seat 15. As can be seen from fig. 1 to 4, the first arm 12 and the second arm 13 are respectively extendable and foldable on the cross member 11.

The following describes in detail how the first arm 12 and the second arm 13 are realized to be expandable and foldable on the cross member 11. Since the first arm 12 and the second arm 13 have the same structure, only how the first arm 12 is connected to the beam 11 will be described below.

As shown in fig. 5, the first arm 12 includes an arm fixing base 121, an arm 122 and a motor fixing base 123 connected end to end. The arm fixing base 121, the arm 122 and the motor fixing base 123 are screwed together by screws.

It is understood that the arm fixing base 121 is used for fixing the first arm 12, the arm 122 is a main body of the first arm 122, and the motor fixing base 123 is used for mounting a propeller (not shown) and a motor (not shown). It should be noted that the first fixing seat 14, the arm fixing seat 121, the inside of the arm 122 and the motor fixing seat 123 are all empty, so as to conveniently dispose the electric wire of the motor.

As shown in fig. 5, the first fixing seat 14 is fixed to the lower surface of the cross beam 11 by screws. The first fixing base 14 is respectively provided with a hinge pin hole 141 and a fixing pin hole 142 for fixing the first support arm 12, and the hinge pin hole 141 and the fixing pin hole 142 are respectively disposed on two sides of the fixing base 14. The two sides of the arm fixing base 121 are respectively provided with a first pin hole 1211 matching with the hinge pin hole 141 and a second pin hole 1212 matching with the fixing pin hole 142.

The first pin 16 penetrates through the hinge pin hole 141 and the first pin hole 1211, and the first pin 16, the hinge pin hole 141 and the first pin hole 1211 form a hinge mechanism, so that the first support arm 12 rotates around the fixed seat 14 in the direction of 0-90 degrees. As can be seen from fig. 5, the first arm 12 and the second arm 13 rotate in opposite directions, the first arm 12 rotates around the fixing seat 14 in a counterclockwise direction, and the second arm 13 rotates around the fixing seat 15 in a clockwise direction. It is noted here that the first pin 16 is provided with a nut so as to fix the first pin 16 in the pin hole formed by the hinge pin hole 141 and the first pin hole 1211.

When the first arm 12 rotates around the first fixing seat 14 to 90 degrees with respect to the cross beam 11, the second pin 17 penetrates through the fixing pin hole 142 and the second pin hole 1212, so that the first arm 12 is fixed on the cross beam 11, and at this time, the first arm 12 is unfolded.

The second pin 17 is pulled out of the pin hole formed by the fixing pin hole 142 and the second pin hole 1212, and then the first arm 12 is rotated around the first fixing seat 14 to be at 0 degree (parallel) to the cross beam 11, so that the first arm 11 is folded.

Preferably, the second pin 17 is a quick release pin, the top of the second pin 17 is an elastic member (not shown), the bottom of the second pin 17 is provided with a protrusion (not shown), when the elastic member at the top is pressed downward, the protrusion is contracted inwards to the inside of the nail body, so that the second pin 17 passes through the pin hole, and when the elastic member at the top is released, the protrusion extends out from the nail body, so that the second pin 17 is fixed on the pin hole.

The utility model discloses when the installation, install first fixing base 14 and second fixing base 15 in the lower surface and the upper surface of crossbeam 11 respectively through the screw, match first pinhole 1211 on the horn fixing base 121 of first horn 12 with loose-leaf pinhole 141 on the first fixing base 14, then insert first pin 16, thereby be fixed in first fixing base 14 with first horn 12 on, then install horn 122 on horn fixing base 121 through the screw again, install motor fixing base 123 on horn 122 through the screw, again install motor and screw on horn fixing base 121. Of course, the first support arm 12 may be spliced first, that is, the arm fixing base 121, the arm 122 and the motor fixing base 123 are connected end to form the first support arm 12, and then the first support arm 12 is mounted on the first fixing base 14. The second arm 13 is then mounted to the second mounting block 15 in the same manner as the first arm 12. After the first arm 12 and the second arm 13 are both mounted on the beam 11, a left fuselage or a right fuselage is formed.

The utility model discloses a theory of operation does: the first arm 12 is rotated about the first holder 14, and when rotated to 90 degrees with respect to the beam 11, the elastic member at the top of the second pin 17 is pressed downward to insert the second pin 17 into the pin hole formed by the fixing pin hole 142 and the second pin hole 1212, and then the elastic member is released, so that the first arm 12 is firmly mounted on the beam 11. The same method is used to operate the three arms of the fuselage. Thus, the drone is in the deployed state ready for flight.

After the unmanned aerial vehicle finishes flying, press down the elastic component at second pin 17 top, extract second pin 17 from the pinhole that fixed pinhole 142, second pinhole 1212 formed, then put into second pin 17 in solitary second pinhole 1212 or fixed pinhole 142, like this, first arm 12 can rotate around first fixing base 14 again, when rotating to become 0 degree with crossbeam 11, first arm 11 just becomes folding folded state. Then, the other three support arms of the fuselage are folded in by the same method, so that the unmanned aerial vehicle can be conveniently placed when the unmanned aerial vehicle does not take off.

In other embodiments, the first fixing seat 14 and the second fixing seat 15 may be disposed on an upper surface or a lower surface, or even a side surface, of the cross beam 11, which is not limited herein.

In this embodiment, fuselage concatenation subassembly is produced with the form of standard component, convenient production and processing.

While the preferred embodiments of the present invention have been described, the present invention is not limited to the above embodiments, and those skilled in the art can make various equivalent modifications or substitutions without departing from the spirit of the present invention, and such equivalent modifications or substitutions are intended to be included within the scope of the present invention as defined by the appended claims.

Claims

1. The utility model provides an unmanned aerial vehicle's fuselage concatenation subassembly which characterized in that includes:

the device comprises a cross beam, wherein two ends of the cross beam are respectively provided with a fixed seat;

the first support arm is arranged at one end of the cross beam and is rotatably connected to the cross beam through a first fixed seat;

the second support arm is arranged at one end of the cross beam, which is far away from the first support arm, and the second support arm is rotatably connected to the cross beam through a second fixed seat;

wherein, the first support arm and the second support arm are respectively provided with a motor and a propeller.

2. The fuselage splicing assembly of claim 1, wherein the lower surface of the beam is provided with the first fixing seat, the upper surface of the beam is provided with the second fixing seat, the first support arm is arranged at one end of the lower surface of the beam through the first fixing seat, the second support arm is arranged at one end of the upper surface of the beam through the second fixing seat, the rotation directions of the first support arm and the second support arm are opposite, and the first support arm and the second support arm are respectively expandable and foldable on the beam.

3. The fuselage splicing assembly according to claim 2, wherein the first fixing seat and the second fixing seat are respectively fixed on the cross beam through screws, and the fixing seats are provided with hinge pin holes which are arranged on one sides of the fixing seats;

the first support arm and the second support arm are respectively provided with a first pin hole matched with the hinge pin hole, the machine body splicing assembly further comprises a first pin, the first pin penetrates through the hinge pin hole and the first pin hole, the first pin, the hinge pin hole and the first pin hole form a hinge mechanism, and the first support arm or the second support arm rotates around the fixed seat in the direction of 0-90 degrees.

4. The fuselage splicing assembly of claim 3, wherein the other side of the fixed seat is provided with a fixed pin hole for fixing a support arm, and the first support arm and the second support arm are respectively provided with a second pin hole matched with the fixed pin hole;

the machine body splicing assembly further comprises a second pin, when the first support arm or the second support arm rotates around the fixed seat to form an angle of 90 degrees with the cross beam, the second pin penetrates through the fixed pin hole and the second pin hole, so that the first support arm or the second support arm is fixed on the cross beam, and the first support arm or the second support arm is unfolded;

and pulling out the second pin from the pin hole formed by the fixing pin hole and the second pin hole, and then, when the first support arm or the second support arm rotates around the fixing seat to form 0 degree with the cross beam, folding and folding the first support arm or the second support arm.

5. The fuselage splicing assembly of claim 4, wherein the first support arm and the second support arm respectively comprise an end-to-end horn fixing seat, a horn and a motor fixing seat, the first pin hole and the second pin hole are respectively formed in two sides of the horn fixing seat, and the motor and the propeller are arranged on the motor fixing seat.

6. The fuselage splicing assembly of claim 5, wherein the interiors of the fixing base, the horn, and the motor fixing base are all empty to provide an electric wire of the motor.

7. The fuselage splicing assembly of claim 5, wherein the horn holder, the horn, and the motor holder are screwed together by screws.

8. The fuselage splicing assembly of claim 4, wherein the second pin is a quick release pin, the top of the second pin is an elastic member, the bottom of the second pin is provided with a protrusion, when the elastic member at the top is pressed downwards, the protrusion is retracted towards the middle inside the nail body, so that the second pin penetrates through the pin hole, and when the elastic member at the top is released, the protrusion extends out of the nail body, so that the second pin is fixed on the pin hole.

9. An unmanned aerial vehicle, characterized in that, includes left fuselage, right fuselage, equipment compartment and connects the left fuselage with the connecting piece of right fuselage, left fuselage with the right fuselage includes the fuselage concatenation subassembly of any one of preceding claims 1 to 8.

10. The unmanned aerial vehicle of claim 9, wherein a distance between the left fuselage and the right fuselage and a length of the connector are set to install the equipment bays of different sizes.