WO2020135637A1

WO2020135637A1 - Logistics unmanned aerial vehicle

Info

Publication number: WO2020135637A1
Application number: PCT/CN2019/128892
Authority: WO
Inventors: 张宝燕
Original assignee: 顺丰科技有限公司
Priority date: 2018-12-27
Filing date: 2019-12-26
Publication date: 2020-07-02
Also published as: CN109625257A

Abstract

A logistics unmanned aerial vehicle comprises a fuselage (1) and four rotary blade shafts (2) extending through the fuselage (1) and arranged in a criss cross fashion. Two ends of the rotary blade shaft (2) respectively extend out of the fuselage (1). A rotary blade is connected to each of the two ends of the rotary blade shaft (2). The four rotary blade shafts (2) include two first rotary blade shafts (3) arranged opposite to each other and two second rotary blade shafts (4) arranged opposite to each other. The first rotary blade shafts (3) are positioned above the second rotary blade shafts (4).

Description

Logistics drone

Technical field

This application generally relates to the field of logistics and transportation, and in particular to a logistics drone.

Background technique

Unmanned aerial vehicles are referred to as "drones" for short, and are unmanned aircraft operated by radio remote control equipment and self-provided program control devices. The domestic logistics drone technology is currently mainly made from consumer-grade or aeromodelling, and is mostly an X-shaped structure with four to eight rotors. The structure is complex, the cost is high, the battery disassembly is inconvenient, and the layout integration is low.

Summary of the invention

In view of the above defects or deficiencies in the prior art, it is desirable to provide a logistics drone.

The invention provides a logistics drone, including a fuselage and four rotor shafts arranged through the fuselage in a zigzag pattern, two ends of the rotor shaft respectively extend out of the fuselage, and the rotor shaft Rotors are connected to the two ends of the two respectively, and the four rotor shafts include two first rotor shafts and two second rotor shafts that are oppositely arranged, and the first rotor shaft is located above the second rotor shaft .

Further, the second rotor shaft is disposed next to the first rotor shaft, and the adjacent first rotor shaft and the second rotor shaft are connected and fixed to the fuselage by a first connecting member.

Further, the first connector includes a first sleeve and a second sleeve connected to the outer side wall of the first sleeve, the axis of the first sleeve is perpendicular to the axis of the second sleeve , The first sleeve is sleeved with the first rotor shaft, the second sleeve is sleeved with the second rotor shaft, and between the first sleeve and the second sleeve Reinforced ribs are provided.

Further, the first connecting member is an integrally formed structure.

Further, between the adjacent first rotor shaft and the second rotor shaft, a portion of the first rotor shaft extending out of the fuselage and the second rotor shaft extending out of the fuselage A second connector is also provided between the parts.

Further, the second connection member includes a first connection portion detachably connected to the first rotor shaft, a second connection portion detachably connected to the second rotor shaft, and the first connection portion and In the third connection portion of the second connection portion, the first connection portion and the third connection portion are bent and connected, and the second connection portion and the third connection portion are bent and connected.

Further, the third connecting portion is an elongated connecting rod, and the first connecting portion includes a first U-shaped socket connected to the third connecting portion and a butt joint with the first U-shaped socket A first cover plate, the second connection portion includes a second U-shaped seat connected to the third connection portion and a second cover plate docked with the second U-shaped seat, the first U-shaped seat The card holder, the third connecting portion and the second U-shaped card holder are an integrally formed structure.

Further, a vertical slot for installing a battery is provided on the top of the fuselage.

Further, the fuselage can also be detachably connected to a cargo warehouse, which is located below the fuselage.

Further, a support foot is connected to the bottom of the fuselage, and an antenna is provided inside the support foot.

According to the above technical solution, this application uses a chevron frame to build the rotor shaft, which has a simple structure, high rigidity and low weight; the battery assembly and disassembly adopts the top-down straight insertion design, and the battery's own gravity has a certain locking effect on the battery installation ; The cargo compartment and the fuselage can be installed separately, which can quickly load the cargo when unloading and loading the cargo, improving the operating efficiency; the supporting legs that constitute the landing gear are equipped with antennas, forming an integrated design of landing gear and antenna, centralized layout, saving materials, No additional weight.

BRIEF DESCRIPTION

By reading the detailed description of the non-limiting embodiments made with reference to the following drawings, other features, objects, and advantages of the present application will become more apparent:

1 is a schematic structural diagram of a logistics drone provided by an embodiment of the present invention;

FIG. 2 is an enlarged schematic view of part A in FIG. 1;

3 is another schematic structural diagram of a logistics drone provided by an embodiment of the present invention;

4 is an installation structure of an antenna in a logistics drone provided by an embodiment of the present invention.

detailed description

The present application will be further described in detail below with reference to the drawings and embodiments. It can be understood that the specific embodiments described herein are only used to explain the related invention, but not to limit the invention. It should also be noted that, for ease of description, only the parts related to the invention are shown in the drawings.

It should be noted that the embodiments in the present application and the features in the embodiments can be combined with each other if there is no conflict. The present application will be described in detail below with reference to the drawings and in conjunction with the embodiments.

As shown in FIGS. 1 to 4, the present invention provides a logistics drone, including a fuselage 1 and four rotor shafts 2 penetrating through the fuselage 1 and arranged in a zigzag pattern, with two ends of the rotor shaft 2 extending respectively On the fuselage 1, the rotor shaft 2 is connected to the rotor at both ends. The four rotor shafts 2 include two oppositely arranged first rotor shafts 3 and two oppositely arranged second rotor shafts 4, the first rotor shaft 3 is located at the Above the second rotor shaft 4.

In this application, the rotor includes a motor base provided at the top of both ends of the rotor shaft, a motor mounted on the motor base, and a propeller connected to the output shaft of the motor, to achieve the function of driving the logistics drone up and down; The root rotor shaft penetrates the fuselage to form a whole, with simple structure, light weight, no splicing of the rotor shaft, and high rigidity.

Further, the second rotor shaft 4 is disposed next to the first rotor shaft 3, and the adjacent first rotor shaft 3 and the second rotor shaft 4 are connected and fixed to the fuselage 1 by a first connector 5.

The first connector 5 is fixed to the side of the fuselage by a rivet or screw connection, and the first connector 5 is connected to the first rotor shaft 3 and the second rotor shaft 4 by a rivet or screw connection. Fix it to prevent the rotor shaft from sliding along its axis.

Further, the first connector 5 includes a first sleeve 7 and a second sleeve 8 connected to the outer side wall of the first sleeve 7, the axis of the first sleeve 7 is perpendicular to the axis of the second sleeve 8, A sleeve 7 is sleeved with the first rotor shaft 3, a second sleeve 8 is sleeved with the second rotor shaft 4, and a reinforcing rib 9 is provided between the first sleeve 7 and the second sleeve 8.

The first sleeve 7 and the second sleeve 8 both have a hollow rectangular parallelepiped structure; along the axial direction of the first sleeve 7, both ends of the first sleeve 7 overhang the second sleeve 8; along the second In the axial direction of the sleeve 8, both ends of the second sleeve 8 overhang the first sleeve 7; the first sleeve and the second sleeve cross each other. A rib 9 is provided between the surface of the first sleeve 7 overhanging the surface of the second sleeve 8 and the outer side wall of the second sleeve 8, and the second sleeve 8 overhangs the surface of the first sleeve and the first Reinforcement ribs 9 are also provided between the outer side walls of the sleeve, so that the structure of the first connecting member 5 is stable, so as to better support the first rotor shaft 3 and the second rotor shaft 4.

Further, the first connector 5 has an integrally formed structure, which has a simple structure and is easy to assemble.

Further, between the adjacent first rotor shaft 3 and the second rotor shaft 4, a portion of the first rotor shaft 3 extending from the fuselage 1 and a portion of the second rotor shaft 4 extending from the fuselage 1 are further provided有second connector 6

Further, the second connecting member 6 includes a first connecting portion 10 detachably connected to the first rotor shaft 3, a second connecting portion 11 detachably connected to the second rotor shaft 4, and connecting the first connecting portion 10 and the second In the third connection portion 12 of the connection portion 11, the first connection portion 10 and the third connection portion 12 are bent and connected, and the second connection portion 11 and the third connection portion 12 are bent and connected.

Further, the third connecting portion 12 is an elongated connecting rod, and the first connecting portion 10 includes a first U-shaped socket 13 connected to the third connecting portion 12 and a first cover docked with the first U-shaped socket 13 Plate 14, the second connection portion 11 includes a second U-shaped card holder 15 connected to the third connection portion 12, and a second cover plate 16 connected to the second U-shaped card holder 15, the first U-shaped card holder 13, the first The three connecting portions 12 and the second U-shaped card holder 15 are an integrally formed structure.

Further, a vertical slot 17 is provided on the top of the fuselage 1 for installing the battery 18. The battery is inserted vertically on the top of the fuselage, and the direction of the vertical slot is consistent with the direction of gravity. The gravity of the battery itself during the flight of the drone has a certain locking effect on the installation of the battery, and the direction of gravity of the battery when removing and installing the battery It is collinear with the disassembly direction, which is convenient for the operator to disassemble and install the battery.

In the center of the top of the fuselage, an avionics box 26 and an avionics cover plate 27 matched with the avionics box 26 are provided. The avionics box is used to install the avionics module including the GPS module. Open the avionics cover to maintain the avionics module inside. In this application, the avionics box, avionics cover and its internal avionics modules all use IP54 protection level, so that the avionics modules are effectively protected; the avionics module is integrated inside the body, which is convenient for disassembly and maintenance and maintenance.

In order to prevent battery failure, the application adopts a distributed design of four batteries in parallel. When one of the batteries fails, other batteries can continue to provide power and improve the redundancy of the battery; using a distributed design of four batteries, the corresponding The left and right of the four vertical slots are symmetrically distributed on the fuselage, so that the center of the mass body composed of 4 batteries is on the center line of the logistics drone, improving flight stability.

Further, the fuselage 1 can also be detachably connected to a cargo warehouse 19, which is located below the fuselage 1. The cargo warehouse 19 is provided with a plurality of hooks on the top, and the side or bottom of the fuselage is provided with a snap slot adapted to the hook, so as to realize quick disassembly and installation between the cargo warehouse and the fuselage.

Further, a support foot 20 is connected to the bottom of the fuselage 1, and an antenna 21 is provided inside the support foot.

As shown in FIG. 4, the top of the support foot 20 is open, and the support foot has a hollow accommodating cavity, and the accommodating cavity has a built-in connection seat 22, and an antenna 21 is installed on the connection seat 22.

In this application, the antenna is placed in the receiving cavity inside the support foot of the drone, and the space of the support foot is used to avoid the interference of the conductive device inside the fuselage on the performance of the antenna, to ensure the performance of the antenna, and does not need to be protected The antenna is provided with additional components to reduce the weight of the drone.

The supporting leg 20 includes a first side plate and a first flange portion 23 connected to the top of the first side plate. The first flange portion 23 and the first side plate are bent at a right angle; the connecting base 22 includes a second The side panel, the bottom plate 25 connected to the bottom of the second side panel, and the second flange portion 24 connected to the top of the second side panel, the second flange portion 24 overlaps the surface of the first flange portion 23, and the antenna 21 is fixed The end is connected to the bottom plate 25; the bottom end of the first side plate is lower than the bottom end of the second side plate. The bottom plate 25, the first side plate, and the bottom of the support leg 20 form a cavity for accommodating the antenna. The cavity forms a protection for the antenna. Depending on the size of the antenna, a first side plate and a second side plate of appropriate length are provided. In this embodiment, the connecting base 22 is lapped on the support foot 20, which has a simple structure and facilitates the installation of the antenna.

Further, at least two screw holes are correspondingly provided on the second flanged portion 24 and the first flanged portion 23, so as to realize the connection between the support foot, the connection base for installing the antenna and the bottom of the drone fuselage.

Further, the width of the second crimping portion 24 is not less than the width of the first crimping portion 23 to ensure that the connecting base can be securely connected to the supporting leg, and to prevent the connecting base from falling off the first crimping portion at the top of the supporting leg.

Further, a plurality of notches are evenly arranged on the edge of the first folded portion 23, and the notch exposes the second folded portion 24. When the antenna is disassembled and repaired, it is convenient to hold the second folded portion by hand to take out the antenna Connecting seat.

Further, the outer surface of the second side plate conforms to the inner surface of the first side plate to prevent the connecting seat 22 from moving in the accommodating cavity, and also to facilitate the alignment and connection between the supporting feet and the screw holes on the connecting seat.

Further, the accommodating cavity is a cylindrical cavity with no dead angle structure to ensure good communication between the antenna and external communication equipment.

Further, the support foot 20 is a tube made of non-shielding material, and cooperates with the cylindrical receiving cavity to ensure good communication between the antenna and external communication equipment.

According to the above technical solution, this application uses a chevron frame to build the rotor shaft, which has a simple structure, high rigidity and low weight; the battery assembly and disassembly adopts the top-down straight insertion design, and the battery's own gravity has a certain locking effect on the battery installation The cargo compartment and the fuselage can be installed separately, which can quickly load the cargo when unloading and loading the cargo, improving the operating efficiency; the supporting legs that constitute the landing gear are equipped with antennas, forming an integrated design of landing gear and antenna, centralized layout, saving materials and weight.

The above description is only the preferred embodiment of the present application and the explanation of the applied technical principles. Those skilled in the art should understand that the scope of the invention involved in this application is not limited to a technical solution formed by a specific combination of the above technical features, but should also cover the above technical features or theirs without departing from the inventive concept. Other technical solutions formed by any combination of equivalent features. For example, a technical solution formed by replacing the above features with technical features disclosed in this application (but not limited to) but having similar functions.

Claims

A logistics drone, including a fuselage, characterized in that it also includes four rotor shafts that penetrate the fuselage and are arranged in a zigzag pattern, and two ends of the rotor shaft respectively extend out of the fuselage. Rotors are respectively connected to the two ends of the rotor shaft. The four rotor shafts include two oppositely arranged first rotor shafts and two oppositely arranged second rotor shafts. The first rotor shaft is located on the second rotor Above the shaft.
The logistics drone according to claim 1, wherein the second rotor shaft is disposed next to the first rotor shaft, and between the adjacent first rotor shaft and the second rotor shaft It is connected and fixed to the fuselage through a first connecting piece.
The logistics drone according to claim 2, characterized in that the first connecting member includes a first sleeve and a second sleeve connected to an outer side wall of the first sleeve, the first set The axis of the barrel is perpendicular to the axis of the second sleeve, the first sleeve is sleeved with the first rotor shaft, the second sleeve is sleeved with the second rotor shaft, the A reinforcing rib is provided between the first sleeve and the second sleeve.
The logistics unmanned aerial vehicle according to claim 3, characterized in that the first connecting member is an integrally formed structure.
The logistics drone according to claim 2, characterized in that between the adjacent first rotor shaft and the second rotor shaft, the portion of the first rotor shaft protruding from the fuselage A second connecting member is further provided between the portion of the second rotor shaft that protrudes from the fuselage.
The logistics drone according to claim 5, wherein the second connecting member includes a first connecting portion detachably connected to the first rotor shaft, and a detachably connected to the second rotor shaft A second connection portion and a third connection portion connecting the first connection portion and the second connection portion, the first connection portion and the third connection portion are bent and connected, and the second connection portion The third connection portion is bent and connected.
The logistics drone according to claim 6, characterized in that the third connecting portion is an elongated connecting rod, and the first connecting portion includes a first U-shaped card connected to the third connecting portion A seat and a first cover plate butt jointed with the first U-shaped seat, the second connection portion includes a second U-shaped seat connected to the third connection portion and the second U-shaped seat In the butted second cover plate, the first U-shaped holder, the third connecting portion, and the second U-shaped holder are an integrally formed structure.
The logistics drone according to claim 1, wherein a vertical slot for installing a battery is provided on the top of the fuselage.
The logistics drone according to claim 1, wherein the fuselage can also be detachably connected to a cargo warehouse, and the cargo warehouse is located below the fuselage.
The logistics drone according to claim 1, wherein a support foot is connected to the bottom of the fuselage, and an antenna is provided inside the support foot.