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WO2020015695A1 - Véhicule aérien sans pilote à soufflante carénée et son boîtier - Google Patents

Véhicule aérien sans pilote à soufflante carénée et son boîtier Download PDF

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Publication number
WO2020015695A1
WO2020015695A1 PCT/CN2019/096486 CN2019096486W WO2020015695A1 WO 2020015695 A1 WO2020015695 A1 WO 2020015695A1 CN 2019096486 W CN2019096486 W CN 2019096486W WO 2020015695 A1 WO2020015695 A1 WO 2020015695A1
Authority
WO
WIPO (PCT)
Prior art keywords
casing
culvert
skeleton
fuselage
drone
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Ceased
Application number
PCT/CN2019/096486
Other languages
English (en)
Chinese (zh)
Inventor
马罡
徐彬
项昌乐
金健侠
刘子铭
刘春桃
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Cool High-Tech Beijing Co Ltd
Original Assignee
Cool High-Tech Beijing Co Ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Cool High-Tech Beijing Co Ltd filed Critical Cool High-Tech Beijing Co Ltd
Publication of WO2020015695A1 publication Critical patent/WO2020015695A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/20—Rotorcraft characterised by having shrouded rotors, e.g. flying platforms
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D47/00—Equipment not otherwise provided for
    • B64D47/08—Arrangements of cameras
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00—Type of UAV
    • B64U10/10—Rotorcrafts
    • B64U10/13—Flying platforms
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U30/00—Means for producing lift; Empennages; Arrangements thereof
    • B64U30/20—Rotors; Rotor supports
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U50/00—Propulsion; Power supply
    • B64U50/10—Propulsion
    • B64U50/13—Propulsion using external fans or propellers
    • B64U50/14—Propulsion using external fans or propellers ducted or shrouded
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U2101/00—UAVs specially adapted for particular uses or applications
    • B64U2101/30—UAVs specially adapted for particular uses or applications for imaging, photography or videography

Definitions

  • the invention relates to the technical field of design and production of unmanned aerial vehicles, in particular to a ducted unmanned aerial vehicle and its casing.
  • the traditional UAV has a complex curved surface and the propeller protrudes from the fuselage, so its structure is more complex, its weight is difficult to be smaller, and customized production is required, resulting in higher production costs.
  • the ducted drone is small and easy to carry.
  • the casing of the ducted drone is usually made of engineering plastics. Although it meets the strength requirements of the entire drone, its overall weight is still large, which leads to The drone's range is small.
  • the present invention discloses a ducted drone housing.
  • the body includes a shell formed by foaming a foamed material, and a rigid load-carrying skeleton built into the shell.
  • the invention also discloses a ducted drone, which includes a casing and a ducted fan arranged in the casing, and the casing is the casing disclosed in any one of the above.
  • the shell of the ducted drone disclosed in the present invention adopts a mode of combining a foamed shell and a hard bearing skeleton.
  • the hard bearing skeleton ensures the strength of the entire shell, and the drone has a large weight.
  • the power motors, flight controllers, and electronic governors are installed on the rigid load-carrying frame.
  • the foamed shell is mainly used to fill the outer shape of the shell, and to ensure the accuracy of the aerodynamic shape of the duct. It can also be used for Install lighter attachments.
  • This kind of casing not only meets the requirements for the strength of the ducted drone, but also effectively reduces the overall weight. With the same battery capacity, it can effectively increase the cruising range of the drone, and its production The process is simple and the production cost is low, which meets the process requirements for mass production.
  • FIG. 1 is a schematic diagram of the overall structure of an angled drone disclosed in an embodiment of the present invention
  • FIG. 2 is a schematic diagram of the overall structure of a ducted drone disclosed in another embodiment of the present invention from another angle;
  • FIG. 4 is a schematic structural diagram of the front side in FIG. 2;
  • FIG. 5 is a schematic structural diagram of a left side in FIG. 2;
  • FIG. 8 is a schematic structural diagram of a hard supporting skeleton disclosed in an embodiment of the present invention.
  • 1 is the shell
  • 2 is the ducted hole
  • 3 is the ducted protective cover
  • 4 is the infrared lighting
  • 5 is the camera
  • 6 is the positioning groove
  • 7 is the positioning protrusion
  • 8 is the fuselage skeleton
  • 9 is the culvert.
  • Road support ring 10 is the support rod
  • 11 is the upper foam shell
  • 12 is the lower foam shell
  • 13 is the motor
  • 14 is the fan
  • 15 is the fan fixing nut
  • 16 is the fairing
  • 17 is the brushless electronic adjustment Speed device
  • 18 is the canal tail vertebra
  • 19 is the airborne ammunition
  • 20 is the battery
  • 21 is the flight controller
  • 22 is the bearing orifice
  • 23 is the connecting rod.
  • Another core of the present invention is to provide a ducted drone using the above-mentioned casing.
  • the casing of the ducted drone disclosed in the present invention includes a casing 1 and a skeleton, wherein the casing 1 is a foamed casing formed of a foamed material, and the skeleton is built-in A rigid load-bearing skeleton in the housing 1.
  • the casing of the ducted drone disclosed in the present invention adopts a pioneering mode of combining a foamed shell and a rigid bearing skeleton.
  • the rigid bearing skeleton ensures the strength of the entire casing.
  • the heavy-duty power motors, flight controllers, and electronic governors of the UAV are installed on the rigid load-carrying skeleton; the foam shell is mainly used to fill the outer shape of the shell and ensure the aerodynamic shape of the duct.
  • the accuracy can also be used to install some light weight accessories.
  • This kind of casing not only meets the requirements for the strength of the ducted drone, but also effectively reduces the overall weight. With the same battery capacity, it can effectively increase the cruising range of the drone, and its production The process is simple and the production cost is low, which meets the process requirements for mass production.
  • the casing 1 includes an upper foamed casing 11 and a lower foamed casing 12, and after the upper foamed casing 11 and the lower foamed casing 12 are fastened together, the interior of the casing 1 is formed into a shape of a rigid supporting skeleton.
  • the upper foam shell 11 and the lower foam shell 12 are connected by fasteners, or they are snapped together, or bonded.
  • the shape of the casing 1 is not limited. In order to improve the ability of the ducted drone to pass through a narrow space, the shape of the casing 1 in this embodiment is preferably a rectangular parallelepiped.
  • the hard bearing frame disclosed in this embodiment includes a fuselage frame 8, a duct support ring 9 and a motor support frame.
  • the fuselage frame 8 extends in the longitudinal direction of the drone.
  • the role of 8 is to provide strength support for the entire rigid load-carrying skeleton, and at the same time provide the installation foundation for other components.
  • the role of the motor support frame is to provide a mounting base for the motor 13
  • the motor support frame is arranged in the duct support ring 9, and the casing 1 is provided with duct holes on the top and bottom surfaces in the thickness direction. 2.
  • the culvert hole 2 and the culvert support ring 9 are provided in a one-to-one correspondence.
  • the longitudinal direction of the drone refers to a forward direction of the drone during flight
  • the lateral direction of the drone refers to a direction perpendicular to the forward direction
  • a plurality of duct support rings 9 on either side of the fuselage skeleton 8 are provided, and the centers of the duct support rings 9 on the same side are located on the same straight line.
  • the longitudinal direction of the drone is parallel; of course, most of the duct support rings 9 on the same side may be located on the same straight line.
  • the culvert support ring 9 may be a square ring, a polygonal ring, etc.
  • the culvert support ring 9 in this embodiment is specifically a circular ring.
  • the motor support frame includes a motor bearing sleeve and a plurality of struts 10, and the motor bearing sleeve is located on the culvert.
  • the center of the support ring 9 ensures that the axis of the motor and the axis of the ducted support ring 9 are arranged concentrically.
  • the support rods 10 are distributed in the ducted support ring 9 in the circumferential direction, and one end of the support rod 10 is connected to the ducted support ring.
  • the inner wall of 9 is connected, and the other end is connected to the motor bearing sleeve, so that the motor bearing sleeve is firmly supported in the center of the duct support ring 9.
  • the motor 13 is built into the motor bearing sleeve.
  • a fan 14 is installed on the output shaft of the motor 13, and the fan 14 is fastened to the output shaft of the motor 13 through a fan fixing nut 15.
  • the tail end of the motor is installed There is a ductus coccyx 18.
  • the included angle between any two adjacent support rods 10 is equal, that is, the support rods 10 are evenly distributed in the support support ring 9, which is more specific
  • the two support rods 10 form a longitudinal diameter that passes through the center of the culvert support ring 9 and is parallel to the longitudinal direction of the casing (or drone).
  • Rod, the other two support rods 10 form a transverse diameter rod that passes through the center of the duct support ring and is perpendicular to the longitudinal direction of the casing (or drone), and a longitudinal diameter rod and a transverse diameter rod in each duct support ring 9 It is connected to an integrated structure.
  • the longitudinal diameter rods in the duct support ring 9 on the same side of the fuselage frame 8 connect the duct support ring on the same side to an integrated structure.
  • the shell also includes The horizontally extending connecting rods 23 of the human machine and the duct support rings on both sides of the fuselage frame 8 are connected by the connecting rods 23 passing through the fuselage frame 8.
  • the duct support ring 9 is divided into two groups by the fuselage skeleton 8.
  • the duct support rings 9 located on the same side of the fuselage skeleton 8 form a group.
  • two adjacent The outer edges of the root culvert support ring 9 are fixedly connected to each other as a whole, and in the same group of culvert support rings 9, the culvert support ring 9 is symmetrical about the transverse mid-axis of the fuselage skeleton 8.
  • the so-called lateral mid-axis means that the mid-axis extends in the transverse direction of the drone and passes through the midpoint of the fuselage skeleton 8. So far, the bypass support ring 9 is not only about the longitudinal symmetrical setting of the drone, but also about Horizontal symmetrical setting of drone.
  • this embodiment further includes a bearing orifice plate 22, which is fastened to the bottom of the fuselage frame 8 and connected to two vertical orifice plates to carry the orifice plate 22.
  • a battery installation cavity is formed by enclosing the vertical hole plate.
  • the battery 20 is built in the battery installation cavity.
  • a hole for heat dissipation is also provided on the bearing hole plate 22.
  • a plurality of heat dissipation holes are arranged in parallel with each other. As shown in Figure 8.
  • the center of the duct support ring 9 located in the middle is located in the lateral direction of the casing.
  • the horizontal mid-axis of the casing and the horizontal mid-axis of the fuselage skeleton 8 are the same straight line.
  • the two segments constituting the fuselage skeleton 8 are equal in length.
  • the mounting groove for mounting the flight controller 21 is shown in FIGS.
  • the center of the mounting groove is located on the lateral mid-axis of the casing, and the lateral diameter rod in the middle of the bypass support ring 9 penetrates
  • the flight controller 21 is embedded in the mounting groove and is mounted on a transverse diameter rod.
  • the casing 1 should be provided with six duct holes 2 corresponding to the duct support ring 9.
  • the six duct holes 2 constitute two rows of duct holes parallel to the longitudinal direction of the shell.
  • the duct The diameter of hole 2 is D.
  • the distance between the centers of two adjacent culvert holes 2 is L 1 , where 21D / 20 ⁇ L 1 ⁇ 3D / 2 ;
  • the distance between the two rows of the bypass channel is L 2 , where 21D / 20 ⁇ L 2 ⁇ 3D / 2, the center of any one of the bypass channels 2 is adjacent to the bypass channel 2
  • the distance between the edges of the shell is L 3 , where 11D / 20 ⁇ L 3 ⁇ 3D / 5.
  • the fuselage ducted same side of the backbone 8 supporting an outer circumference of the fuselage skeleton ring 9 as the closest distance between 8 L 4, wherein, 1D / 20 ⁇ L 4 ⁇ 1D / 2 .
  • installation space for the brushless electronic governor 17 is left at the two symmetrical end positions of the fuselage skeleton 8.
  • the brushless electronic governor 17 is installed therein, and is the same as the fuselage skeleton 8.
  • an ammunition mounting bracket is also provided in the area formed between two adjacent ducting support rings 9 and the fuselage skeleton 8.
  • the ammunition mounting bracket may be specifically designed to be circular, and the ammunition mounting bracket and the fuselage skeleton 8 and The outer circle of at least one of the two ducted support rings 9 is tangent.
  • the ducted drone can also perform special combat tasks.
  • the upper surface of the motor support frame is also covered with a fairing 16 to improve the airflow characteristics in the ducted hole 2 and to protect the fan 14 and avoid the fan blades Collision with external objects, and at the same time prevent flying objects such as sand, dust and debris from entering the duct hole 2.
  • a duct protection cover 3 is also installed in the air inlet and outlet of the duct hole 2.
  • the duct protective cover 3 is substantially flush with the upper surface and the lower surface of the casing 1.
  • the duct protective cover 3 may be provided only in the air inlet or the air outlet of the duct 2.
  • the foaming material may be foam
  • the rigid supporting frame may be engineering plastic, or a metal material (such as aluminum alloy) with a small density and sufficient strength, or a carbon fiber or glass. Fiber, etc., the casing not only meets the requirements for the strength of the ducted drone, but also effectively reduces the overall weight. With the same battery capacity, it can effectively increase the drone's cruising range.
  • the production process is simple and the production cost is low, which meets the technical requirements for mass production.
  • a ducted drone is disclosed in the embodiment of the present invention.
  • the ducted drone adopts the casing disclosed in any one of the above embodiments.
  • a plurality of mounting openings are provided on the side of the casing.
  • the mounting opening is provided with an infrared illuminating light 4 and a camera 5 for image acquisition.
  • the number and setting of the camera 5 and the infrared illuminating light 4 The position and the like are not limited, and can be adaptively designed according to the actual use of the drone.
  • the infrared illuminator 4 and the camera 5 are disposed on the side or the bottom of the housing 1, as shown in FIG. 5, the camera 5 is arranged near the longitudinal central axis or is located on the longitudinal central axis.
  • the infrared illuminating lamps 4 are specifically two, which are respectively located on two sides of the camera 5.
  • one of the top surface and the bottom surface of the housing 1 is provided with a positioning groove 6, and the other is provided with a positioning protrusion 7 corresponding to the position of the positioning groove 6 in the thickness direction of the housing, and the positioning concave
  • the groove 6 is recessed toward the inside of the housing 1, the positioning protrusion 7 is protruded toward the outside of the housing 1, and the positioning protrusion 7 can be adapted to the positioning groove 6.
  • the shape of the positioning groove 6 in the above embodiment is not limited.
  • the positioning groove 6 may be a circular groove, a rectangular groove, a regular groove, or an irregularly shaped groove.
  • the cross-sectional shape of the positioning protrusion 7 may be the same as or different from the shape of the positioning groove 6, as long as the positioning protrusion 7 in two adjacent drones stacked adjacently can be inserted into the positioning groove 6, and the positioning protrusion 7 and positioning groove 6 can position the drone in the circumferential direction.
  • the ducted fan of the unmanned aerial vehicle disclosed in the above embodiment is disposed inside the casing 1. Since there are no components such as an external propeller and a wing, its own occupied space is significantly reduced; in addition, since the present invention
  • the top and bottom surfaces of the disclosed drones are flat structures, so they are particularly suitable for stacking.
  • the top and bottom surfaces of two unmanned aerial vehicles that are adjacent to each other after stacking fit together, which minimizes space.
  • one of the top surface and the bottom surface of the housing 1 is provided with a positioning groove 6 and the other is provided with a positioning protrusion 7 corresponding to the position of the positioning groove 6 in the thickness direction, After being stacked, the positioning protrusions 7 and the positioning grooves 6 of the two adjacent drones will be mated, thereby playing a role of circumferential limit and effectively avoiding the tilting and sliding of the drone.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Remote Sensing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Toys (AREA)

Abstract

La présente invention concerne un boîtier d'un véhicule aérien sans pilote à soufflante carénée. Le boîtier comprend un boîtier externe formé par moussage d'une mousse, et un cadre de support dur disposé à l'intérieur du boîtier externe. Le boîtier satisfait l'exigence de boîtiers résistants pour un véhicule aérien sans pilote à soufflante carénée, tout en réduisant également son poids total. Le boîtier peut augmenter le kilométrage d'endurance d'un véhicule aérien sans pilote sans changer la capacité de la batterie, son processus de production est simple et ses coûts de production sont faibles. En outre, il satisfait les exigences de traitement de la production en série. La présente invention concerne en outre un véhicule aérien sans pilote à soufflante carénée mettant en œuvre le boîtier.
PCT/CN2019/096486 2018-07-20 2019-07-18 Véhicule aérien sans pilote à soufflante carénée et son boîtier Ceased WO2020015695A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CN201810803894.6A CN108945418A (zh) 2018-07-20 2018-07-20 一种涵道式无人机及其壳体
CN201810803894.6 2018-07-20

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Publication Number Publication Date
WO2020015695A1 true WO2020015695A1 (fr) 2020-01-23

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CN (1) CN108945418A (fr)
WO (1) WO2020015695A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN115541072A (zh) * 2022-10-20 2022-12-30 南京大学 一种爬壁机器人的足部压力检测结构
CN115610545A (zh) * 2022-10-20 2023-01-17 南京大学 一种爬壁机器人的足部结构

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* Cited by examiner, † Cited by third party
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CN108945418A (zh) * 2018-07-20 2018-12-07 酷黑科技（北京）有限公司 一种涵道式无人机及其壳体
CN111942580A (zh) * 2020-09-24 2020-11-17 河南鲲之腾教育科技有限公司 一种穿越机机架及穿越机
CN119190443A (zh) * 2024-11-28 2024-12-27 南京开天眼无人机科技有限公司 组装式壳体及应用该壳体的飞行救生圈

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN115541072A (zh) * 2022-10-20 2022-12-30 南京大学 一种爬壁机器人的足部压力检测结构
CN115610545A (zh) * 2022-10-20 2023-01-17 南京大学 一种爬壁机器人的足部结构
CN115541072B (zh) * 2022-10-20 2023-09-22 南京大学 一种爬壁机器人的足部压力检测结构

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