WO2018049720A1 - Ensemble bras d'aéronef pour aéronef, et aéronef - Google Patents

Ensemble bras d'aéronef pour aéronef, et aéronef Download PDF

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Publication number
WO2018049720A1
WO2018049720A1 PCT/CN2016/104593 CN2016104593W WO2018049720A1 WO 2018049720 A1 WO2018049720 A1 WO 2018049720A1 CN 2016104593 W CN2016104593 W CN 2016104593W WO 2018049720 A1 WO2018049720 A1 WO 2018049720A1
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WO
WIPO (PCT)
Prior art keywords
opening
arm
air guiding
aircraft
arm housing
Prior art date
Application number
PCT/CN2016/104593
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English (en)
Chinese (zh)
Inventor
冯建刚
王震
Original Assignee
深圳市大疆创新科技有限公司
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 深圳市大疆创新科技有限公司 filed Critical 深圳市大疆创新科技有限公司
Publication of WO2018049720A1 publication Critical patent/WO2018049720A1/fr

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    • 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
    • B64U10/14—Flying platforms with four distinct rotor axes, e.g. quadcopters
    • 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
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/08—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U20/00—Constructional aspects of UAVs
    • B64U20/90—Cooling

Definitions

  • the present invention relates to the field of aircraft, and more particularly to an arm assembly and an aircraft to which the arm assembly is applied.
  • the technical problem to be solved by the present invention is to provide an arm assembly of an aircraft and an aircraft, which can improve the heat dissipation capability of the aircraft.
  • a technical solution adopted by the present invention is to provide an arm assembly of an aircraft, the arm assembly including an arm housing and a wind guiding mechanism, and a cavity is formed in the arm housing.
  • the arm housing is provided with an opening, the opening is in communication with the cavity, and the air guiding mechanism is disposed on the arm housing and corresponds to the opening to pass the arm The air flow of the housing is guided.
  • the arm assembly is for supporting a propeller
  • the opening is formed at a lower side of the arm assembly to allow the external airflow generated by the propeller during rotation to pass through the opening and the machine
  • the cavities of the arm housing are in communication.
  • the air guiding mechanism is embedded in the opening.
  • the arm housing comprises an upper arm housing and a lower arm housing.
  • the air guiding mechanism includes at least one air guiding plate, and two ends of the air guiding plate are connected to the opening.
  • the opening has a length direction, the length direction is consistent with the length direction of the arm assembly, the air deflector has at least two, and the at least two air deflectors are spaced along the length direction. .
  • the opening comprises a first opening and a second opening, the first opening and the second opening are spaced apart, and the first opening and the second opening are along the middle of the arm
  • the air guiding mechanism includes a first air guiding portion and a second air guiding portion, the first air guiding portion is mounted on the first opening, and the second air guiding portion is mounted on On the second opening.
  • the air deflector is disposed obliquely with respect to a cross section of the opening.
  • the arm housing and the air guiding mechanism are provided with a fitting mechanism that cooperates with each other, and the air guiding mechanism is fixed to the arm housing.
  • the assembly mechanism includes a mounting hole and a mounting post, the mounting hole is disposed on the air guiding mechanism, the mounting post is disposed on the arm housing, and the mounting post is inserted into the mounting hole Further, the air guiding mechanism is fixed to the arm housing.
  • the present invention also provides an aircraft comprising a body, a propeller and the arm assembly according to any one of claims 1 to 10, wherein the body forms a cavity, the arm An assembly is coupled to the body, the cavity is in communication with the cavity, and the propeller is disposed at an end of the arm assembly.
  • the propeller is disposed on an upper side of the arm housing, and the air guiding mechanism is disposed on a lower side of the arm housing.
  • the air guiding mechanism is located between the propeller and the body.
  • the aircraft is a multi-rotor unmanned aerial vehicle.
  • the invention has the beneficial effects that the invention is different from the prior art, and the invention provides an arm housing and an air guiding mechanism on the arm assembly, wherein the arm housing is provided with an opening, and the air guiding mechanism is connected to the opening By guiding the external airflow entering the inside of the arm housing, the heat dissipation capability of the aircraft can be effectively improved.
  • FIG. 1 is a schematic view showing the assembly of a boom assembly according to a first embodiment of the present invention
  • FIG. 2 is a schematic exploded view of a boom assembly according to a first embodiment of the present invention
  • FIG. 3 is a schematic structural view of an air guiding mechanism in an arm assembly according to a first embodiment of the present invention
  • Figure 4 is a partial perspective view of the arm housing in the arm assembly according to the first embodiment of the present invention.
  • Figure 5 is an enlarged view of A of Figure 2;
  • Figure 6 is a schematic structural view of an aircraft according to a second embodiment of the present invention.
  • Figure 7 is a schematic diagram of airflow analysis of an aircraft in accordance with a second embodiment of the present invention.
  • FIG. 1 is a schematic view showing the assembly of the arm assembly 10 according to the first embodiment of the present invention
  • FIG. 2 is a disassembled schematic view of the arm assembly 10 according to the first embodiment of the present invention
  • the arm assembly 10 includes an arm housing 12 and an air guiding mechanism 14 (see FIG. 2) disposed inside the arm housing 12, and a cavity 121 is formed in the arm housing 12, and the arm housing is formed.
  • the body 12 is provided with an opening 122, and the opening 122 communicates with the cavity 121.
  • the arm assembly 10 is for supporting the propeller 20, and the opening 122 is opened on the lower side of the arm assembly 10 to allow the external airflow generated by the propeller 20 during the rotation to communicate with the cavity 121 of the arm housing 12 through the opening 122.
  • an external lower temperature airflow may enter the cavity 121 to reduce the temperature in the cavity 121, or an internal higher temperature airflow exiting the cavity 121, also causing the temperature in the cavity 121. Can be reduced.
  • the arm housing 12 includes an upper arm housing 124 and a lower arm housing 126 that cooperate with each other.
  • the upper arm housing 124 and the lower arm housing 126 abut each other to form a cavity 121.
  • the opening 122 is disposed on the lower arm housing 126 and located within the cavity 121.
  • FIG. 2 in order to clearly show the configuration inside the arm assembly 10, the upper arm housing 124 is removed.
  • an opening 122 is defined in the lower arm housing 126 to allow the screw
  • the external airflow generated by the propeller 20 during the rotation enters the inside of the arm housing 12 through the opening 122.
  • the propeller 20 and the opening 122 are respectively located on both sides of the arm housing 12.
  • the air guiding mechanism 14 is disposed inside the arm housing 12, optionally embedded in the hole wall of the opening 122, thereby guiding the external airflow entering the arm housing 12 through the opening 122. Specifically, the air guiding mechanism 14 is disposed at the opening 122 of the lower arm housing 126 and is located in the cavity 121 formed by the upper arm housing 124 and the lower arm housing body 126 abutting each other.
  • the heat dissipation capability of the aircraft can be effectively improved.
  • FIG. 3 is a schematic structural view of the air guiding mechanism 14 in the arm assembly 10 according to the first embodiment of the present invention
  • FIG. 4 is a machine in the arm assembly 10 according to the first embodiment of the present invention.
  • the air guiding mechanism 14 includes at least one air guiding plate 142. As can be seen in FIG. 3, two sets of air guiding plates 142 are disposed in the air guiding mechanism 14, and correspondingly on the lower arm housing 126. Two openings 122 are provided (refer to a partial perspective view of the arm housing of FIG. 4).
  • the opening 122 has a longitudinal direction, and the longitudinal direction is consistent with the longitudinal direction of the arm assembly.
  • the air deflector 142 has at least two, and at least two air guiding plates 142 are spaced apart in the longitudinal direction.
  • the opening 122 includes a first opening 1222 and a second opening 1224.
  • the first opening 1222 and the second opening 1224 are spaced apart, and the first opening 1222 and the second opening 1224 are axisymmetric.
  • the air guiding mechanism 14 includes a first air guiding portion 146 and a second air guiding portion 147, and a connecting portion 148 connecting the first air guiding portion 146 and the second air guiding portion 147.
  • the first air guiding portion 146 is mounted.
  • the second air guiding portion 147 is disposed on the second opening 1224.
  • the first air guiding portion 146 includes a first peripheral wall 1462 and a first air guiding plate 1422, and both ends of the first air guiding plate 1422 are connected to the first peripheral wall 1462.
  • the second air guiding portion 147 includes a second peripheral wall 1472 and a second air guiding plate 1424, and both ends of the second air guiding plate 1424 are connected to the second peripheral wall 1462.
  • Figure 5 is an enlarged view of A of Figure 2 .
  • the arm shell The body 12 and the air guiding mechanism 14 are provided with mutually fitting mounting mechanisms, and the air guiding mechanism 14 is fixed to the arm housing 12.
  • the assembly mechanism includes an assembly hole 144 and an assembly post 128.
  • the fitting hole 144 is disposed on the connecting portion 148 of the air guiding mechanism 14, and the mounting post 128 is disposed on the lower arm housing 126.
  • the specific connection between the air guiding mechanism 14 and the opening 122 is such that the first peripheral wall 1462 of the first air guiding portion 146 is embedded inside the hole wall of the first opening 1222, and the second peripheral wall 1472 of the second air guiding portion 147 is embedded.
  • the inner side of the hole wall of the second opening 1224 is disposed, and the mounting post 128 is inserted into the mounting hole 144, and the air guiding mechanism 14 is fixed to the lower arm housing body 126.
  • the number of air deflectors 142 and the number of openings 122 may be set according to specific use conditions, and are not limited by the above examples.
  • the air deflector 142 is disposed obliquely with respect to the cross section of the opening 122, and the angle of inclination is between 0 and 90 degrees.
  • the inclination angle of the air deflector 142 can be adjusted according to the external environment: when the external ambient temperature is high, for example, in a low latitude region, the tilt angle can be appropriately adjusted to increase the introduced air volume; and the external ambient temperature is higher. At low altitudes, such as high latitudes, the tilt angle can be appropriately adjusted to reduce the amount of air introduced, and even the air deflector 142 can be closed to avoid internal heat dissipation and the machine is at a good operating temperature.
  • FIG. 6 is a schematic structural view of an aircraft according to a second embodiment of the present invention
  • FIG. 7 is a schematic diagram of airflow analysis of an aircraft according to a second embodiment of the present invention.
  • the aircraft may be a drone or other aircraft and includes a body 30, a propeller 20A, and an arm assembly 10A.
  • a cavity 32 is formed in the body 30, the arm assembly 10A is connected to the body 30, the cavity 32 is in communication with the cavity 121A, the propeller 20A is disposed on the arm assembly 10A, and the arm assembly 10A is provided with an opening 122A for guiding the wind.
  • the mechanism 14A is arranged to direct the external airflow entering the interior of the arm housing 12A through the opening 122A toward the body 30 (as specifically shown in Figure 7).
  • the propeller 20A is disposed on the upper side of the arm housing 12A
  • the air guiding mechanism 14A is disposed on the lower side of the arm housing 12A
  • the air guiding mechanism 14A is disposed in the middle of the arm assembly 10A and located at the propeller 20A and the body. Between 30.
  • the lower arm housing 126A on the lower side of the arm housing 12A is provided with an opening 122A and is engaged with the air guiding mechanism 14A.
  • the airflow enters the arm housing 12A through the opening 122A of the lower arm housing body 126A, and flows to the cavity 32 inside the body 30 through the air guiding mechanism 14A, and then the air body 30 is driven by the propeller 20A.
  • the internal components achieve the effect of heat dissipation.

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

Abstract

La présente invention porte sur un ensemble bras d'aéronef pour un aéronef et sur un aéronef, l'ensemble bras d'aéronef (10) pour l'aéronef comprenant un logement de bras d'aéronef (12) et un mécanisme de guidage d'air (14), le logement de bras d'aéronef (12) étant pourvu intérieurement d'une cavité (121), le logement de bras d'aéronef (12) étant pourvu d'un trou d'ouverture (122), le trou d'ouverture (122) étant en communication avec la cavité (121), et le mécanisme de guidage d'air (14) étant disposé sur le logement de bras d'aéronef (12) et correspondant au trou d'ouverture (122), de façon à guider un flux d'air passant à travers le logement de bras d'aéronef (12). Le mécanisme de guidage d'air (14) est raccordé au trou d'ouverture (122), de façon à guider un flux d'air externe entrant dans l'intérieur du logement de bras d'aéronef (12), ce qui permet d'améliorer efficacement la capacité de dissipation de chaleur de l'aéronef.
PCT/CN2016/104593 2016-09-14 2016-11-04 Ensemble bras d'aéronef pour aéronef, et aéronef WO2018049720A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CN201621058145.8U CN206141808U (zh) 2016-09-14 2016-09-14 一种飞行器的机臂组件以及飞行器
CN201621058145.8 2016-09-14

Publications (1)

Publication Number Publication Date
WO2018049720A1 true WO2018049720A1 (fr) 2018-03-22

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WO (1) WO2018049720A1 (fr)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN206141808U (zh) * 2016-09-14 2017-05-03 深圳市大疆创新科技有限公司 一种飞行器的机臂组件以及飞行器
CN108995818A (zh) * 2017-06-07 2018-12-14 深圳光启合众科技有限公司 涵道风扇
WO2019127390A1 (fr) * 2017-12-29 2019-07-04 深圳市大疆创新科技有限公司 Ensemble bras pour véhicule aérien sans pilote, et véhicule aérien sans pilote
CN113093188B (zh) * 2021-04-02 2022-01-11 滁州学院 一种基于无人机遥感的农作物种类识别系统

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN103863548A (zh) * 2014-03-26 2014-06-18 重庆金泰航空工业有限公司 一种四轴式飞行装置顶盖与机身组合
US20140231582A1 (en) * 2012-10-03 2014-08-21 Sean Headrick Methods and Systems of Constructing a Multi Rotor Aircraft Fuselage
CN203793607U (zh) * 2014-03-26 2014-08-27 重庆金泰航空工业有限公司 农用无人飞行器电子调速器布置结构
CN104919139A (zh) * 2013-01-09 2015-09-16 联合工艺公司 机翼和制造方法
CN204642144U (zh) * 2015-04-30 2015-09-16 深圳市大疆创新科技有限公司 无人机
CN105939930A (zh) * 2015-04-30 2016-09-14 深圳市大疆创新科技有限公司 热管理系统及热管理方法，及应用该热管理系统的无人机
CN206141808U (zh) * 2016-09-14 2017-05-03 深圳市大疆创新科技有限公司 一种飞行器的机臂组件以及飞行器

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20140231582A1 (en) * 2012-10-03 2014-08-21 Sean Headrick Methods and Systems of Constructing a Multi Rotor Aircraft Fuselage
CN104919139A (zh) * 2013-01-09 2015-09-16 联合工艺公司 机翼和制造方法
CN103863548A (zh) * 2014-03-26 2014-06-18 重庆金泰航空工业有限公司 一种四轴式飞行装置顶盖与机身组合
CN203793607U (zh) * 2014-03-26 2014-08-27 重庆金泰航空工业有限公司 农用无人飞行器电子调速器布置结构
CN204642144U (zh) * 2015-04-30 2015-09-16 深圳市大疆创新科技有限公司 无人机
CN105939930A (zh) * 2015-04-30 2016-09-14 深圳市大疆创新科技有限公司 热管理系统及热管理方法，及应用该热管理系统的无人机
CN206141808U (zh) * 2016-09-14 2017-05-03 深圳市大疆创新科技有限公司 一种飞行器的机臂组件以及飞行器

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