WO2021196138A1 - Dispositif de dissipation de chaleur pour cabine de véhicule aérien sans pilote - Google Patents

Dispositif de dissipation de chaleur pour cabine de véhicule aérien sans pilote Download PDF

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Publication number
WO2021196138A1
WO2021196138A1 PCT/CN2020/083043 CN2020083043W WO2021196138A1 WO 2021196138 A1 WO2021196138 A1 WO 2021196138A1 CN 2020083043 W CN2020083043 W CN 2020083043W WO 2021196138 A1 WO2021196138 A1 WO 2021196138A1
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WO
WIPO (PCT)
Prior art keywords
heat dissipation
heat
cabin
fin
dissipation device
Prior art date
Application number
PCT/CN2020/083043
Other languages
English (en)
Chinese (zh)
Inventor
杨思强
Original Assignee
南京达索航空科技有限公司
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 南京达索航空科技有限公司 filed Critical 南京达索航空科技有限公司
Publication of WO2021196138A1 publication Critical patent/WO2021196138A1/fr

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U20/00—Constructional aspects of UAVs
    • B64U20/90—Cooling
    • B64U20/96—Cooling using air
    • 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
    • B64D33/10—Radiator arrangement
    • 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
    • B64D9/00—Equipment for handling freight; Equipment for facilitating passenger embarkation or the like
    • H—ELECTRICITY
    • H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
    • H05K—PRINTED CIRCUITS; CASINGS OR CONSTRUCTIONAL DETAILS OF ELECTRIC APPARATUS; MANUFACTURE OF ASSEMBLAGES OF ELECTRICAL COMPONENTS
    • H05K7/00—Constructional details common to different types of electric apparatus
    • H05K7/20—Modifications to facilitate cooling, ventilating, or heating

Definitions

  • the utility model belongs to the technical field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle cabin heat dissipation device.
  • Unmanned aircraft is abbreviated as unmanned aerial vehicle, which is an unmanned aircraft operated by radio remote control equipment and self-provided program control devices.
  • UAV has the advantages of flexibility, rapid response, unmanned flight and easy operation. It is widely used in meteorology, exploration, photography and other fields.
  • the integrated circuit components inside the cabin will generate a lot of heat. If this heat cannot be dissipated in time, it will easily cause the circuit board to overheat and affect the flight stability of the UAV. Therefore, it is necessary to install a heat dissipation device in the drone cabin to promote the rapid dissipation of heat.
  • a heat dissipation device for an unmanned aircraft cabin is provided to solve the above-mentioned problems existing in the prior art.
  • a heat dissipating device for a cabin of an unmanned aerial vehicle comprising: a cabin outer tube fixed on the drone and an inner cabin tube inserted in the cabin outer tube, the top of the cabin outer tube is closed, and the side outer wall of the cabin outer tube is close to One end of the bottom is provided with a fixing part for fixing the heat dissipation device, a plurality of arc-shaped first radiating fins and first heat insulation fins are attached to the side inner wall of the outer cylinder of the engine room; the top of the inner cylinder of the engine room is closed, and the engine room
  • the inner cylinder is fixed with a support plate for fixing the integrated circuit board, the bottom of the engine room inner cylinder is screwed with a bottom plate, and the side outer wall of the engine room inner cylinder is attached with a plurality of second radiating fins and second insulation fins;
  • the outer cylinder of the engine room and the inner cylinder of the engine room are rotatably connected.
  • the first heat radiating fin, the first heat insulation fin, the second heat radiating fin, and the second heat insulation fin are all arc-shaped structures and the arc surface angles are equal; the first heat dissipation fin and the second heat insulation fin The fins are arranged at intervals, and the second heat dissipation fins and the second heat insulation fins are arranged at intervals; the inner diameter of the first heat dissipation fin or the first heat insulation fin is equal to the outer diameter of the second heat dissipation fin or the second heat insulation fin;
  • the relative rotation of the content, the heat sink has two states: heat dissipation and heat preservation; when the heat sink is in the heat dissipation state, the first heat sink overlaps the second heat sink, and the heat in the cabin inner cylinder passes through the first heat sink and the second heat sink When the heat dissipation device is in the heat preservation state, the first heat sink and the second heat sink are in a staggered distribution.
  • the first heat insulation fin and the second heat insulation fin are arranged at intervals to block the heat in the inner cylinder of the engine room. Reduce the speed of heat dissipation.
  • the drone's cabin can have the dual functions of heat dissipation and heat preservation, adapting to flight requirements in different environments.
  • the first heat sink and the second heat sink are made of thermally conductive silicone sheets, which have excellent thermal conductivity and can ensure the heat dissipation effect of the heat sink.
  • the first insulation sheet and the second insulation sheet are made of polystyrene board, and the polystyrene board has a certain insulation performance, which can make the heat dissipation device have a certain insulation performance, so that the drone can adapt to Flying in an alpine environment.
  • a fan is fixed on the top inner wall of the inner cylinder of the nacelle, and a number of heat dissipation holes are opened on the bottom plate along the vertical direction. Dissipate to the outside of the heat dissipation device through the heat dissipation holes, and the cold air outside the heat dissipation device enters the interior of the inner cylinder of the nacelle through the heat dissipation holes, thereby realizing rapid heat dissipation of the heat dissipation device.
  • the heat dissipation hole includes a first through hole near the middle of the bottom plate and a second through hole near the edge of the bottom plate, and the diameter of the top end of the first through hole is larger than the diameter of the bottom end of the first through hole; The diameter of the top end of the second through hole is smaller than the diameter of the bottom end of the second through hole; through this arrangement, the convection of air between the inner cylinder of the nacelle and the outside of the heat dissipation device is promoted, and the heat dissipation effect of the heat dissipation device is improved.
  • the side inner wall of the outer cylinder of the engine room is provided with a first annular groove at one end close to the bottom, and the end of the side outer wall of the inner cylinder of the engine room near the bottom is provided with a second annular groove.
  • the groove and the second annular groove are arranged oppositely, and a number of balls are arranged in the first and second annular grooves; through this arrangement, the relative rotation of the nacelle inner tube and the nacelle outer tube is promoted, and the nacelle inner tube and the nacelle outer tube are reduced Friction and wear during relative rotation.
  • the cooling device for the cabin of the unmanned aerial vehicle provided by the utility model includes: an inner tube of the cabin, an outer tube of the cabin, a first radiating fin, a first insulation fin, a second radiating fin, and a second insulation fin.
  • the inner tube of the nacelle and the outer tube of the nacelle can be relatively rotated, so that the first radiating fin and the second radiating fin are in different distribution states. When the first radiating fin and the second radiating fin overlap, the heat in the inner tube of the nacelle is radiated through the first heat sink.
  • the fins and the second radiating fins quickly conduct and dissipate to promote heat dissipation; when the first and second radiating fins are staggered, the first and second insulation fins heat the inside of the cabin inner tube and reduce the heat dissipation speed .
  • the heat dissipation device for the nacelle of the drone provided by the utility model can increase the heat dissipation speed in the engine nacelle, while also taking into account the heat preservation function, so that the drone can adapt to flight requirements in different environments.
  • Fig. 1 is a schematic diagram of the structure of the heat dissipation device for the nacelle of the unmanned aerial vehicle of the present invention.
  • Figure 2 is a cross-sectional view of the heat dissipation device of the present invention.
  • Fig. 3 is a partial view of the utility model at A in Fig. 2.
  • Fig. 4 is a distribution diagram of the first heat dissipation fin, the first heat insulation fin, the second heat dissipation fin and the second heat insulation fin when the heat dissipation device of the present invention is in a heat dissipation state.
  • Fig. 5 is a distribution diagram of the first heat dissipation fin, the first heat preservation fin, the second heat dissipation fin and the second heat preservation fin when the heat dissipation device of the present invention is in a heat preservation state.
  • Figure 6 is a cross-sectional view of the structure of the bottom plate of the present invention.
  • engine room outer tube 10 fixed portion 11, first annular groove 12, first radiating fin 13, first insulation sheet 14, engine room inner tube 20, second annular groove 21, The second heat sink 22, the second heat insulation sheet 23, the bottom plate 30, the heat dissipation hole 31, the first through hole 311, the second through hole 312, the support plate 40, the balls 50, and the fan 60.
  • UAVs are extremely widely used.
  • the integrated circuit components inside the cabin generate a lot of heat. If it is not discharged in time, the circuit board will easily overheat and affect the flight stability of the UAV.
  • drones sometimes need to adapt to the flying environment in high-cold areas, where the temperature is low, which can easily cause the power supply of the drone to be unstable, cause the drone to have insufficient flight power, and even cause the drone to ground. Falling conditions. Therefore, how to improve the heat dissipation device to ensure the heat dissipation effect while having the heat preservation function has become a problem that needs to be solved urgently.
  • the present invention provides an unmanned aerial vehicle cabin heat dissipation device, as shown in FIG. 1 and FIG.
  • the nacelle outer tube 10 has a cylindrical structure, the top of the nacelle outer tube 10 is closed, and the side outer wall of the nacelle outer tube 10 is provided with a plurality of fixing parts 11 at one end near the bottom.
  • the fixing portion 11 in this embodiment includes a connecting lug, and a connecting through hole is opened on the connecting lug.
  • the outer cylinder 10 of the nacelle is fixed to the unmanned aerial vehicle by setting screws or bolts in the connecting through hole.
  • the nacelle inner tube 20 also has a cylindrical structure. The top of the nacelle inner tube 20 is closed. The bottom inner wall of the nacelle inner tube 20 is provided with internal threads.
  • the bottom of the nacelle inner tube 20 is screwed with a circular bottom plate 30.
  • the side of the bottom plate 30 An external thread is provided, and the external thread is adapted to the internal thread on the bottom of the inner cylinder 20 of the nacelle.
  • the inner cylinder 20 and the bottom plate 30 of the nacelle surround to form a closed containment cavity (not marked in the figure).
  • the containment chamber is provided with a support plate 40, which is fixedly connected to the side inner wall of the nacelle, and the integrated circuit of the drone is installed With the support plate 40 on it.
  • the nacelle inner tube 20 and the nacelle outer tube 10 are relatively rotatable.
  • One end of the side inner wall of the nacelle outer tube 10 close to the bottom is along the first annular groove 12 in the circumferential direction; A second annular groove 21 is opened in the direction.
  • the first annular groove 12 and the second annular groove 21 are arranged oppositely.
  • a number of balls 50 are arranged in the first annular groove 12 and the second annular groove 21.
  • a plurality of arc-shaped first heat dissipation fins 13 and first heat insulation fins 14 are attached to the side inner wall of the outer cylinder 10 of the nacelle.
  • a plurality of arc-shaped second heat dissipation fins 22 and second heat insulation fins 23 are attached to the side outer wall of the inner cylinder 20 of the nacelle.
  • the arc angles of the first heat dissipation fin 13, the first heat insulation fin 14, the second heat dissipation fin 22, and the second heat insulation fin 23 are all equal, which are all 30°.
  • the lengths of the first heat dissipation fin 13, the first heat insulation fin 14, the second heat dissipation fin 22, and the second heat insulation fin 23 in the vertical direction are also equal.
  • the number of the first heat dissipation fins 13 and the first heat insulation fins 14 is equal, and both are six;
  • the numbers of the second heat sink 22 and the second heat insulation piece 23 are also equal, both being six;
  • the second heat sink 22 and the second heat insulation piece 23 are arranged at intervals to cover the lateral outer wall of the inner cylinder 20 of the nacelle.
  • the inner diameter of the first heat dissipation fin 13 or the first heat insulation fin 14 is equal to the outer diameter of the second heat dissipation fin 22 or the second heat insulation fin 23.
  • the heat dissipation device With the relative rotation of the nacelle outer tube 10 and the nacelle inner tube 20, the heat dissipation device has two states of heat dissipation and heat preservation.
  • the first heat sink 13 and the second heat sink 22 overlap, the first heat sink 13 and the second heat sink 22 form a connected thermal bridge. Due to the high thermal conductivity of the first heat sink 13 and the second heat sink 22, the cabin The heat of the content is quickly conducted and dissipated through the second heat sink 22 and the first heat sink 13, so as to realize rapid heat dissipation. At this time, the heat sink is in a heat dissipation state.
  • the first heat insulating fins 14 and the second heat insulating fins 23 are also staggered, and the thermal bridge formed by the first heat sink 13 and the second heat sink 22 is interrupted.
  • An insulation layer formed by a thermal insulation sheet 14 and a second thermal insulation sheet 23 blocks the heat in the inner cylinder 20 of the nacelle, reduces the heat dissipation speed, and keeps the heat dissipation device in a thermal insulation state.
  • the first heat sink 13 and the second heat sink 22 in this embodiment are made of JRF-PM800 thermally conductive silicone sheet, and its thermal conductivity can reach 8.0W/(MK), with excellent thermal conductivity, and can ensure heat dissipation The device quickly dissipates heat.
  • the thermal insulation sheet in this embodiment is made of polystyrene board (also known as polystyrene board), its thermal conductivity is not more than 0.041W/(MK), and has a certain thermal insulation performance, so that the heat dissipation device has a thermal insulation function. Adapt the drone to the alpine environment.
  • the heat in the nacelle inner tube 20 through heat conduction essentially belongs to a passive heat dissipation method, and the heat is dissipated through conduction and radiation.
  • the heat in the inner cylinder 20 of the nacelle first needs to be transferred through the air and then transmitted and dissipated through the second heat sink 22 and the first heat sink 13.
  • This heat dissipation process requires multiple heat transfer media, so a certain heat transfer time is required. Therefore, there is room for improvement in the heat dissipation device proposed by the present invention.
  • a fan 60 is fixed on the top inner wall of the inner cylinder 20 of the nacelle; at the same time, a number of heat dissipation holes 31 are opened on the bottom plate 30 along the vertical direction. .
  • the continuous rotation of the fan 60 promotes the convection of the hot air in the inner cylinder 20 of the engine room and the hot air outside, and promotes heat exchange, so that the hot air is emitted through the heat dissipation holes 31, and the cold air enters the engine room inner cylinder through the heat dissipation holes 31.
  • the rapid heat dissipation of the heat dissipation device is realized.
  • the heat dissipation hole 31 includes a first through hole 311 near the middle of the bottom plate 30 and The second through hole 312 at the edge of the bottom plate 30.
  • the diameter of the top end of the first through hole 311 is larger than the diameter of the bottom end of the first through hole 311.
  • the diameter of the top end of the second through hole 312 is smaller than the diameter of the bottom end of the second through hole 312.
  • the outside cold air easily enters the interior of the nacelle inner tube 20 through the second through hole 312, while the hot air in the nacelle inner tube 20 is difficult to pass through the second through hole 312.
  • the two through holes 312 are discharged.
  • cold air enters the nacelle inner tube 20 from the second through hole 312 near the side, and the hot air in the nacelle inner tube 20 is discharged from the first through hole 311 near the middle, thereby forming a stable air circulation loop and improving the cabin.
  • the convection of the air inside and outside the cylinder 20 improves the heat dissipation effect of the heat dissipation device.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Microelectronics & Electronic Packaging (AREA)
  • Remote Sensing (AREA)
  • Cooling Or The Like Of Electrical Apparatus (AREA)

Abstract

L'invention concerne un dispositif de dissipation de chaleur pour la cabine d'un véhicule aérien sans pilote, le dispositif comprenant : un cylindre interne de cabine (20), un cylindre externe de cabine (10), une première feuille de dissipation de chaleur (13), une première feuille de conservation de chaleur (14), une seconde feuille de dissipation de chaleur (22) et une seconde feuille de conservation de chaleur (23). À la suite de la rotation relative du cylindre interne de cabine et du cylindre externe de cabine, lorsque la première feuille de dissipation de chaleur et la seconde feuille de dissipation de chaleur se chevauchent, la chaleur dans le cylindre interne de cabine est rapidement conduite et dissipée au moyen de la première feuille de dissipation de chaleur et de la seconde feuille de dissipation de chaleur, ce qui favorise la dissipation de chaleur. Lorsque la première feuille de dissipation de chaleur et la seconde feuille de dissipation de chaleur sont distribuées en quinconce, la première feuille de conservation de chaleur et la seconde feuille de conservation de chaleur réalisent une conservation de chaleur à l'intérieur du cylindre interne de cabine, réduisant ainsi la vitesse à laquelle la chaleur est dissipée. Le dispositif de dissipation de chaleur décrit pour la cabine d'un véhicule aérien sans pilote peut augmenter la vitesse à laquelle la chaleur est dissipée à l'intérieur de la cabine de moteur, tout en ayant également une fonction de conservation de la chaleur, ce qui permet au véhicule aérien sans pilote de s'adapter aux exigences de vol dans différents environnements.
PCT/CN2020/083043 2020-03-31 2020-04-02 Dispositif de dissipation de chaleur pour cabine de véhicule aérien sans pilote WO2021196138A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CN202020446462.7U CN211969749U (zh) 2020-03-31 2020-03-31 一种无人机机舱散热装置
CN202020446462.7 2020-03-31

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WO2021196138A1 true WO2021196138A1 (fr) 2021-10-07

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114265331A (zh) * 2021-12-21 2022-04-01 重庆交通大学 一种无人机发动机舱热仿真方法

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20130112805A1 (en) * 2011-07-06 2013-05-09 Borealis Technical Limited Method for reducing requirements for aircraft brake size, complexity, and heat dissipation
CN104670499A (zh) * 2015-02-28 2015-06-03 广州快飞计算机科技有限公司 一种植保无人机
US20150159968A1 (en) * 2011-09-14 2015-06-11 Borealis Technical Limited Heat dissipation system for aircraft drive wheel drive assembly
CN105836116A (zh) * 2016-04-07 2016-08-10 湖北易瓦特科技股份有限公司 冷却型无人机
CN106628151A (zh) * 2016-12-30 2017-05-10 易瓦特科技股份公司 机壳快拆式无人机
CN108216652A (zh) * 2018-01-17 2018-06-29 安徽中骄智能科技有限公司 一种用于无人机电机散热机架
CN209661174U (zh) * 2019-03-15 2019-11-22 南京机电职业技术学院 一种保温杯

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20130112805A1 (en) * 2011-07-06 2013-05-09 Borealis Technical Limited Method for reducing requirements for aircraft brake size, complexity, and heat dissipation
US20150159968A1 (en) * 2011-09-14 2015-06-11 Borealis Technical Limited Heat dissipation system for aircraft drive wheel drive assembly
CN104670499A (zh) * 2015-02-28 2015-06-03 广州快飞计算机科技有限公司 一种植保无人机
CN105836116A (zh) * 2016-04-07 2016-08-10 湖北易瓦特科技股份有限公司 冷却型无人机
CN106628151A (zh) * 2016-12-30 2017-05-10 易瓦特科技股份公司 机壳快拆式无人机
CN108216652A (zh) * 2018-01-17 2018-06-29 安徽中骄智能科技有限公司 一种用于无人机电机散热机架
CN209661174U (zh) * 2019-03-15 2019-11-22 南京机电职业技术学院 一种保温杯

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114265331A (zh) * 2021-12-21 2022-04-01 重庆交通大学 一种无人机发动机舱热仿真方法

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