CN106058283A - Heat radiation structure and method for fuel cell of unmanned aerial vehicle - Google Patents

Heat radiation structure and method for fuel cell of unmanned aerial vehicle Download PDF

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Publication number
CN106058283A
CN106058283A CN201610664458.6A CN201610664458A CN106058283A CN 106058283 A CN106058283 A CN 106058283A CN 201610664458 A CN201610664458 A CN 201610664458A CN 106058283 A CN106058283 A CN 106058283A
Authority
CN
China
Prior art keywords
motor
fuel cell
unmanned plane
management module
speed
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.)
Pending
Application number
CN201610664458.6A
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Chinese (zh)
Inventor
卢致辉
陈金颖
马廉攀
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.)
Shenzhen Micromulticopter Aero Technology Co Ltd
Original Assignee
Shenzhen Micromulticopter Aero Technology 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 Shenzhen Micromulticopter Aero Technology Co Ltd filed Critical Shenzhen Micromulticopter Aero Technology Co Ltd
Priority to CN201610664458.6A priority Critical patent/CN106058283A/en
Publication of CN106058283A publication Critical patent/CN106058283A/en
Pending legal-status Critical Current

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Classifications

    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
    • H01M8/00—Fuel cells; Manufacture thereof
    • H01M8/04—Auxiliary arrangements, e.g. for control of pressure or for circulation of fluids
    • H01M8/04007—Auxiliary arrangements, e.g. for control of pressure or for circulation of fluids related to heat exchange
    • 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
    • B64D37/00—Arrangements in connection with fuel supply for power plant
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
    • H01M8/00—Fuel cells; Manufacture thereof
    • H01M8/04—Auxiliary arrangements, e.g. for control of pressure or for circulation of fluids
    • H01M8/04007—Auxiliary arrangements, e.g. for control of pressure or for circulation of fluids related to heat exchange
    • H01M8/04014—Heat exchange using gaseous fluids; Heat exchange by combustion of reactants
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
    • H01M8/00—Fuel cells; Manufacture thereof
    • H01M8/04—Auxiliary arrangements, e.g. for control of pressure or for circulation of fluids
    • H01M8/04298—Processes for controlling fuel cells or fuel cell systems
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
    • H01M8/00—Fuel cells; Manufacture thereof
    • H01M8/04—Auxiliary arrangements, e.g. for control of pressure or for circulation of fluids
    • H01M8/04298—Processes for controlling fuel cells or fuel cell systems
    • H01M8/04313—Processes for controlling fuel cells or fuel cell systems characterised by the detection or assessment of variables; characterised by the detection or assessment of failure or abnormal function
    • H01M8/0432—Temperature; Ambient temperature
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
    • Y02E60/00—Enabling technologies; Technologies with a potential or indirect contribution to GHG emissions mitigation
    • Y02E60/30—Hydrogen technology
    • Y02E60/50—Fuel cells
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
    • Y02T90/40—Application of hydrogen technology to transportation, e.g. using fuel cells

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Manufacturing & Machinery (AREA)
  • Sustainable Development (AREA)
  • Sustainable Energy (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Electrochemistry (AREA)
  • General Chemical & Material Sciences (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Combustion & Propulsion (AREA)
  • Fuel Cell (AREA)

Abstract

The invention discloses a heat radiation structure and method for a fuel cell of an unmanned aerial vehicle, belonging to the field of unmanned aerial vehicles. The heat radiation structure comprises a control system arranged in the unmanned aerial vehicle, a fuel cell stack installed at the bottom of the unmanned aerial vehicle, a motor and blades. The heat radiation structure is characterized in that the motor is mounted below the fuel cell; air flow generated by the motor dissipates heat for the fuel cell and provides flying power; the lower end of the fuel cell stack is provided with a porous housing; the motor is arranged at the lower end of the porous housing; and the blades are mounted on the motor shaft of the motor. According to the invention, power consumption of a fan is transferred to the motor; the motor realizes heat radiation of the fuel cell stack and provides power for flying of the unmanned aerial vehicle; so effective utilization of energy is realized.

Description

A kind of radiator structure for unmanned plane fuel cell and method
Technical field
The invention belongs to the fuel cell application in unmanned plane field, be specifically related to a kind of for unmanned plane fuel cell Radiator structure and method.
Background technology
Existing fuel cell pile uses fan to dispel the heat, and fan work needs to consume substantial amounts of energy, and in nothing Man-machine field, fan, in addition to consumed energy, also increases complete machine weight and volume, thus shortens unmanned plane cruising time.
Therefore, the unmanned technical approach using fan cooling of the prior art, the burden of unmanned plane can be increased undoubtedly.
Summary of the invention
The present invention overcomes unmanned plane in prior art to need to use fan to carry out dispelling the heat and increasing complete machine weight and volume, from And shorten unmanned plane cruising time, it is provided that a kind of motor is arranged on below fuel cell pile, cancels the use of fan, not only Heat sinking function can be provided for pile, simultaneously for can be that the flight of unmanned plane provides power, thus reach effectively utilizing of the energy Radiator structure and method for unmanned plane fuel cell.
The present invention is achieved through the following technical solutions: a kind of radiator structure for unmanned plane fuel cell, bag Include be arranged in unmanned plane control system, be installed on the fuel cell pack bottom unmanned plane, motor and blade, its feature exists In: described motor is installed on the lower section of fuel cell, and the air-flow that motor produces is for fuel cell pack heat radiation and provides flight dynamic Power, the lower end of described fuel cell pack is provided with a porous outer housing, and motor is installed on the lower end of porous outer housing, and blade is installed on On the motor shaft of motor.
As preferred technical scheme, described fuel cell pack is bolt-connected to bottom unmanned plane and stays gap.
As preferred technical scheme, the sidewall of described porous outer housing is close to fuel cell pack and seals, and lower section is passed through Screw connects motor.
As preferred technical scheme, described porous outer housing is provided with more than one air-flow through hole.
As preferred technical scheme, described control system include manage module, fuel cell pack, unmanned plane motor and Motor a, management module forms two-way and controls, and controls 1 connection motor a, is used for controlling to manage motor a, controls the 2 unmanned electricity of control Machine, fuel cell pack is unmanned plane motor, motor a and management module provide electric energy.
As preferred technical scheme, described management module detection fuel cell stack temperature, detector unit uses temperature Degree sensor, temperature sensor is installed on fuel cell pack.
Unmanned plane driving method:
(1) management module detects fuel cell pile temperature, and fuel cell pile in real time by temperature sensor Temperature is by controlling 1 signal management motor a rotating speed, to guarantee that fuel cell pile is operated in safety range；
(2) management module monitors and in real time by controlling 2 signal management unmanned plane motor speeds, unmanned plane motor speed Determined by unmanned plane during flying state；
(3) when unmanned plane will be when riseing, management module first passes through control 1 signal makes motor a accelerate to shape at full speed State, whether the management module monitors unmanned plane speed that rises reaches requirement: if reached, then management module keeps motor a and unmanned The rotating speed of dynamo-electric machine is constant；
If not up to, then management module makes unmanned plane motor progressively accelerate by controlling 2 signals, until it meets soaring Rate request；If it does, then management module makes unmanned plane motor progressively slow down by controlling 2 signals, until it meets soaring Rate request；
(4) when unmanned plane will be when declining, management module is by controlling 1 rotating speed current for signal maintenance motor a not Becoming, management module gradually reduces unmanned plane motor speed until meeting decrease speed by controlling 2 signals simultaneously；
If unmanned plane to land, then management module is progressively dropped by decrease speed set in advance control 2 signals Low unmanned plane motor speed is until rotating speed is 0, and after UAV Landing, management module is by real-time temperature sensor detection fuel Battery stack temperature, after fuel cell pile temperature drops to safe temperature, management module is by controlling 1 signal at stop motor a.
Motor is arranged on below fuel cell pile, uses management module to control it and manage.For fuel Battery pile, management module monitors its temperature in real time, controls the rotating speed of motor according to temperature, thus by the temperature of fuel cell pile Degree controls in claimed range；For UAS, management module receives external command, thus controls fuel cell pile Motor and unmanned plane other motor co-ordination during unmanned plane during flying.
The invention has the beneficial effects as follows: fan power consumption is transferred on motor by the present invention, and motor can not only carry for pile For heat sinking function, simultaneously for can be that the flight of unmanned plane provides power, thus reach effective utilization of the energy.
Accompanying drawing explanation
In order to be illustrated more clearly that the embodiment of the present invention or technical scheme of the prior art, below will be to embodiment or existing In having technology to describe, the required accompanying drawing used is briefly described, it should be apparent that, the accompanying drawing in describing below is only this Some embodiments of invention, for those of ordinary skill in the art, on the premise of not paying creative work, it is also possible to Other accompanying drawing is obtained according to these accompanying drawings.
Fig. 1 is the system block diagram of the present invention；
Fig. 2 is the structural representation of the present invention.
Detailed description of the invention
All features disclosed in this specification, or disclosed all methods or during step, except mutually exclusive Feature and/or step beyond, all can combine by any way.
Any feature disclosed in this specification (including any accessory claim, summary and accompanying drawing), unless chatted especially State, all can be by other equivalences or there is the alternative features of similar purpose replaced.I.e., unless specifically stated otherwise, each feature is only It it is an example in a series of equivalence or similar characteristics.
Fig. 1 is the system block diagram of the present invention, in Fig. 1, eliminates the use of fan, and motor is directly installed on fuel electricity The bottom of Chi Dui, the air-flow that motor work produces can dispel the heat for pile, also can provide power for the flight of unmanned plane.
Driving method is as follows:
Firstly the need of starting fluid battery pile, it is management module for power supply by fuel cell pile, and fuel cell Pile provides power for motor a and unmanned plane motor；
Management module detects fuel cell pile temperature, and fuel cell stack temperature in real time by temperature sensor By controlling 1 signal management motor a rotating speed, to guarantee that fuel cell pile is operated in safety range；
Management module monitors in real time and by controlling 2 signal management unmanned plane motor speeds, unmanned plane motor speed is by nothing Man-machine state of flight determines；
Unmanned plane manages during soaring: when unmanned plane will be when riseing, and management module first passes through control 1 signal Motor a is made to accelerate to full-speed state.Whether the management module monitors unmanned plane speed that rises reaches requirement: if reached, then manage The rotating speed of module holding motor a and unmanned plane motor is constant；If not up to, then management module makes unmanned by controlling 2 signals Dynamo-electric machine progressively accelerates, until it meets soaring rate request；If it does, then management module makes unmanned by controlling 2 signals Dynamo-electric machine progressively slows down, until it meets soaring rate request
Unmanned plane manages during declining: when unmanned plane will be when declining, and management module maintains by controlling 1 signal Rotating speed current for motor a is constant, simultaneously management module by control 2 signals gradually reduce unmanned plane motor speed until meet under Reduction of speed degree；If unmanned plane to land, then management module is gradually reduced by decrease speed set in advance control 2 signals Unmanned plane motor speed is until rotating speed is 0, and after UAV Landing, management module is by real-time temperature sensor detection fuel electricity Pond stack temperature, after fuel cell pile temperature drops to safe temperature, management module is by controlling 1 signal at stop motor a.
Fig. 2 is the radiator structure scheme of installation of the unmanned plane of the present invention, and in Fig. 2, fuel cell pile is by bolt even Receiving bottom unmanned plane and keep certain distance, this distance can be installed according to cooling requirements, leaves space, the purpose of distance is not Allow fuel cell pack directly contact with the bottom surface of unmanned plane, thus avoid the heat of fuel cell pack that unmanned plane body is caused Impact.
Erection sequence is the most successively: porous outer housing 2, motor, blade.
The sidewall of porous outer housing is close to fuel cell pile 1 and seals, and lower section screw connects motor 3.On electric machine main shaft Fixing a blade 4, blade uses for unmanned plane lifting so that it is obtain enough ascending airs.
It is unmanned plane when powering when fuel cell stack operation, needs air around to form air-flow, pass through internal porosity The pore of porous outer housing flows out from below, realizes the heat radiation bottom fuel cell with this, and the rotation of blade drives air to be formed Such type of flow, is therefore installed on the lower end of fuel cell pack by motor, is rotated the formation realizing air-flow by blade, this Therefore a little air-flows can eliminate radiator fan use in unmanned plane just for the heat radiation of fuel cell pack.
The invention has the beneficial effects as follows: fan power consumption is transferred on motor by the present invention, and motor can not only carry for pile For heat sinking function, simultaneously for can be that the flight of unmanned plane provides power, thus reach effective utilization of the energy.
The above, the only detailed description of the invention of the present invention, but protection scope of the present invention is not limited thereto, and any The change expected without creative work or replacement, all should contain within protection scope of the present invention.Therefore, the present invention Protection domain should be as the criterion with the protection domain that claims are limited.

Claims (7)

1., for a radiator structure for unmanned plane fuel cell, including the control system being arranged in unmanned plane, it is installed on nothing The fuel cell pack of man-machine bottom, motor and blade, it is characterised in that: described motor is installed on the lower section of fuel cell, electricity The air-flow that machine produces is for fuel cell pack heat radiation and provides flying power, and the lower end of described fuel cell pack is provided with more than one Hole outer housing, motor is installed on the lower end of porous outer housing, and blade is installed on the motor shaft of motor.
2. the radiator structure for unmanned plane fuel cell as claimed in claim 1, it is characterised in that: described fuel cell pack It is bolt-connected to bottom unmanned plane and stays gap.
3. the radiator structure for unmanned plane fuel cell as claimed in claim 1, it is characterised in that: described porous outer housing Sidewall is close to fuel cell pack and seals, and lower section is connected by screw motor.
Porous outer housing the most according to claim 1, it is characterised in that: it is provided with more than one gas on described porous outer housing Opening.
Radiator structure for unmanned plane fuel cell the most according to claim 2, it is characterised in that: described control system Including management module, fuel cell pack, unmanned plane motor and motor a, management module forms two-way and controls, and controls 1 connection electricity Machine a, is used for controlling to manage motor a, controls the 2 unmanned motors of control, and fuel cell pack is unmanned plane motor, motor a and management Module provides electric energy.
Radiator structure for unmanned plane fuel cell the most according to claim 5, it is characterised in that: described management module Detection fuel cell stack temperature, detector unit uses temperature sensor, and temperature sensor is installed on fuel cell pack.
7. a unmanned plane driving method, concrete grammar is as follows:
(1) management module detects fuel cell pile temperature, and fuel cell stack temperature in real time by temperature sensor By controlling 1 signal management motor a rotating speed, to guarantee that fuel cell pile is operated in safety range；
(2) management module monitors in real time and by controlling 2 signal management unmanned plane motor speeds, unmanned plane motor speed is by nothing Man-machine state of flight determines；
(3) when unmanned plane will be when riseing, management module first passes through control 1 signal makes motor a accelerate to full-speed state, Whether the management module monitors unmanned plane speed that rises reaches requirement: if reached, then management module keeps motor a and unmanned dynamo-electric The rotating speed of machine is constant；
If not up to, then management module makes unmanned plane motor progressively accelerate by controlling 2 signals, until it meets soaring speed Requirement；If it does, then management module makes unmanned plane motor progressively slow down by controlling 2 signals, until it meets soaring speed Requirement；
(4) when unmanned plane will be when declining, management module maintains the current rotating speed of motor a constant by controlling 1 signal, with Shi Guanli module gradually reduces unmanned plane motor speed until meeting decrease speed by controlling 2 signals；
If unmanned plane to land, then management module gradually reduces nothing by decrease speed set in advance control 2 signals Man-machine motor speed is until rotating speed is 0, and after UAV Landing, management module is by real-time temperature sensor detection fuel cell Stack temperature, after fuel cell pile temperature drops to safe temperature, management module is by controlling 1 signal at stop motor a.
CN201610664458.6A 2016-08-11 2016-08-11 Heat radiation structure and method for fuel cell of unmanned aerial vehicle Pending CN106058283A (en)

Priority Applications (1)

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Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN111372854A (en) * 2017-11-24 2020-07-03 斗山摩拜创新株式会社 Fuel cell power pack for unmanned aerial vehicle and state information monitoring method thereof
CN112038665A (en) * 2020-09-17 2020-12-04 广州鼎奥科技有限公司 Fuel cell group for unmanned aerial vehicle of steerable voltage
CN113193208A (en) * 2021-04-25 2021-07-30 电子科技大学 Air cooling type fuel cell power system of fixed wing unmanned aerial vehicle

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105000183A (en) * 2015-06-29 2015-10-28 中国气象局气象探测中心 Self-propelled dropsonde system
CN105015756A (en) * 2015-07-23 2015-11-04 北京天航华创科技股份有限公司 Wind power generation and heat dissipation and cooling-integrated structure for stratospheric airship
WO2016116902A1 (en) * 2015-01-22 2016-07-28 Zodiac Aerotechnics Aircraft fuel cell heat usages
CN205900703U (en) * 2016-08-11 2017-01-18 深圳市科比特航空科技有限公司 A heat radiation structure for unmanned aerial vehicle fuel cell

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2016116902A1 (en) * 2015-01-22 2016-07-28 Zodiac Aerotechnics Aircraft fuel cell heat usages
CN105000183A (en) * 2015-06-29 2015-10-28 中国气象局气象探测中心 Self-propelled dropsonde system
CN105015756A (en) * 2015-07-23 2015-11-04 北京天航华创科技股份有限公司 Wind power generation and heat dissipation and cooling-integrated structure for stratospheric airship
CN205900703U (en) * 2016-08-11 2017-01-18 深圳市科比特航空科技有限公司 A heat radiation structure for unmanned aerial vehicle fuel cell

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN111372854A (en) * 2017-11-24 2020-07-03 斗山摩拜创新株式会社 Fuel cell power pack for unmanned aerial vehicle and state information monitoring method thereof
US11952141B2 (en) 2017-11-24 2024-04-09 Doosan Mobility Innovation Inc. Fuel cell power pack for drone and state information monitoring method thereof
CN112038665A (en) * 2020-09-17 2020-12-04 广州鼎奥科技有限公司 Fuel cell group for unmanned aerial vehicle of steerable voltage
CN113193208A (en) * 2021-04-25 2021-07-30 电子科技大学 Air cooling type fuel cell power system of fixed wing unmanned aerial vehicle
CN113193208B (en) * 2021-04-25 2022-10-14 电子科技大学 Air cooling type fuel cell power system of fixed wing unmanned aerial vehicle

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