WO2021064819A1 - Appareil de démarrage de moteur - Google Patents

Appareil de démarrage de moteur Download PDF

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Publication number
WO2021064819A1
WO2021064819A1 PCT/JP2019/038609 JP2019038609W WO2021064819A1 WO 2021064819 A1 WO2021064819 A1 WO 2021064819A1 JP 2019038609 W JP2019038609 W JP 2019038609W WO 2021064819 A1 WO2021064819 A1 WO 2021064819A1
Authority
WO
WIPO (PCT)
Prior art keywords
engine
generator
power supply
supply switch
engine start
Prior art date
Application number
PCT/JP2019/038609
Other languages
English (en)
Japanese (ja)
Inventor
賢治郎 橋爪
Original Assignee
株式会社テクノスヤシマ
八洲電業株式会社
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 株式会社テクノスヤシマ, 八洲電業株式会社 filed Critical 株式会社テクノスヤシマ
Priority to PCT/JP2019/038609 priority Critical patent/WO2021064819A1/fr
Priority to CN201980052375.3A priority patent/CN112601700A/zh
Priority to JP2020566856A priority patent/JP6969716B2/ja
Publication of WO2021064819A1 publication Critical patent/WO2021064819A1/fr

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Classifications

    • 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
    • B64D31/00—Power plant control systems; Arrangement of power plant control systems in aircraft
    • B64D31/02—Initiating means
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/04—Helicopters
    • B64C27/06—Helicopters with single rotor
    • 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
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/02—Aircraft characterised by the type or position of power plants
    • B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00—Type of UAV
    • B64U10/10—Rotorcrafts
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U50/00—Propulsion; Power supply
    • B64U50/10—Propulsion
    • B64U50/11—Propulsion using internal combustion piston engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02N—STARTING OF COMBUSTION ENGINES; STARTING AIDS FOR SUCH ENGINES, NOT OTHERWISE PROVIDED FOR
    • F02N11/00—Starting of engines by means of electric motors
    • F02N11/04—Starting of engines by means of electric motors the motors being associated with current generators
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02N—STARTING OF COMBUSTION ENGINES; STARTING AIDS FOR SUCH ENGINES, NOT OTHERWISE PROVIDED FOR
    • F02N11/00—Starting of engines by means of electric motors
    • F02N11/12—Starting of engines by means of mobile, e.g. portable, starting sets
    • 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

Definitions

  • the present invention relates to an engine starting device for starting an engine used by a generator for an aircraft such as a multi-rotor helicopter.
  • UAVs Unmanned Aerial Vehicles
  • unmanned exploration helicopters have been studied for military use in the United States and other countries.
  • an air vehicle such as a multi-rotor helicopter, which is also called a drone, is used for long-distance product delivery work, for example.
  • the hybrid system for UAVs where the generator is combined with the battery, is suitable for long-distance product delivery work, etc., but has a built-in starter motor to start the engine used by the generator. Often requires an engine shaft mounted portable engine starter.
  • the present inventor has noticed that in such an engine shaft-mounted portable engine starter, the weight of the device tends to be large, and some skill for safe use is required.
  • the present invention provides an engine starting device capable of eliminating the need for an engine shaft-mounted portable engine starter incorporating a starter motor for starting an engine used by a generator.
  • the purpose is to provide.
  • the first invention is an engine starting device for an air vehicle including a generator that uses an engine to generate electricity.
  • a generator that uses an engine to generate electricity.
  • an engine start power supply switch for turning on / off the power supply to the generator is provided.
  • the power supply is turned on by the engine start power supply switch, the power generation rotor of the generator rotates with respect to the power generation stator of the generator, so that the engine crankshaft of the engine is rotated. It is an engine starter.
  • the second invention is the first engine starting device of the present invention, characterized in that the battery for supplying power to the generator is built-in or mounted on the flying object.
  • a third aspect of the present invention is provided with a flight motor electric circuit for electrically connecting the flight motor of the flying object to the generator.
  • the first engine starting device of the present invention is characterized in that an engine starting power supply connector capable of electrically connecting the engine starting power supply switch to the generator is provided in the flight motor electric circuit.
  • the engine start power supply switch when the engine start power supply switch is electrically connected to the generator by the engine start power supply connector, the engine start power supply switch is electrically connected to the generator. , The flight motor is electrically disconnected from the generator, When the engine start power supply switch is not electrically connected to the generator by the engine start power supply connector, the engine start power supply switch is electrically disconnected from the generator and the flight motor is the generator.
  • the third engine starting device of the present invention which is electrically connected to the engine.
  • the engine starting power supply connector is a third engine starting device of the present invention, characterized in that it is provided at an end of the drawn flight motor electric circuit.
  • an engine starting device capable of eliminating the need for an engine shaft-mounted portable engine starter having a built-in starter motor for starting an engine used by a generator.
  • the multi-rotor helicopter 200 is an example of an air vehicle in the present invention.
  • the generator 210 is an example of the generator in the present invention.
  • the power generation rotor 211 is an example of a power generation rotor in the present invention.
  • the power generation stator 212 is an example of the power generation stator in the present invention.
  • the engine 213 is an example of an engine in the present invention, and the engine crankshaft 213s is an example of an engine crankshaft in the present invention.
  • the flight motor electric circuit 250 is an example of the flight motor electric circuit in the present invention.
  • the engine start power supply connector 260 is an example of the engine start power supply connector in the present invention.
  • the engine starting device 300 is an example of the engine starting device in the present invention.
  • Battery 310 is an example of a battery in the present invention.
  • the engine start power supply switch 320 is an example of the engine start power supply switch in the present invention.
  • FIG. 1 is a schematic perspective view of the multi-rotor helicopter system 100 of the embodiment of the present invention
  • FIG. 2 is a portion of the multi-rotor helicopter system 100 of the embodiment of the present invention in the vicinity of the engine starting device 300. It is a block diagram.
  • the maximum non-landing flight time of a multi-rotor UAV for pesticide application is approximately 2 hours with a 3 kg payload such as a camera unit and approximately 20 minutes with a 10 kg payload.
  • Battery technology is expected to achieve a maximum non-landing flight time of 10 hours with a payload of 10 kilograms, but due to restrictions on weight volume energy density, a maximum non-landing flight time exceeding 2 hours can be achieved by a battery-powered UAV system. It is difficult to achieve.
  • the present inventor believes that it is desirable to put an ultra-compact and lightweight hybrid system for UAV into practical use.
  • the helicopter battery 220 is charged using the generator 210 and supplies electric power to the flight motor 240 that drives the propeller 241.
  • the number of propellers 241 is 4, but it may be 1 or 5 or more in consideration of safety.
  • the helicopter battery controller 230 is a controller that controls the operation of the helicopter battery 220.
  • the engine cylinder 213c As a component of an engine 213 such as a gasoline engine having two engine cylinders 213c, the engine cylinder 213c is driven by the engine power taken out via a spark plug, an air cleaner, and a power transmission belt mechanism, and is driven by cooling air W.
  • Two engine air-cooled fan devices 213f and the like for cooling are efficiently arranged, and ultra-compactness and weight reduction are realized.
  • the belt tension of such a power transmission belt mechanism can be adjusted in consideration of the load balance during power generation, and the load on the engine air-cooled fan device 213f side is balanced with the load on the power generation rotor 211 side, and the load on the engine 213 is balanced. A small load equilibrium state is achieved.
  • the engine starting device 300 is a device for a multi-rotor helicopter 200 having a generator 210 that generates electricity using the engine 213.
  • the engine shaft-mounted portable engine starter having a built-in starter motor which tends to increase the weight of the device and requires some skill for safe use, is a portable engine starter. Not needed.
  • the engine start power supply switch 320 is a switch that turns on / off the power supply to the generator 210 when the engine 213 is started.
  • the power generation rotor 211 of the generator 210 rotates with respect to the power generation stator 212 of the generator 210, so that the engine crankshaft 213s of the engine 213 is rotated.
  • the battery 310 supplies power to the power generation rotor 211 when the engine 213 is started, but may supply power to the power generation stator 212.
  • the electronic speed controller 330 uses a battery to change the motor rotation speed of the power generation rotor 211, which is used not as an original generator component but as a starter motor component, by turning the battery voltage on and off by PWM (Pulse Width Modulation) control. It is a controller that controls the operation of 310.
  • PWM Pulse Width Modulation
  • the dedicated starter motor is used. It is completely unnecessary, and the device weight of the engine starting device 300 does not increase. Needless to say, a helicopter-mounted engine starter such as a recoil starter for starting the engine 213, which tends to hinder weight reduction, is also unnecessary.
  • the engine start power supply switch 320 is a button-type push-on switch that uses a return spring member or the like, in which power supply is turned on only in a relatively short period of time when the button is pressed down by the user. After the engine 213 is started, the power supply is quickly turned off by the engine start power supply switch 320, so that the normal power generation operation by the engine 213 is smoothly started.
  • the battery 310 that supplies power to the generator 210 is built-in.
  • the battery 310 that supplies power to the generator 210 may be mounted on the multi-rotor helicopter 200.
  • the portable main body housing 340 of the engine starting device 300 stores not only the engine starting power supply switch 320 and the electronic speed controller 330 but also the battery 310, but the battery 310 does not have to be stored.
  • the engine starting device 300 itself may be mounted on the multi-rotor helicopter 200.
  • helicopter battery 220 may supply power to the generator 210 instead of the battery 310.
  • a flight motor electric circuit 250 that electrically connects the flight motor 240 of the multi-rotor helicopter 200 to the generator 210 is provided.
  • the flight motor electric circuit 250 is provided with an engine start power supply connector 260 capable of electrically connecting the engine start power supply switch 320 to the generator 210.
  • the engine starting power supply connector 260 be mounted on the multi-rotor helicopter 200 in advance before using the engine starting device 300.
  • the engine start power supply switch 320 When the engine start power supply switch 320 is electrically connected to the generator 210 by the engine start power supply connector 260, the engine start power supply switch 320 is electrically connected to the generator 210 and the flight motor 240 is a generator. It is electrically disconnected from 210. When the engine start power supply switch 320 is not electrically connected to the generator 210 by the engine start power supply connector 260, the engine start power supply switch 320 is electrically disconnected from the generator 210, and the flight motor 240 is the generator 210. Is electrically connected to.
  • connection switch 252 that switches the electrical connection state S between the flight motor 240 and the generator 210 is mechanically turned off by pushing the connection switch contact stick member 253 as shown in FIG. As shown in 4, it is mechanically turned on by returning the connection switch return spring member (not shown).
  • FIGS. 3 and 4 are explanatory views (No. 1 and 2) of turning on / off the electrical connection between the flight motor 240 and the generator 210 of the multi-rotor helicopter system 100 according to the embodiment of the present invention.
  • the helicopter battery controller 230 When the engine 213 is started and power is turned on by the engine start power switch 320, the helicopter battery controller 230 performs automatic control to disconnect the electrical connection between the helicopter battery 220 and the generator 210. May be good. This is because the operation of the engine 213, which is different from the normal power generation operation in which the helicopter battery 220 is charged, may cause an electrically undesired phenomenon for the helicopter battery 220. It goes without saying that the electrical connection between such a helicopter battery 220 and the generator 210 may be turned off semi-automatically or manually.
  • the helicopter battery controller 230 may perform automatic control to turn on the electrical connection between the helicopter battery 220 and the generator 210. This is because the normal power generation operation by the engine 213, which charges the helicopter battery 220, is not wasted. It goes without saying that the electrical connection between such a helicopter battery 220 and the generator 210 may be turned on semi-automatically or manually.
  • a part of the flight motor electric circuit 250 is pulled out to the outside of the multi-rotor helicopter 200.
  • the engine start power supply connector 260 is provided at the end of the drawn flight motor electric circuit 250.
  • the engine start power supply connector 260 is attached to the tip of the cable 251 of the flight motor electric circuit 250, which can be easily attached to and detached from the insertion port provided on the outer surface of the engine start device 300.
  • the cable 251 is lightweight, so that the engine starting device 300 does not bear the weight burden of the flight motor 240.
  • the engine start power supply connector 260 but also the cable 251 of the flight motor electric circuit 250 and the like may be sold as an accessory component of the engine start device 300, or may be sold separately.
  • the root portion of the cable 251 of the flight motor electric circuit 250 may be easily detachable from an outlet provided on the outer surface of the multi-rotor helicopter 200, such an outlet to the outside of the multi-rotor helicopter 200. It may be attached to an exposed area, it may be attached to a place covered by a removable helicopter body bonnet, or it may be covered with an openable / closable waterproof cover or a removable waterproof cap. May be good.
  • the engine starting power supply connector 260 is provided on the outer surface of the multi-rotor helicopter 200 so that the tip of the cable of the engine starting device 300 can be easily attached and detached. It may be attached to the provided outlet.
  • FIG. 5 is a schematic perspective view of the multi-rotor helicopter system 100 of the modified example of the embodiment of the present invention
  • FIG. 6 is an engine of the multi-rotor helicopter system 100 of the modified example of the embodiment of the present invention. It is a partial block diagram in the vicinity of the starting device 300.
  • the program of the invention related to the present invention executes the operation of all or a part of the multi-rotor helicopter engine starting method of the invention related to the present invention described above (or process, operation, action, etc.) on the computer. It is a program that works in cooperation with a computer.
  • the recording medium of the invention related to the present invention is all or part of all or part of the steps (or process, operation, action, etc.) of the multi-rotor helicopter engine starting method of the invention related to the present invention described above. It is a recording medium on which a program for causing a computer to execute the above-mentioned operation is recorded, and is a computer-readable recording medium in which the read program is used in cooperation with a computer.
  • operation of a step means an operation of all or a part of the above-mentioned steps.
  • one usage form of the program of the invention related to the present invention is a form in which the program is transmitted in a transmission medium such as the Internet, light, radio waves, or sound waves, read by a computer, and operates in cooperation with the computer. It may be.
  • the recording medium includes a ROM (Read Only Memory) and the like.
  • the computer is not limited to pure hardware such as a CPU (Central Processing Unit), but may include a firmware, an OS (Operating System), and further peripheral devices.
  • a CPU Central Processing Unit
  • OS Operating System
  • the configuration of the present invention may be realized by software or hardware.
  • the engine starter in the present invention can eliminate the need for an engine shaft mounted portable engine starter with a built-in starter motor to start the engine used by the generator, and can be used for aircraft such as multi-rotor helicopters. It is useful for the purpose of using it as an engine starting device for starting an engine used by a generator.
  • Multi-rotor helicopter system 200 Multi-rotor helicopter 210 Generator 211 Power generation rotor 212 Power generation stator 213 Engine 213s Engine crank shaft 213c Engine cylinder 213f Engine air-cooled fan device 220 Helicopter battery 230 Helicopter battery controller 240 Flight motor 241 Propeller 250 Flight motor Electric circuit 251 Cable 252 Connection switch 253 Connection switch Contact stick member 260 Engine start power supply connector 300 Engine starter 310 Battery 320 Engine start power supply switch 330 Electronic speed controller 340 Portable body chassis W Cooling air S Connection status

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Remote Sensing (AREA)
  • Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)

Abstract

Un système hybride destiné à un aéronef sans pilote ayant un générateur combiné à une batterie est approprié pour des tâches de livraison de marchandises de longue distance, mais nécessite souvent un démarreur de moteur portable de type monté sur un arbre de moteur qui comprend un moteur de démarreur pour démarrer un moteur utilisé par le générateur.　L'invention concerne un appareil de démarrage de moteur (300) destiné à un hélicoptère multirotor (200) pourvu d'un générateur (210) qui génère de l'énergie à l'aide d'un moteur (213), l'appareil de démarrage de moteur (300) étant pourvu d'un commutateur d'alimentation électrique de démarrage de moteur (320) qui allume/éteint l'alimentation électrique du générateur (210) lorsque le moteur (213) est démarré. Lorsque l'alimentation électrique est activée par le commutateur d'alimentation électrique de démarrage de moteur (320), un rotor de production d'énergie (211) du générateur (210) tourne par rapport à un stator de génération d'énergie (212) du générateur (210), et ainsi un vilebrequin de moteur (213s) du moteur (213) est mis en rotation.
PCT/JP2019/038609 2019-09-30 2019-09-30 Appareil de démarrage de moteur WO2021064819A1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
PCT/JP2019/038609 WO2021064819A1 (fr) 2019-09-30 2019-09-30 Appareil de démarrage de moteur
CN201980052375.3A CN112601700A (zh) 2019-09-30 2019-09-30 发动机起动装置
JP2020566856A JP6969716B2 (ja) 2019-09-30 2019-09-30 エンジン始動装置

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/JP2019/038609 WO2021064819A1 (fr) 2019-09-30 2019-09-30 Appareil de démarrage de moteur

Publications (1)

Publication Number Publication Date
WO2021064819A1 true WO2021064819A1 (fr) 2021-04-08

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PCT/JP2019/038609 WO2021064819A1 (fr) 2019-09-30 2019-09-30 Appareil de démarrage de moteur

Country Status (3)

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JP (1) JP6969716B2 (fr)
CN (1) CN112601700A (fr)
WO (1) WO2021064819A1 (fr)

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2011047338A (ja) * 2009-08-27 2011-03-10 Nisshinbo Holdings Inc 可搬型エンジン始動装置
JP2014148967A (ja) * 2013-02-04 2014-08-21 Hitachi Koki Co Ltd エンジン作業機
WO2017030034A1 (fr) * 2015-08-14 2017-02-23 株式会社プロドローン Dispositif de production d'énergie et véhicule aérien sans pilote pourvu de celui-ci
JP2018168750A (ja) * 2017-03-30 2018-11-01 本田技研工業株式会社 エンジン発電機
JP2019519414A (ja) * 2017-01-23 2019-07-11 北京瑞深航空科技有限公司Ｂｅｉｊｉｎｇ Ｒｉｃｈｅｎｐｏｗｅｒ Ｔｅｃｈｎｏｌｏｇｙ Ｃｏ．， Ｌｔｄ． ハイブリッド動力源無人機

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5125597A (en) * 1990-06-01 1992-06-30 General Electric Company Gas turbine engine powered aircraft environmental control system and boundary layer bleed with energy recovery system
JP2001016900A (ja) * 1999-06-28 2001-01-19 Mitsuba Corp 始動発電機
CN1140040C (zh) * 2001-05-21 2004-02-25 笪桂生 车辆用综合电机系统
US20040155527A1 (en) * 2003-02-10 2004-08-12 Bryde Jan Henrik Distributed power generation, conversion, and storage system
DE102007033356A1 (de) * 2007-07-16 2009-01-22 Compact Dynamics Gmbh Wasserflugzeug oder Bodeneffektfahrzeug
FR2954283B1 (fr) * 2009-12-23 2012-03-02 Hispano Suiza Sa Aeronef comportant un demarreur-generateur electrique pour le ou chaque turboreacteur et un train d'aterrissage equipe d'un moteur electrique de manoeuvre au sol
CN203331861U (zh) * 2013-07-04 2013-12-11 中国汽车技术研究中心 一种应急车载充电装置
FR3027286B1 (fr) * 2014-10-20 2018-01-05 Safran Helicopter Engines Systeme propulsif hybride d'un aeronef multi-moteur
CN107117320A (zh) * 2017-04-06 2017-09-01 徐成 一种多旋翼油电混合动力飞行器

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2011047338A (ja) * 2009-08-27 2011-03-10 Nisshinbo Holdings Inc 可搬型エンジン始動装置
JP2014148967A (ja) * 2013-02-04 2014-08-21 Hitachi Koki Co Ltd エンジン作業機
WO2017030034A1 (fr) * 2015-08-14 2017-02-23 株式会社プロドローン Dispositif de production d'énergie et véhicule aérien sans pilote pourvu de celui-ci
JP2019519414A (ja) * 2017-01-23 2019-07-11 北京瑞深航空科技有限公司Ｂｅｉｊｉｎｇ Ｒｉｃｈｅｎｐｏｗｅｒ Ｔｅｃｈｎｏｌｏｇｙ Ｃｏ．， Ｌｔｄ． ハイブリッド動力源無人機
JP2018168750A (ja) * 2017-03-30 2018-11-01 本田技研工業株式会社 エンジン発電機

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CN112601700A (zh) 2021-04-02
JPWO2021064819A1 (ja) 2021-10-28
JP6969716B2 (ja) 2021-11-24

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