WO2021064819A1 - Engine-starting apparatus - Google Patents

Engine-starting apparatus 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
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WO
WIPO (PCT)
Prior art keywords
engine
generator
power supply
supply switch
engine start
Prior art date
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PCT/JP2019/038609
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French (fr)
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.)
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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/en
Priority to CN201980052375.3A priority patent/CN112601700B/en
Priority to JP2020566856A priority patent/JP6969716B2/en
Publication of WO2021064819A1 publication Critical patent/WO2021064819A1/en

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    • 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)
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  • Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)

Abstract

A hybrid system for a UAV having a generator combined with a battery is suited for long-distance commodity delivery work, but often needs an engine shaft-mounted type portable engine starter which includes a starter motor for starting an engine used by the generator.　An engine-starting apparatus (300) is for a multirotor helicopter (200) provided with a generator (210) which generates power by using an engine (213), the engine-starting apparatus (300) being provided with an engine start power supply switch (320) that turns on/off power supply to the generator (210) when the engine (213) is started, wherein, when the power supply is turned on by the engine start power supply switch (320), a power generation rotor (211) of the generator (210) rotates with respect to a power generation stator (212) of the generator (210), and thus an engine crankshaft (213s) of the engine (213) is rotated.

Description

エンジン始動装置Engine starter
　本発明は、マルチローターヘリコプターのような飛行体のための、発電機が利用するエンジンを始動させるエンジン始動装置に関する。 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.
　無人探査ヘリコプターなどのＵＡＶ（Ｕｎｍａｎｎｅｄ　Ａｅｒｉａｌ　Ｖｅｈｉｃｌｅ）は、米国などで軍事利用を目的として研究されてきた。 UAVs (Unmanned Aerial Vehicles) such as unmanned exploration helicopters have been studied for military use in the United States and other countries.
　近年では、リチウムイオンバッテリー技術が急速に発展してきており、ＬｉＰｏ（Ｌｉｔｈｉｕｍ　Ｐｏｌｙｍｅｒ）バッテリーなどのバッテリーを搭載するＵＡＶが農薬散布作業などの農業利用を目的として実用化されている（たとえば、特許文献１参照）。 In recent years, lithium-ion battery technology has been rapidly developed, and UAVs equipped with batteries such as LiPo (Lithium Polymer) batteries have been put into practical use for agricultural use such as pesticide spraying work (for example, Patent Document 1). reference).
特開２０１４－７６６７６号公報Japanese Unexamined Patent Publication No. 2014-76676
　ところで、本発明者は、ＵＡＶのような飛行体がさまざまな利用を目的としてより広く実用化されることが望ましいと考えている。 By the way, the present inventor believes that it is desirable that an air vehicle such as a UAV be put into practical use more widely for various purposes.
　より具体的には、本発明者は、ドローンとも呼ばれる、マルチローターヘリコプターのような飛行体が、たとえば、長距離商品配送作業などに利用されることが望ましいと考えている。 More specifically, the present inventor considers that it is desirable that 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.
　しかしながら、発電機がバッテリーと組合わせられているＵＡＶのためのハイブリッドシステムは、長距離商品配送作業などに適しているが、発電機が利用するエンジンを始動させるためのスターターモーターを内蔵しているエンジンシャフト装着式ポータブルエンジンスターターをしばしば必要とする。 However, 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.
　本発明者は、このようなエンジンシャフト装着式ポータブルエンジンスターターにおいては、装置重量が大きくなりやすく、安全な使用のための技量がある程度は要求されることに気付いた。 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.
　本発明は、上述された従来の課題を考慮し、発電機が利用するエンジンを始動させるためのスターターモーターを内蔵しているエンジンシャフト装着式ポータブルエンジンスターターを不要とすることができるエンジン始動装置を提供することを目的とする。 In consideration of the above-mentioned conventional problems, 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.
　第１の本発明は、エンジンを利用して発電を行う発電機を備えた飛行体のためのエンジン始動装置であって、
　前記エンジンを始動させるとき、前記発電機への給電をオンオフするエンジン始動給電スイッチを備え、
　前記給電が前記エンジン始動給電スイッチによりオンされると、前記発電機の発電ローターが前記発電機の発電ステーターに対して回転することにより、前記エンジンのエンジンクランクシャフトが回転させられることを特徴とするエンジン始動装置である。 The first invention is an engine starting device for an air vehicle including a generator that uses an engine to generate electricity.
When the engine is started, an engine start power supply switch for turning on / off the power supply to the generator is provided.
When 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.
　第２の本発明は、前記発電機への前記給電を行うバッテリーは、内蔵されている、または前記飛行体へ搭載されていることを特徴とする第１の本発明のエンジン始動装置である。 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.
　第３の本発明は、前記飛行体の飛行モーターを前記発電機と電気的に接続する飛行モーター電気回路が、設けられており、
　前記エンジン始動給電スイッチを前記発電機と電気的に接続可能であるエンジン始動給電コネクターが、前記飛行モーター電気回路に設けられていることを特徴とする第１の本発明のエンジン始動装置である。 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.
　第４の本発明は、前記エンジン始動給電スイッチが前記エンジン始動給電コネクターにより前記発電機と電気的に接続される場合には、前記エンジン始動給電スイッチが前記発電機と電気的に接続されるとともに、前記飛行モーターは前記発電機と電気的に切断され、
　前記エンジン始動給電スイッチが前記エンジン始動給電コネクターにより前記発電機と電気的に接続されない場合には、前記エンジン始動給電スイッチが前記発電機と電気的に切断されるとともに、前記飛行モーターは前記発電機と電気的に接続されることを特徴とする第３の本発明のエンジン始動装置である。 In the fourth aspect of the present invention, 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.
　第５の本発明は、前記飛行モーター電気回路の一部は、前記飛行体の機体外部へ引出されており、
　前記エンジン始動給電コネクターは、前記引出された飛行モーター電気回路の端部に設けられていることを特徴とする第３の本発明のエンジン始動装置である。 In the fifth aspect of the present invention, a part of the flight motor electric circuit is pulled out to the outside of the airframe of the flight body.
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.
　本発明により、発電機が利用するエンジンを始動させるためのスターターモーターを内蔵しているエンジンシャフト装着式ポータブルエンジンスターターを不要とすることが可能なエンジン始動装置を提供することができる。 INDUSTRIAL APPLICABILITY According to the present invention, it is possible to provide 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.
本発明における実施の形態のマルチローターヘリコプターシステムの模式的な斜視図Schematic perspective view of the multi-rotor helicopter system of the embodiment of the present invention. 本発明における実施の形態のマルチローターヘリコプターシステムのエンジン始動装置近傍の部分ブロック図Partial block diagram near the engine starter of the multi-rotor helicopter system of the embodiment of the present invention. 本発明における実施の形態のマルチローターヘリコプターシステムの飛行モーターと発電機との間の電気的接続のオンオフの説明図（その一）Explanatory drawing for turning on / off the electrical connection between the flight motor and the generator of the multi-rotor helicopter system according to the embodiment of the present invention (No. 1). 本発明における実施の形態のマルチローターヘリコプターシステムの飛行モーターと発電機との間の電気的接続のオンオフの説明図（その二）Explanatory drawing for turning on / off the electrical connection between the flight motor and the generator of the multi-rotor helicopter system according to the embodiment of the present invention (No. 2). 本発明における実施の形態の変形例のマルチローターヘリコプターシステムの模式的な斜視図Schematic perspective view of a modified multi-rotor helicopter system according to an embodiment of the present invention. 本発明における実施の形態の変形例のマルチローターヘリコプターシステムのエンジン始動装置近傍の部分ブロック図Partial block diagram of the vicinity of the engine starting device of the multi-rotor helicopter system of the modified example of the embodiment in the present invention.
　以下、図面を参照しながら、本発明における実施の形態について詳細に説明する。 Hereinafter, embodiments of the present invention will be described in detail with reference to the drawings.
　マルチローターヘリコプター２００は、本発明における飛行体の例である。 The multi-rotor helicopter 200 is an example of an air vehicle in the present invention.
　発電機２１０は、本発明における発電機の例である。発電ローター２１１は、本発明における発電ローターの例である。発電ステーター２１２は、本発明における発電ステーターの例である。エンジン２１３は本発明におけるエンジンの例であり、エンジンクランクシャフト２１３ｓは本発明におけるエンジンクランクシャフトの例である。飛行モーター電気回路２５０は、本発明における飛行モーター電気回路の例である。エンジン始動給電コネクター２６０は、本発明におけるエンジン始動給電コネクターの例である。 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.
　エンジン始動装置３００は、本発明におけるエンジン始動装置の例である。 The engine starting device 300 is an example of the engine starting device in the present invention.
　バッテリー３１０は、本発明におけるバッテリーの例である。エンジン始動給電スイッチ３２０は、本発明におけるエンジン始動給電スイッチの例である。 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.
　はじめに、図１および２を参照しながら、本実施の形態のマルチローターヘリコプターシステム１００の構成および動作について具体的に説明する。 First, the configuration and operation of the multi-rotor helicopter system 100 of the present embodiment will be specifically described with reference to FIGS. 1 and 2.
　ここに、図１は本発明における実施の形態のマルチローターヘリコプターシステム１００の模式的な斜視図であり、図２は本発明における実施の形態のマルチローターヘリコプターシステム１００のエンジン始動装置３００近傍の部分ブロック図である。 Here, FIG. 1 is a schematic perspective view of the multi-rotor helicopter system 100 of the embodiment of the present invention, and 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.
　本実施の形態のマルチローターヘリコプターシステム１００の動作について説明しながら、本発明に関連した発明のマルチローターヘリコプターエンジン始動方法についても説明する。 While explaining the operation of the multi-rotor helicopter system 100 of the present embodiment, the method of starting the multi-rotor helicopter engine of the invention related to the present invention will also be described.
　多くの産業用ＵＡＶにおいては、リチウムイオンバッテリーを利用するバッテリー駆動型ＵＡＶシステムが採用されている。農薬散布用マルチローター型ＵＡＶの最大無着陸飛行時間は、カメラユニットのような３キログラムのペイロードでおよそ２時間であり、１０キログラムのペイロードでおよそ２０分である。１０キログラムのペイロードで１０時間の最大無着陸飛行時間を実現するバッテリー技術が期待されるが、重量体積エネルギー密度の制約があるので、２時間を超える最大無着陸飛行時間をバッテリー駆動型ＵＡＶシステムにより実現することは困難である。 Many industrial UAVs use battery-powered UAV systems that use lithium-ion batteries. 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.
　一方、ガソリンのオクタン価は高いので、ガソリンエンジンにより代表される内燃機関の駆動装置を利用して大きなエネルギーを取出すことができる可能性はあるが、装置重量が大きくなりやすい。 On the other hand, since the octane number of gasoline is high, there is a possibility that a large amount of energy can be extracted by using the drive device of an internal combustion engine represented by a gasoline engine, but the device weight tends to be large.
　本発明者は、ＵＡＶのための超小型軽量ハイブリッドシステムの実用化が望ましいと考えている。 The present inventor believes that it is desirable to put an ultra-compact and lightweight hybrid system for UAV into practical use.
　ヘリコプターバッテリー２２０は、発電機２１０を利用して充電され、プロペラー２４１を駆動する飛行モーター２４０へ電力を供給する。プロペラー２４１の数は、４であるが、１であってもよいし、安全性を考慮して５以上であってもよい。 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.
　ヘリコプターバッテリーコントローラー２３０は、ヘリコプターバッテリー２２０の動作制御を行うコントローラーである。 The helicopter battery controller 230 is a controller that controls the operation of the helicopter battery 220.
　２つのエンジン気筒２１３ｃを有するガソリンエンジンのようなエンジン２１３の部品として、点火プラグ、エアクリーナー、および、動力伝達ベルト機構を介して取出されたエンジン動力で駆動されて冷却風Ｗでエンジン気筒２１３ｃを冷却する２つのエンジン空冷ファン装置２１３ｆなどが効率的に配置されており、超小型化および軽量化が実現される。このような動力伝達ベルト機構のベルトテンションは発電時の負荷バランスを考慮して調節可能であり、エンジン空冷ファン装置２１３ｆの側の負荷が発電ローター２１１の側の負荷と釣合ってエンジン２１３の負担が小さい負荷平衡状態が達成される。 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.
　エンジン始動装置３００は、エンジン２１３を利用して発電を行う発電機２１０を有するマルチローターヘリコプター２００のための装置である。 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.
　本実施の形態においては、後述されるように、装置重量が大きくなりやすく、安全な使用のための技量がある程度は要求される、スターターモーターを内蔵しているエンジンシャフト装着式ポータブルエンジンスターターは、不要である。 In the present embodiment, as will be described later, 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.
　つぎに、図２を主として参照しながら、本実施の形態のマルチローターヘリコプターシステム１００の構成および動作についてより具体的に説明する。 Next, the configuration and operation of the multi-rotor helicopter system 100 of the present embodiment will be described more specifically with reference to FIG. 2.
　エンジン始動給電スイッチ３２０は、エンジン２１３を始動させるとき、発電機２１０への給電をオンオフするスイッチである。 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.
　給電がエンジン始動給電スイッチ３２０によりオンされると、発電機２１０の発電ローター２１１が発電機２１０の発電ステーター２１２に対して回転することにより、エンジン２１３のエンジンクランクシャフト２１３ｓが回転させられる。 When the power supply is turned on by the engine start power supply switch 320, 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.
　バッテリー３１０は、エンジン２１３を始動させるとき、発電ローター２１１への給電を行うが、発電ステーター２１２への給電を行ってもよい。 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.
　電子スピードコントローラー３３０は、本来の発電機構成部材としてではなく、スターターモーター構成部材として利用される発電ローター２１１のモーター回転速度をＰＷＭ（Ｐｕｌｓｅ　Ｗｉｄｔｈ　Ｍｏｄｕｌａｔｉｏｎ）制御によるバッテリー電圧オンオフで変化させるために、バッテリー３１０の動作制御を行うコントローラーである。 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.
　発電ローター２１１および発電ステーター２１２は、本来の発電機構成部材としてではなく、エンジン２１３を始動させるとき、エンジンクランクシャフト２１３ｓを回転させるためのスターターモーター構成部材として利用されるので、専用のスターターモーターは全く不要であり、エンジン始動装置３００の装置重量は大きくならない。そして、軽量化を阻害しやすい、エンジン２１３を始動させるためのリコイルスターターのようなヘリコプター搭載型エンジンスターターも不要であることは、言うまでもない。 Since the power generation rotor 211 and the power generation stator 212 are used not as the original generator components but as the starter motor components for rotating the engine crankshaft 213s when the engine 213 is started, 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.
　エンジン始動給電スイッチ３２０は、ユーザーによるボタン押下げが行われている比較的に短い期間においてのみ給電がオンされる、復帰スプリング部材などを利用するボタン型プッシュオンスイッチである。エンジン２１３が始動された後、給電はエンジン始動給電スイッチ３２０により速やかにオフされるので、エンジン２１３による通常の発電動作はスムーズに開始される。 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.
　エンジン始動給電スイッチ３２０のユーザー操作は機械操作に不慣れな初心者などにとっても極めて容易であるので、エンジンシャフト装着式ポータブルエンジンスターターが内蔵しているスターターモーターへの巻込みのような事故はほぼ全く発生し得ないのみならず、安全な使用のための技量も要求されない。 Since the user operation of the engine start power supply switch 320 is extremely easy even for beginners who are unfamiliar with machine operation, accidents such as getting caught in the starter motor built in the portable engine starter mounted on the engine shaft occur almost completely. Not only is it impossible, but no skill is required for safe use.
　本実施の形態においては、発電機２１０への給電を行うバッテリー３１０は、内蔵されている。 In the present embodiment, the battery 310 that supplies power to the generator 210 is built-in.
　なお、変形例の形態においては、発電機２１０への給電を行うバッテリー３１０は、マルチローターヘリコプター２００へ搭載されていてもよい。 In the modified example, the battery 310 that supplies power to the generator 210 may be mounted on the multi-rotor helicopter 200.
　より具体的に述べると、つぎの通りである。 More specifically, it is as follows.
　エンジン始動装置３００のポータブル本体筐体３４０は、エンジン始動給電スイッチ３２０および電子スピードコントローラー３３０のみならずバッテリー３１０も収納するが、バッテリー３１０を収納しなくてもよい。エンジン始動装置３００そのものが、マルチローターヘリコプター２００へ搭載されていてもよい。 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.
　もちろん、ヘリコプターバッテリー２２０が、バッテリー３１０の代わりに発電機２１０への給電を行ってもよい。 Of course, the helicopter battery 220 may supply power to the generator 210 instead of the battery 310.
　マルチローターヘリコプター２００の飛行モーター２４０を発電機２１０と電気的に接続する飛行モーター電気回路２５０が、設けられている。エンジン始動給電スイッチ３２０を発電機２１０と電気的に接続可能であるエンジン始動給電コネクター２６０が、飛行モーター電気回路２５０に設けられている。 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.
　エンジン始動給電コネクター２６０は、工具などが取付けに必要とされることもあるので、エンジン始動装置３００の使用の前にあらかじめマルチローターヘリコプター２００へ取付けられていることが望ましい。 Since tools and the like may be required for mounting the engine starting power supply connector 260, it is desirable that the engine starting power supply connector 260 be mounted on the multi-rotor helicopter 200 in advance before using the engine starting device 300.
　エンジン始動給電スイッチ３２０がエンジン始動給電コネクター２６０により発電機２１０と電気的に接続される場合には、エンジン始動給電スイッチ３２０が発電機２１０と電気的に接続されるとともに、飛行モーター２４０は発電機２１０と電気的に切断される。エンジン始動給電スイッチ３２０がエンジン始動給電コネクター２６０により発電機２１０と電気的に接続されない場合には、エンジン始動給電スイッチ３２０が発電機２１０と電気的に切断されるとともに、飛行モーター２４０は発電機２１０と電気的に接続される。 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.
　より具体的に述べると、つぎの通りである。 More specifically, it is as follows.
　飛行モーター２４０と発電機２１０との間の電気的な接続状態Ｓを切替える接続スイッチ２５２は、図３に示されているように接続スイッチ当接スティック部材２５３の押しにより機械的にオフされ、図４に示されているように接続スイッチ復帰スプリング部材（図示せず）の戻しにより機械的にオンされる。 The 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).
　ここに、図３および４は、本発明における実施の形態のマルチローターヘリコプターシステム１００の飛行モーター２４０と発電機２１０との間の電気的接続のオンオフの説明図（その一および二）である。 Here, 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.
　ユーザーがマルチローターヘリコプター２００の機体へ近づいているとき、飛行モーター２４０の意図しない危険な回転開始を抑制する、このような電気的接続のオンオフが自動制御、半自動制御または手動制御で行われてもよいことは、言うまでもない。 When the user is approaching the fuselage of the multi-rotor helicopter 200, such electrical connections can be turned on and off automatically, semi-automatically or manually to prevent unintended and dangerous start of rotation of the flight motor 240. Needless to say, the good thing is.
　エンジン２１３が始動されるとき、給電がエンジン始動給電スイッチ３２０によりオンされると、ヘリコプターバッテリーコントローラー２３０はヘリコプターバッテリー２２０と発電機２１０との間の電気的接続をオフするための自動制御を行ってもよい。これは、ヘリコプターバッテリー２２０が充電される、通常の発電動作とは異なるエンジン２１３の動作により、ヘリコプターバッテリー２２０にとって電気的に望ましくない現象が発生し得るからである。このようなヘリコプターバッテリー２２０と発電機２１０との間の電気的接続が半自動制御または手動制御でオフされてもよいことは、言うまでもない。 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.
　エンジン２１３が始動された後、ヘリコプターバッテリーコントローラー２３０はヘリコプターバッテリー２２０と発電機２１０との間の電気的接続をオンするための自動制御を行ってもよい。これは、ヘリコプターバッテリー２２０が充電される、エンジン２１３による通常の発電動作が無駄にならないからである。このようなヘリコプターバッテリー２２０と発電機２１０との間の電気的接続が半自動制御または手動制御でオンされてもよいことは、言うまでもない。 After the engine 213 is started, 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.
　飛行モーター電気回路２５０の一部は、マルチローターヘリコプター２００の機体外部へ引出されている。エンジン始動給電コネクター２６０は、引出された飛行モーター電気回路２５０の端部に設けられている。 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.
　より具体的に述べると、つぎの通りである。 More specifically, it is as follows.
　エンジン始動給電コネクター２６０は、エンジン始動装置３００の外表面に設けられた差込み口と容易に脱着可能である、飛行モーター電気回路２５０のケーブル２５１の先端部分へ取付けられている。 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.
　ポータブル本体筐体３４０が飛行開始までにケーブル２５１から取外されれば、ケーブル２５１は軽量であるので、エンジン始動装置３００は飛行モーター２４０の重量負担にならない。 If the portable main body housing 340 is removed from the cable 251 by the start of flight, the cable 251 is lightweight, so that the engine starting device 300 does not bear the weight burden of the flight motor 240.
　そして、ケーブル２５１は長尺部材であるので、ユーザーはポータブル本体筐体３４０の取外しのためにマルチローターヘリコプター２００の機体へ近づく必要がなく、飛行モーター２４０の意図しない回転開始にともなう危険はほとんど全くない。 And since the cable 251 is a long member, the user does not have to approach the body of the multi-rotor helicopter 200 to remove the portable main body housing 340, and there is almost no danger associated with the unintended rotation start of the flight motor 240. Absent.
　エンジン始動給電コネクター２６０のみならず、飛行モーター電気回路２５０のケーブル２５１などは、エンジン始動装置３００の付属コンポーネントとして販売されてもよいし、別売りされてもよい。 Not only 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.
　飛行モーター電気回路２５０のケーブル２５１の根本部分はマルチローターヘリコプター２００の外表面に設けられた差込み口と容易に脱着可能であってもよく、そのような差込み口は、マルチローターヘリコプター２００の外部へ露出する箇所へ取付けられていてもよいし、取外し可能なヘリコプター本体ボンネットで覆われている箇所へ取付けられていてもよいし、開閉可能な防水カバーまたは脱着可能な防水キャップなどで覆われていてもよい。 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.
　もちろん、図５および６に示されているように、エンジン始動給電コネクター２６０は、エンジン始動装置３００のケーブルの先端部分などが容易に脱着可能であるように、マルチローターヘリコプター２００の外表面に設けられた差込み口へ取付けられていてもよい。 Of course, as shown in FIGS. 5 and 6, 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.
　ここに、図５は本発明における実施の形態の変形例のマルチローターヘリコプターシステム１００の模式的な斜視図であり、図６は本発明における実施の形態の変形例のマルチローターヘリコプターシステム１００のエンジン始動装置３００近傍の部分ブロック図である。 Here, 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, and 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.
　なお、本発明に関連した発明のプログラムは、上述された本発明に関連した発明のマルチローターヘリコプターエンジン始動方法の全部または一部のステップ（または工程、動作および作用など）の動作をコンピューターに実行させるためのプログラムであって、コンピューターと協働して動作するプログラムである。 In addition, 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.
　また、本発明に関連した発明の記録媒体は、上述された本発明に関連した発明のマルチローターヘリコプターエンジン始動方法の全部または一部のステップ（または工程、動作および作用など）の全部または一部の動作をコンピューターに実行させるためのプログラムを記録した記録媒体であり、読取られたプログラムがコンピューターと協働して利用されるコンピューター読取り可能な記録媒体である。 In addition, 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.
　なお、上述された「一部のステップ（または工程、動作および作用など）」は、それらの複数のステップの内の一つまたはいくつかのステップを意味する。 Note that the above-mentioned "partial step (or process, operation, action, etc.)" means one or several steps among the plurality of steps.
　また、上述された「ステップ（または工程、動作および作用など）の動作」は、上述されたステップの全部または一部の動作を意味する。 Further, the above-mentioned "operation of a step (or process, operation, action, etc.)" means an operation of all or a part of the above-mentioned steps.
　また、本発明に関連した発明のプログラムの一利用形態は、インターネット、光、電波または音波などのような伝送媒体の中を伝送され、コンピューターにより読取られ、コンピューターと協働して動作するという形態であってもよい。 Further, 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.
　また、記録媒体としては、ＲＯＭ（Ｒｅａｄ　Ｏｎｌｙ　Ｍｅｍｏｒｙ）などが含まれる。 Further, the recording medium includes a ROM (Read Only Memory) and the like.
　また、コンピューターは、ＣＰＵ（Ｃｅｎｔｒａｌ　Ｐｒｏｃｅｓｓｉｎｇ　Ｕｎｉｔ）などのような純然たるハードウェアに限らず、ファームウェア、ＯＳ（Ｏｐｅｒａｔｉｎｇ　Ｓｙｓｔｅｍ）、そしてさらに周辺機器を含んでもよい。 Further, 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.
　なお、上述されたように、本発明の構成は、ソフトウェア的に実現されてもよいし、ハードウェア的に実現されてもよい。 As described above, the configuration of the present invention may be realized by software or hardware.
　本発明におけるエンジン始動装置は、発電機が利用するエンジンを始動させるためのスターターモーターを内蔵しているエンジンシャフト装着式ポータブルエンジンスターターを不要とすることができ、マルチローターヘリコプターのような飛行体のための、発電機が利用するエンジンを始動させるエンジン始動装置に利用する目的に有用である。 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.
　１００　マルチローターヘリコプターシステム
　２００　マルチローターヘリコプター
　２１０　発電機
　２１１　発電ローター
　２１２　発電ステーター
　２１３　エンジン
　２１３ｓ　エンジンクランクシャフト
　２１３ｃ　エンジン気筒
　２１３ｆ　エンジン空冷ファン装置
　２２０　ヘリコプターバッテリー
　２３０　ヘリコプターバッテリーコントローラー
　２４０　飛行モーター
　２４１　プロペラー
　２５０　飛行モーター電気回路
　２５１　ケーブル
　２５２　接続スイッチ
　２５３　接続スイッチ当接スティック部材
　２６０　エンジン始動給電コネクター
　３００　エンジン始動装置
　３１０　バッテリー
　３２０　エンジン始動給電スイッチ
　３３０　電子スピードコントローラー
　３４０　ポータブル本体筐体
　Ｗ　冷却風
　Ｓ　接続状態 100 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

Claims (5)

  1. 　エンジンを利用して発電を行う発電機を備えた飛行体のためのエンジン始動装置であって、
    　前記エンジンを始動させるとき、前記発電機への給電をオンオフするエンジン始動給電スイッチを備え、
    　前記給電が前記エンジン始動給電スイッチによりオンされると、前記発電機の発電ローターが前記発電機の発電ステーターに対して回転することにより、前記エンジンのエンジンクランクシャフトが回転させられることを特徴とするエンジン始動装置。     An engine starter for an aircraft equipped with a generator that uses an engine to generate electricity.
    When the engine is started, an engine start power supply switch for turning on / off the power supply to the generator is provided.
    When 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. Engine starter.
  2. 　前記発電機への前記給電を行うバッテリーは、内蔵されている、または前記飛行体へ搭載されていることを特徴とする請求項１に記載のエンジン始動装置。 The engine starting device according to claim 1, wherein the battery that supplies power to the generator is built-in or mounted on the flying object.
  3. 　前記飛行体の飛行モーターを前記発電機と電気的に接続する飛行モーター電気回路が、設けられており、
    　前記エンジン始動給電スイッチを前記発電機と電気的に接続可能であるエンジン始動給電コネクターが、前記飛行モーター電気回路に設けられていることを特徴とする請求項１に記載のエンジン始動装置。     A flight motor electric circuit for electrically connecting the flight motor of the flying object to the generator is provided.
    The engine starting device according to claim 1, wherein 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.
  4. 　前記エンジン始動給電スイッチが前記エンジン始動給電コネクターにより前記発電機と電気的に接続される場合には、前記エンジン始動給電スイッチが前記発電機と電気的に接続されるとともに、前記飛行モーターは前記発電機と電気的に切断され、
    　前記エンジン始動給電スイッチが前記エンジン始動給電コネクターにより前記発電機と電気的に接続されない場合には、前記エンジン始動給電スイッチが前記発電機と電気的に切断されるとともに、前記飛行モーターは前記発電機と電気的に接続されることを特徴とする請求項３に記載のエンジン始動装置。     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 and the flight motor generates the power generation. Electrically disconnected from the machine
    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 engine starting device according to claim 3, wherein the engine starting device is electrically connected to the engine.
  5. 　前記飛行モーター電気回路の一部は、前記飛行体の機体外部へ引出されており、
    　前記エンジン始動給電コネクターは、前記引出された飛行モーター電気回路の端部に設けられていることを特徴とする請求項３に記載のエンジン始動装置。     A part of the flight motor electric circuit is pulled out to the outside of the airframe of the flight body.
    The engine starting device according to claim 3, wherein the engine starting power supply connector is provided at an end of the drawn flight motor electric circuit.
PCT/JP2019/038609 2019-09-30 2019-09-30 Engine-starting apparatus WO2021064819A1 (en)

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