CN106741977A - 一种涵道式无人飞行器顶置发动机直驱双冷装置 - Google Patents

一种涵道式无人飞行器顶置发动机直驱双冷装置 Download PDF

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Publication number
CN106741977A
CN106741977A CN201710071770.9A CN201710071770A CN106741977A CN 106741977 A CN106741977 A CN 106741977A CN 201710071770 A CN201710071770 A CN 201710071770A CN 106741977 A CN106741977 A CN 106741977A
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China
Prior art keywords
unmanned vehicle
engine
cooling
culvert type
type unmanned
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CN201710071770.9A
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景朝锋
张学军
潘志刚
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Shenzhen City Hangyu Aviation Technology Co Ltd
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Shenzhen City Hangyu Aviation Technology Co Ltd
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Priority to CN201710071770.9A priority Critical patent/CN106741977A/zh
Publication of CN106741977A publication Critical patent/CN106741977A/zh
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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
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/08—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00—Type of UAV
    • B64U10/10—Rotorcrafts
    • B64U10/13—Flying platforms
    • 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U50/00—Propulsion; Power supply
    • B64U50/10—Propulsion
    • B64U50/13—Propulsion using external fans or propellers
    • B64U50/14—Propulsion using external fans or propellers ducted or shrouded

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Remote Sensing (AREA)
  • Cooling, Air Intake And Gas Exhaust, And Fuel Tank Arrangements In Propulsion Units (AREA)

Abstract

本发明提供了一种无人飞行器直驱双冷装置，通过采用发动机的直驱方式进行冷却提高了对涵道式无人飞行器的发动机冷却效率，减小了发动机的燃油消耗。

Description

一种涵道式无人飞行器顶置发动机直驱双冷装置
技术领域
本申请涉及一种涵道式无人飞行器，具体涉及一种涵道式无人飞行器的冷却装置。
背景技术
近年来，无人飞行器的生产和研发逐步兴起，无人飞行器由于其自身具备的鲜明技术特点，在军事和民用领域得到了广泛的应用和飞速的发展，尤其在农业保护、通信中继、防灾减灾、气象监测、电力传输、测绘、航拍、娱乐等领域具有着广泛的应用。无人机包括多种类型，而涵道式无人机具有垂直起降和悬停的飞行特点，在体积、隐蔽性和飞行性能上都具有鲜明的特点，已成为微小型无人机领域中生产和应用较多的机型。
目前，涵道式无人飞行器的生产公司陆续推出了多种型号的涵道式无人飞行器。例如，Sikorsky公司推出的Cypher无人机飞行器采用共轴双桨涵道式布局的涵道式飞行器；美国著名的霍尼韦尔公司推出了kestrel无人飞行器；新加坡也推出了自己的涵道式风扇无人机fantail。涵道式无人飞行器通常主要包括载荷舱、涵道风扇系统、着陆架和动力系统所组成。涵道式无人飞行器根据具体的需要通常采用电动机和油机两种类型，对于载荷在5kg以下的涵道式无人飞行器采用的通常为电动机，而载荷量较大的涵道式无人飞行器通常采用的是燃油发动机。随着涵道式无人飞行器的优点的发掘，许多领域，例如通信中继、防灾巡逻等领域通常需安装大型的载荷设备用于开展相关的应用，因而，燃油发动机是目前主要的大载荷无人飞行器的主要动力系统。然而对于燃油发动机作为动力系统的无人飞行器，由于发动机在工作时的热量主要依靠外部的空气进行冷却，这一冷却方式往往受到机体结构和流场影响散热效率差，这就导致在实际的飞行过程中无人机的发动机常处于过热的状态，而发动机的散热对其工作效率产生重大影响，材料的过热会影响动力输出、油耗高、缸体易损坏甚至出现飞行故障导致的飞行事故。并且，涵道式无人飞行器在执行任务时，散热还会造成续航能力不足，维修保养频繁的缺点。
发明内容
为了解决无人飞行器发动机的散热问题，本发明主要采用由发动机直接驱动两个冷却风扇给发动机的两个气缸进行主动散热的无人飞行器顶置发动机直驱双冷装置对无人飞行器的发动机进行散热。本发明提供了一种无人飞行器顶置发动机直驱双冷装置，由主动轮、被动轮、皮带、传动轴、散热风扇、轴承和安装底座组成，所述散热风扇安装在发动机缸头上方通过修改加长发动机曲轴使背部输出动力带动主动轮，主动轮通过皮带传递到被动轮，被动轮由传动轴链接风扇使之旋转产生气流，给发动机缸体散热。
有益效果：发明的涵道式无人飞行器顶置发动机直驱双冷装置，由发动机直接驱动两个冷却风扇给发动机的两个气缸进行主动散热。这种直驱式双冷方式，不需要额外电源和动力，根据发动机工作状态自动调节冷却风力，彻底解决了涵道式无人飞行器顶置发动机因不易散热温度高而导致的功率下降、高油耗、磨损大、寿命低、易发生事故等诸多问题。涵道式无人飞行器顶置发动机直驱双冷装置，能简单可靠高效地保障无人飞行器的飞行安全，而且比传统的自然风冷方式，降低百分之三十的油耗。
附图说明
图1为涵道式无人飞行器发动机直驱双冷装置的剖面图；图2为涵道式无人飞行器发动机直驱双冷装置的俯视图；图3为涵道式无人飞行器的整体结构图。

Claims (1)

1.一种涵道式无人飞行器顶置发动机直驱双冷装置，由主动轮、被动轮、皮带、传动轴、散热风扇、安装底座组成，所述散热风扇安装在发动机缸头上方通过修改加长发动机曲轴使背部输出动力带动主动轮，主动轮通过皮带传递到被动轮，被动轮由传动轴链接风扇使之旋转产生气流，给发动机缸体散热；所述发动机直驱双冷装置安装在顶置发动机的顶部，所述顶置发动机位于涵道式无人飞行器的机体上部。
CN201710071770.9A 2017-02-09 2017-02-09 一种涵道式无人飞行器顶置发动机直驱双冷装置 Pending CN106741977A (zh)

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Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN107489513A (zh) * 2017-09-22 2017-12-19 湖南省库塔科技有限公司 一种用于直升机的风冷系统
US11148820B1 (en) * 2018-02-19 2021-10-19 Parallel Flight Technologies, Inc. System defining a hybrid power unit for thrust generation in an aerial vehicle and method for controlling the same
US20230182916A1 (en) * 2020-12-28 2023-06-15 Parallel Flight Technologies, Inc. System defining a hybrid power unit for thrust generation in an aerial vehicle and method for controlling the same
US11993375B2 (en) 2018-02-19 2024-05-28 Parallel Flight Technologies, Inc. Method and apparatus for lifting a payload

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CN204264452U (zh) * 2014-11-27 2015-04-15 哈尔滨盛世特种飞行器有限公司 电动单旋翼涵道式无人飞行器
CN205022897U (zh) * 2015-09-28 2016-02-10 湖北易瓦特科技股份有限公司 具有冷却系统的排气通道
CN106043680A (zh) * 2016-07-28 2016-10-26 易瓦特科技股份公司 航空发动机

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DE19711570A1 (de) * 1996-03-21 1997-10-30 Folger Wolfgang Luftfahrzeug
KR20110052370A (ko) * 2009-11-12 2011-05-18 (주)한성티앤아이 무인헬리콥터용 공냉식엔진 냉각장치
CN202414168U (zh) * 2011-11-29 2012-09-05 成都精石模型开发有限公司 一种能有效消除共振的多用途无人直升机
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Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN107489513A (zh) * 2017-09-22 2017-12-19 湖南省库塔科技有限公司 一种用于直升机的风冷系统
CN107489513B (zh) * 2017-09-22 2024-04-16 驼网网络科技南京有限公司 一种用于直升机的风冷系统
US11148820B1 (en) * 2018-02-19 2021-10-19 Parallel Flight Technologies, Inc. System defining a hybrid power unit for thrust generation in an aerial vehicle and method for controlling the same
US11993375B2 (en) 2018-02-19 2024-05-28 Parallel Flight Technologies, Inc. Method and apparatus for lifting a payload
US20230182916A1 (en) * 2020-12-28 2023-06-15 Parallel Flight Technologies, Inc. System defining a hybrid power unit for thrust generation in an aerial vehicle and method for controlling the same
US11858632B2 (en) * 2020-12-28 2024-01-02 Parallel Flight Technologies, Inc. System defining a hybrid power unit for thrust generation in an aerial vehicle and method for controlling the same

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