CN106741916A - 一种涵道式无人飞行器矢量动力组件 - Google Patents
一种涵道式无人飞行器矢量动力组件 Download PDFInfo
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- CN106741916A CN106741916A CN201710078960.3A CN201710078960A CN106741916A CN 106741916 A CN106741916 A CN 106741916A CN 201710078960 A CN201710078960 A CN 201710078960A CN 106741916 A CN106741916 A CN 106741916A
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- 230000008450 motivation Effects 0.000 claims 1
- 230000000694 effects Effects 0.000 abstract description 4
- 230000009187 flying Effects 0.000 description 2
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/20—Rotorcraft characterised by having shrouded rotors, e.g. flying platforms
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/82—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft
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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
- 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
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- 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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/20—Rotors; Rotor supports
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- 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
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
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- Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
Abstract
本发明提供了一种结构紧凑、设计合理、易于操控、油耗低、整流效果好的涵道式无人飞行器。通过对涵道式无人机的各部件进行优化,相较于传统的涵道式无人机具有明显的优点。
Description
技术领域
本发明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矢量动力组件。
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。传统的涵道式无人飞行器具有垂直起降和悬停的优点,但也同样存在缺陷,例如,燃油动力的涵道式无人飞行器通常采用风冷因而冷却效果差,导致发动机难以有效降低温度,从而增加油耗;另外,涵道式无人飞行器的扭矩平衡通常采用6片或8片结构,因而,整流效率有待于进一步的提高。
发明内容
为了克服现有技术中的不足,本发明提供了一种涵道式无人飞行器矢量动力组件,其特征在于,所述涵道式无人飞行器矢量动力组件包括,环形油箱涵道体、起落架、顶置发动机、五叶螺旋桨、扭矩平衡片、导流板、方向姿态控制器、安装盘;所述涵道式无人飞行器矢量动力组件的顶部设置安装盘,所述安装盘能够可拆卸安装任务设备;所述涵道式无人飞行器矢量动力组件的安装盘下部设置顶置发动机,所述顶置发动机下部安装所述五叶螺旋桨;所述扭矩平衡片和导流板共同设置在所述五叶螺旋桨下部的涵道体内,并且扭矩平衡片和导流板在垂直方向上呈上下设置,扭矩平衡片的下边缘和导流板的上边缘在同一水平面内;所述方向姿态控制器安装在所述导流板上;所述扭矩平衡片为逆向切线扭矩平衡片,共有16片组成;所述方向姿态控制器共有8组,分别控制姿态和方向;所述顶置发动机上还设置有冷却装置。
有益效果:该矢量动力控制组件结构紧凑、使用安全、可垂直起降、可稳定悬停、可安装模块化载荷设备、也可作为垂直起降固定翼飞行器的推进装置来使用。通过在涵道式无人飞行器的顶部设置安装盘能够可拆卸的安装载荷设备扩展了涵道式无人机的用途,并且采用逆向切线分布式扭矩平衡片,能把螺旋浆产生的旋转气流汇聚在一起平滑无阻导出,不但整流效率高而且没有任何升力损失,平衡扭矩的作用也非常强,并且通过优化导流板和扭矩平衡片的位置和数量以及采用分别控制姿态和方向的姿态方向控制器达到了在整流效率提高的同时提高了对姿态和方向的稳定控制,实现了对姿态和方向的解耦控制,以及显著降低了升力的损耗和飞行的不稳定性。另外,顶置发动机上部设置冷却装置能够提高发动机的冷却效果,降低发动机的油耗。
附图说明
图1为涵道式无人飞行器矢量动力组件,(1)安装盘,(2)顶置发动机,(3)五叶螺旋桨,(4)方向姿态控制器,(5)导流板,(6)扭矩平衡片。
Claims (1)
1.一种涵道式无人飞行器矢量动力组件,其特征在于,所述涵道式无人飞行器矢量动力组件包括,环形油箱涵道体、起落架、顶置发动机、五叶螺旋桨、扭矩平衡片、导流板、方向姿态控制器、安装盘;所述涵道式无人飞行器矢量动力组件的顶部设置安装盘,所述安装盘能够可拆卸安装任务设备;所述涵道式无人飞行器矢量动力组件的安装盘下部设置顶置发动机,所述顶置发动机下部安装所述五叶螺旋桨;所述扭矩平衡片和导流板共同设置在所述五叶螺旋桨下部的涵道体内,并且扭矩平衡片和导流板在垂直方向上呈上下设置,扭矩平衡片的下边缘和导流板的上边缘在同一水平面内;所述方向姿态控制器安装在所述导流板上;所述扭矩平衡片为逆向切线扭矩平衡片,共有16片组成;所述方向姿态控制器共有8组,分别控制姿态和方向;所述顶置发动机上还设置有冷却装置。
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Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN108791909A (zh) * | 2018-07-16 | 2018-11-13 | 飞瑞航空科技(江苏)有限公司 | 一种无人机发动机安装机构 |
Citations (5)
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US20080054121A1 (en) * | 2006-05-11 | 2008-03-06 | Urban Aeronautics Ltd. | Ducted fan VTOL vehicles |
CN103587685A (zh) * | 2013-11-11 | 2014-02-19 | 中国南方航空工业(集团)有限公司 | 飞行器 |
CN104960666A (zh) * | 2015-05-26 | 2015-10-07 | 北京理工大学 | 一种纵列双涵道飞行车辆的可倾转矢量控制辅助系统 |
EP2985220A1 (en) * | 2014-08-11 | 2016-02-17 | Dusan Milivoi Stan | Apparatus and method for providing control and augmenting thrust at reduced speed and ensuring reduced drag at increased speed |
CN106828914A (zh) * | 2017-02-09 | 2017-06-13 | 深圳市航宇航空科技有限公司 | 一种基于涵道式动力矢量组件的模块化垂直起降固定翼无人飞行器 |
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- 2017-02-14 CN CN201710078960.3A patent/CN106741916A/zh active Pending
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20080054121A1 (en) * | 2006-05-11 | 2008-03-06 | Urban Aeronautics Ltd. | Ducted fan VTOL vehicles |
CN103587685A (zh) * | 2013-11-11 | 2014-02-19 | 中国南方航空工业(集团)有限公司 | 飞行器 |
EP2985220A1 (en) * | 2014-08-11 | 2016-02-17 | Dusan Milivoi Stan | Apparatus and method for providing control and augmenting thrust at reduced speed and ensuring reduced drag at increased speed |
CN104960666A (zh) * | 2015-05-26 | 2015-10-07 | 北京理工大学 | 一种纵列双涵道飞行车辆的可倾转矢量控制辅助系统 |
CN106828914A (zh) * | 2017-02-09 | 2017-06-13 | 深圳市航宇航空科技有限公司 | 一种基于涵道式动力矢量组件的模块化垂直起降固定翼无人飞行器 |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN108791909A (zh) * | 2018-07-16 | 2018-11-13 | 飞瑞航空科技(江苏)有限公司 | 一种无人机发动机安装机构 |
CN108791909B (zh) * | 2018-07-16 | 2023-09-22 | 飞瑞航空科技(江苏)有限公司 | 一种无人机发动机安装机构 |
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