WO2013056492A1 - Avion composite constitué d'une voilure fixe et d'hélices à commande électrique et doté de fonctions d'hélicoptère - Google Patents

Avion composite constitué d'une voilure fixe et d'hélices à commande électrique et doté de fonctions d'hélicoptère Download PDF

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Publication number
WO2013056492A1
WO2013056492A1 PCT/CN2011/083301 CN2011083301W WO2013056492A1 WO 2013056492 A1 WO2013056492 A1 WO 2013056492A1 CN 2011083301 W CN2011083301 W CN 2011083301W WO 2013056492 A1 WO2013056492 A1 WO 2013056492A1
Authority
WO
WIPO (PCT)
Prior art keywords
aircraft
wing
blade
fixed
helicopter
Prior art date
Application number
PCT/CN2011/083301
Other languages
English (en)
Chinese (zh)
Inventor
田瑜
江文彦
Original Assignee
Tian Yu
Jiang Wenyan
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 Tian Yu, Jiang Wenyan filed Critical Tian Yu
Publication of WO2013056492A1 publication Critical patent/WO2013056492A1/fr

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
    • B64C29/0008—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded
    • B64C29/0016—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers
    • B64C29/0025—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers the propellers being fixed relative to the fuselage

Definitions

  • the rotor that is directly connected to the power system is far less efficient than the wing of a fixed-wing aircraft, so power consumption is large. Because its forward speed is mainly provided by the component force generated by the tilting of the rotor paddle through the swash plate, the resistance of the helicopter to fly forward is also much larger than that of the fixed-wing aircraft. Therefore, its flight speed, distance and endurance are not as good as fixed-wing aircraft. For this reason, technicians in the aerospace industry have been looking for aircraft that combine the advantages of fixed-wing aircraft and helicopters.
  • the separate lift engine is simple in design, the lift engine does not work during cruising, and it takes up the internal volume, which is dead weight. Reducing or eliminating dead weight is an urgent problem for vertical landing aircraft.
  • the most straightforward way to combine cruise and lift engines is to tilt the jet engine and blow the engine directly to the ground, which of course produces direct lift. So simple, why not the first choice for vertical landing aircraft? First, tilting the engine imposes significant limitations on the position of the engine on the aircraft.
  • the paddles are respectively disposed on both sides of the fuselage and upper and lower sides of the wing, and are symmetrically placed with respect to the center of gravity of the aircraft.
  • each of the electric multi-blade power systems or paddles is coupled to the fuselage or wing by a support arm.
  • the angle of attack angle is 10° -30°.
  • the paddle is a foldable paddle.
  • the aircraft comprises a fixed wing power system.
  • the fixed wing power system is electric or fuel powered.
  • the electronic gyro can be used to control the speed of four paddles to form a stable rotor helicopter flight platform. By changing the paddle speed, the lift and torque of the four blades are changed to control the flight and steering of the rotor helicopter in all directions.
  • the electronic gyro is a commonly used device in the field, and the technician can select the type according to the specific needs.

Abstract

La présente invention a trait à un avion composite constitué d'une voilure fixe et d'hélices à commande électrique, et doté de fonctions d'hélicoptère, lequel avion composite comprend un ensemble avion à voilure fixe. L'ensemble comprend un corps d'avion (1), des ailes (2) et un système de commande (61) de la surface de gouverne de direction de voilure fixe. L'avion comprend en outre un système électrique (4) pour les hélices à commande électrique et un organe de commande général (6). L'organe de commande général (6) comprend le système de commande (61) de la surface de gouverne de direction de voilure fixe et un système de commande (62) des hélices à commande électrique. L'organe de commande général (6) est en outre utilisé de manière à contrôler le système de commande (61) de la surface de gouverne de direction de voilure fixe et le système de commande (62) des hélices à commande électrique de sorte qu'ils fonctionnent séparément ou de façon coordonnée. Le plan de rotation de la pale du système électrique (4) des hélices à commande électrique est perpendiculaire à l'axe central du corps d'avion. L'avion composite constitué de la voilure fixe et des hélices à commande électrique peut non seulement décoller, atterrir et voler à la verticale comme un hélicoptère, mais aussi décoller, atterrir et voler comme un avion à voilure fixe, ou décoller en mode hélicoptère, voler en mode voilure fixe puis atterrir en mode hélicoptère.
PCT/CN2011/083301 2011-10-17 2011-12-01 Avion composite constitué d'une voilure fixe et d'hélices à commande électrique et doté de fonctions d'hélicoptère WO2013056492A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CN201120397882.1 2011-10-17
CN 201120397882 CN202728574U (zh) 2011-10-17 2011-10-17 固定翼与电动多桨组成的具有直升机功能的复合飞行器

Publications (1)

Publication Number Publication Date
WO2013056492A1 true WO2013056492A1 (fr) 2013-04-25

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PCT/CN2011/083301 WO2013056492A1 (fr) 2011-10-17 2011-12-01 Avion composite constitué d'une voilure fixe et d'hélices à commande électrique et doté de fonctions d'hélicoptère

Country Status (2)

Country Link
CN (1) CN202728574U (fr)
WO (1) WO2013056492A1 (fr)

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* Cited by examiner, † Cited by third party
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JP2022016568A (ja) * 2020-02-27 2022-01-21 義郎 中松 翼回転垂直離着陸長距離航空機

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CN103640690A (zh) * 2013-09-02 2014-03-19 张更生 一种改变飞机发动机垂直起落与快速飞行的方法
CN105173076B (zh) * 2015-09-29 2018-09-14 广西圣尧航空科技有限公司 一种垂直起降无人机
CN105346725A (zh) * 2015-09-29 2016-02-24 上海圣尧智能科技有限公司 一种垂直起降无人机
CN106114854B (zh) * 2016-08-09 2019-06-25 烟台中飞海装科技有限公司 一种无人驾驶航空器
CN106114853B (zh) * 2016-08-09 2019-05-10 烟台中飞海装科技有限公司 一种无人驾驶航空器
CN107021219B (zh) * 2017-04-07 2020-06-09 南昌航空大学 固定翼无人机及其控制方法
US10053213B1 (en) * 2017-05-08 2018-08-21 Pinnacle Vista, LLC Multi-copter lift body aircraft with tail pusher
CN109305356A (zh) * 2017-08-29 2019-02-05 陕西安康领航智能股份有限公司 一种倾转式垂直起降无人机
JP6609760B1 (ja) * 2018-09-22 2019-11-27 株式会社エアロネクスト 飛行体
CN110203387A (zh) * 2019-05-09 2019-09-06 深圳市禾启智能科技有限公司 垂直起降固定翼飞行器
CN112849403B (zh) * 2019-11-26 2023-09-29 上海峰飞航空科技有限公司 无人飞行器及其控制方法
JP6736198B1 (ja) * 2020-06-18 2020-08-05 株式会社エアロネクスト 飛行体

Citations (4)

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ES2015827A6 (es) * 1989-10-10 1990-09-01 Del Campo Aguilera Juan Aeronave porta-equipos telecomandada.
CN101549754A (zh) * 2009-04-29 2009-10-07 北京航空航天大学 一种旋定翼复合式飞行器及其设计的方法
CN102133926A (zh) * 2011-03-08 2011-07-27 上海大学 一种尾坐式垂直起降无人飞行器
CN201923320U (zh) * 2011-01-13 2011-08-10 杨苡 双发动机垂直起降固定翼无人机

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
ES2015827A6 (es) * 1989-10-10 1990-09-01 Del Campo Aguilera Juan Aeronave porta-equipos telecomandada.
CN101549754A (zh) * 2009-04-29 2009-10-07 北京航空航天大学 一种旋定翼复合式飞行器及其设计的方法
CN201923320U (zh) * 2011-01-13 2011-08-10 杨苡 双发动机垂直起降固定翼无人机
CN102133926A (zh) * 2011-03-08 2011-07-27 上海大学 一种尾坐式垂直起降无人飞行器

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2022016568A (ja) * 2020-02-27 2022-01-21 義郎 中松 翼回転垂直離着陸長距離航空機

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