WO2019090999A1 - Aéronef à voilure fixe à décollage et atterrissage verticaux - Google Patents

Aéronef à voilure fixe à décollage et atterrissage verticaux Download PDF

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Publication number
WO2019090999A1
WO2019090999A1 PCT/CN2018/075102 CN2018075102W WO2019090999A1 WO 2019090999 A1 WO2019090999 A1 WO 2019090999A1 CN 2018075102 W CN2018075102 W CN 2018075102W WO 2019090999 A1 WO2019090999 A1 WO 2019090999A1
Authority
WO
WIPO (PCT)
Prior art keywords
semi
wing
fuselage
annular
fixed
Prior art date
Application number
PCT/CN2018/075102
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English (en)
Chinese (zh)
Inventor
殷兰兰
鲍静云
范晋红
王威
胡蒋东
郑万福
Original Assignee
深圳市龙云创新航空科技有限公司
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 深圳市龙云创新航空科技有限公司 filed Critical 深圳市龙云创新航空科技有限公司
Publication of WO2019090999A1 publication Critical patent/WO2019090999A1/fr

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Classifications

    • 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
    • B64U30/21—Rotary wings
    • 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00—Type of UAV
    • B64U10/25—Fixed-wing aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U50/00—Propulsion; Power supply
    • B64U50/10—Propulsion
    • B64U50/19—Propulsion using electrically powered motors

Definitions

  • the invention relates to the field of aircrafts, and in particular to a fixed-wing aircraft for vertical take-off and landing.
  • the existing drone models mainly include helicopters and fixed-wing aircraft.
  • helicopter can take off and land vertically, has strong maneuverability, but has weak endurance and small load;
  • fixed-wing aircraft has strong endurance, but requires specific runway take-off and landing, and has special requirements for the take-off and landing environment.
  • the prior art also describes a multi-rotor UAV.
  • the multi-rotor UAV usually installs multiple rotors on the fixed-wing fuselage, and uses the rotor to achieve vertical take-off and landing.
  • the operation is flexible and the mobility is strong, but the battery life is short.
  • the load capacity is weak.
  • the present invention provides a fixed-wing aircraft with vertical take-off and landing.
  • the characteristics of long-life and large load of the fixed-wing aircraft can be combined with the characteristics of multi-rotor vertical take-off and landing and strong maneuverability.
  • the present invention provides a vertical take-off and landing fixed-wing aircraft with reduced volume, weight reduction, flexibility, load capacity and endurance.
  • a fixed-wing aircraft for vertical take-off and landing includes: a fuselage, a semi-annular wing symmetrically distributed with respect to the left and right sides of the fuselage, wherein the semi-annular wing is provided with a propeller rotating axially around the semi-annular wing;
  • the semi-annular wing and the propeller are rotatable integrally about an axis perpendicular to the fuselage; when the semi-annular wing and the propeller are rotated to a horizontal position, the drone moves up and down vertically; the semi-annular wing and the semi-annular wing When the propeller is rotated to the upright position, the drone is cruising horizontally.
  • the method further includes two rotating shafts perpendicular to the fuselage, and the two rotating shafts have four shaft ends, and each of the shaft ends is fixedly connected to one of the semi-annular wings;
  • the shaft can be rotated about its own axis.
  • the four semi-annular wings are in the same horizontal plane, and the semi-annular wings on the same side of the fuselage are facing front and rear.
  • the middle portion of the rotating shaft is connected to the fuselage through a connecting block, and the fixed portion of the connecting block is fixedly connected with the body, and the rotating portion of the connecting block can be opposite to the The fuselage is raised or lowered.
  • the semi-annular wing when the rotating portion of the connecting block is raised, the semi-annular wing is horizontally disposed with its toroid facing forward along the fuselage.
  • the semi-annular wing when the rotating portion of the connecting block is lowered, the semi-annular wing is vertically disposed, and the annular surface of the semi-annular wing faces downward with respect to the fuselage.
  • the propeller when the semi-annular wing is horizontally disposed, the propeller is adjacent to a lower edge of the semi-annular wing.
  • the empennage is further included, the empennage being located at the tail of the fuselage, the empennage including a vertical tail and a horizontal tail connected to each other.
  • a support frame is further included, the support frame being distributed symmetrically with respect to the fuselage under the fuselage.
  • the invention provides a semi-annular wing symmetrically disposed on the left and right sides of the fuselage, an axially rotating propeller around the semi-annular wing in the semi-annular wing, and the semi-annular wing propeller is integrally rotated about an axis perpendicular to the fuselage, through Adjusting the attitude of the semi-annular wing and the propeller to realize the vertical take-off, hovering and cruising of the drone, prolonging the life of the drone, replacing the traditional fixed wing with a semi-annular wing, reducing the volume of the drone and The weight increases the load capacity and flexibility of the drone, and the drone runs smoothly and has good aerodynamic performance.
  • FIG. 1 is a schematic structural view of an embodiment of the present invention
  • Figure 2 is a partial structural view of an embodiment of the present invention.
  • FIG. 3 is a schematic diagram of a posture of horizontal cruising according to an embodiment of the present invention.
  • Fig. 4 is a schematic view showing the attitude of vertical take-off and landing in an embodiment of the present invention.
  • the vertical-wing fixed-wing aircraft includes:
  • the semi-annular wing of the present invention does not exactly refer to half of the circular annulus, but rather to a portion of the circular annulus.
  • the left and right sides of the unmanned vehicle body 1 are symmetrically provided with a semi-annular wing 2, and the semi-annular wing 2 is provided with a propeller 3 which is rotatable about the axial direction of the semi-annular wing 2, a semi-annular wing 2 and a propeller 3
  • the body can be integrally rotated about an axis perpendicular to the body 1, and the attitude of the semi-annular wing 2 and the propeller 3 relative to the body 1 is adjusted according to the flight phase of the drone.
  • the semi-annular wing 2 When the drone is in the process of vertical take-off and landing, the semi-annular wing 2 is horizontally disposed, and the propeller 3 in the semi-annular wing 2 is also in a horizontal posture, and the motor drives the propeller 3 to rotate to cause a pressure difference between the upper and lower surfaces of the drone to increase the motor output. The power makes the drone finally get the upward lift.
  • the lift is greater than the gravity of the drone, the vertical take-off of the drone can be realized.
  • the output power of the motor When the output power of the motor is reduced, the lift obtained by the drone is reduced and gradually decreases vertically. .
  • the drone When the pulling force is in opposition to the gravity of the drone, the drone is in a hovering state.
  • the control system (not shown) that rotates the semi-annular wing 2 and the propeller 3 in the semi-annular wing 2 about an axis perpendicular to the fuselage 1 until the semi-annular wing 2 and the propeller 3 In the vertical direction, the motor drives the propeller 3 to rotate, and the airflow coming from the front of the wing passes through the acceleration of the propeller 3 and quickly passes through the semi-annular wing 2, forming a negative pressure zone in the semi-annular wing 2; whereas the conventional fixed-wing aircraft is Through the airfoil curvature, the airflow creates a pressure difference on the upper and lower surfaces of the wing when the airflow passes through the wing to lift the wing, so the semi-annular wing can obtain greater lift than the conventional wing, thereby improving the life of the drone.
  • the design of the semi-annular wing increases the difference between the maximum speed and the minimum speed of the drone
  • the above structure realizes the vertical take-off, hovering and cruising of the drone by adjusting the attitude of the semi-annular wing 2 and the propeller 3, prolonging the life time of the drone, and replacing the conventional fixed wing with the semi-annular wing 2, thereby reducing the
  • the size and weight of the drone increase the load capacity of the drone, and the drone runs smoothly and has good aerodynamic performance.
  • two rotating shafts 4 perpendicular to the fuselage 1 are disposed, and the middle portion of the rotating shaft 4 is connected with the fuselage 1 , and the four axial ends of the two rotating shafts 4 are respectively fixedly connected to one.
  • the semi-annular wing 2 provides sufficient power for the flight of the drone, and the rotating shaft 4 can rotate around its own axis to drive the semi-annular wing 2 and the propeller 3 to rotate, and has a simple structure and convenient operation.
  • the four semi-annular wings 2 are in the same horizontal plane, the center of gravity of the drone is stable, and the semi-annular wings 2 on the same side of the fuselage 1 are facing front and rear, thus, in the absence of During the horizontal cruising of the man-machine, the semi-annular wing 2 on the same side of the fuselage 1 forms a wing, and the propeller accelerates the airflow in front of the drone to reach the propeller at the rear at a higher speed, which can be located at the rear of the propeller. A greater negative pressure is created in the semi-annular wing, further increasing the lift obtained by the drone.
  • the intermediate portions of the two rotating shafts 4 are respectively connected to the body 1 through a connecting block, and the fixing portion 9 of the connecting block is fixedly connected with the body 1, and the connecting block is connected.
  • the rotating portion 5 can be lifted or lowered relative to the body 1.
  • the drone is in a state of vertical take-off and landing, and at this time, the center of gravity of the drone sinks with the lifting of the rotating portion 5 of the connecting block, and the stability of the drone is improved.
  • the fuselage 1 is smoothly lifted; when the rotating portion 5 of the connecting block is lowered, the drone is in a state of horizontal cruising, and the center of gravity of the drone is increased as the rotating portion 5 of the connecting block is lowered, and the drone is flexible. Enhancement is conducive to the change of the state of motion such as turning and speed change.
  • the toroidal surface of the semi-annular wing 2 is disposed forward along the body 1, and the rotating portion 5 of the connecting block is lowered.
  • the toroidal surface of the semi-annular wing 2 is disposed downward with respect to the fuselage 1, which can effectively reduce the wind resistance of the drone during the movement.
  • the rotating portion 5 of the connecting block when the rotating portion 5 of the connecting block is raised, the semi-annular wing 2 is horizontally disposed, and at this time, the propeller 3 is close to the lower edge of the semi-annular wing 2, and the drone is reduced. Wind resistance received during vertical takeoff and landing.
  • the tail of the fuselage 1 is provided with a vertical tail 6 and a horizontal tail 7 connected to each other for flexible adjustment of the posture of the drone during flight.
  • a support frame 8 symmetrically distributed with respect to the left and right sides of the fuselage 1 is disposed.
  • the support frame 8 functions to support the protection body 1 during the vertical take-off and landing of the drone.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Toys (AREA)

Abstract

Un aéronef à voilure fixe à décollage et atterrissage verticaux comprend un fuselage et des ailes semi-circulaires (2) réparties symétriquement par rapport au fuselage sur la gauche et sur la droite. Des hélices (3) tournant autour des directions axiales des ailes semi-circulaires sont disposées dans les ailes semi-circulaires. Les ailes semi-circulaires sont disposées symétriquement sur le côté gauche et le côté droit du fuselage, les hélices tournant autour des directions axiales des ailes semi-circulaires sont disposées dans les ailes semi-circulaires, et les ailes semi-circulaires ainsi que les hélices tournent d'un seul tenant autour de l'axe perpendiculaire au fuselage ; un aéronef sans pilote décolle et atterrit verticalement, est en vol stationnaire et poursuit sa course en ajustant les attitudes des ailes semi-circulaires et des hélices, réduisant ainsi la durée de vol de l'aéronef sans pilote ; en remplaçant les ailes fixes classiques par les ailes semi-circulaires, le volume et le poids de l'aéronef sans pilote sont réduits, la capacité de chargement et la flexibilité de l'aéronef sans pilote sont améliorées, le fonctionnement de l'aéronef sans pilote est stable, et la performance aérodynamique de l'aéronef sans pilote est bonne.
PCT/CN2018/075102 2017-11-10 2018-02-02 Aéronef à voilure fixe à décollage et atterrissage verticaux WO2019090999A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CN201711107693.4A CN107878747B (zh) 2017-11-10 2017-11-10 一种垂直起降的固定翼飞行器
CN201711107693.4 2017-11-10

Publications (1)

Publication Number Publication Date
WO2019090999A1 true WO2019090999A1 (fr) 2019-05-16

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CN (1) CN107878747B (fr)
WO (1) WO2019090999A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11472545B2 (en) 2020-04-21 2022-10-18 Liviu Grigorian Giurca Propulsion system and aircraft with vertical take-off and landing-VTOL

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112550694B (zh) * 2020-12-08 2023-05-05 清华大学 一种基于混合电推进系统的垂直起降倾转动力翼飞机
CN114313259A (zh) * 2021-12-30 2022-04-12 中国人民解放军总参谋部第六十研究所 一种纵向滚翼单元及基于该纵向滚翼单元的纵向滚翼飞行器
US20240174348A1 (en) * 2022-11-28 2024-05-30 Jonathan Christian Russ Electric Motor Propeller System

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WO2015189684A1 (fr) * 2014-06-12 2015-12-17 BERMOND, Gérome Aéronef convertible à aile basculante
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CN105775131A (zh) * 2016-02-26 2016-07-20 杭州深空实业股份有限公司 空中姿态可变形的无人飞行器
CN106132825A (zh) * 2013-12-23 2016-11-16 李尚泫 多旋翼飞行体
CN207510713U (zh) * 2017-11-10 2018-06-19 深圳市龙云创新航空科技有限公司 一种垂直起降的固定翼飞行器

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FR3041930B1 (fr) * 2015-10-05 2022-02-25 La Broise Denis Pierre Marie De Aeronef a decollage et atterrissage vertical, a ailes circulaires et cockpit basculant, pilote par controle differentiel des propulseurs
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US20030080242A1 (en) * 2001-10-31 2003-05-01 Hideharu Kawai Vertical takeoff and landing aircraft
KR20090067686A (ko) * 2007-12-21 2009-06-25 한국항공우주연구원 틸트-덕트 비행체 및 상기 비행체의 자세제어
CN106132825A (zh) * 2013-12-23 2016-11-16 李尚泫 多旋翼飞行体
WO2015189684A1 (fr) * 2014-06-12 2015-12-17 BERMOND, Gérome Aéronef convertible à aile basculante
CN105270625A (zh) * 2015-10-23 2016-01-27 庆安集团有限公司 一种多用途垂直起降无人机
CN105775131A (zh) * 2016-02-26 2016-07-20 杭州深空实业股份有限公司 空中姿态可变形的无人飞行器
CN207510713U (zh) * 2017-11-10 2018-06-19 深圳市龙云创新航空科技有限公司 一种垂直起降的固定翼飞行器

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11472545B2 (en) 2020-04-21 2022-10-18 Liviu Grigorian Giurca Propulsion system and aircraft with vertical take-off and landing-VTOL

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CN107878747B (zh) 2024-06-11
CN107878747A (zh) 2018-04-06

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