WO2018145355A1 - Aéronef à décollage et atterrissage verticaux à voilure fixe - Google Patents

Aéronef à décollage et atterrissage verticaux à voilure fixe Download PDF

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Publication number
WO2018145355A1
WO2018145355A1 PCT/CN2017/079204 CN2017079204W WO2018145355A1 WO 2018145355 A1 WO2018145355 A1 WO 2018145355A1 CN 2017079204 W CN2017079204 W CN 2017079204W WO 2018145355 A1 WO2018145355 A1 WO 2018145355A1
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WO
WIPO (PCT)
Prior art keywords
wing
vertical
landing
phase
aircraft
Prior art date
Application number
PCT/CN2017/079204
Other languages
English (en)
Chinese (zh)
Inventor
鲍静云
刘双
范晋红
殷兰兰
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 WO2018145355A1 publication Critical patent/WO2018145355A1/fr

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
    • B64C27/26—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed 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

Definitions

  • the present invention relates to the field of aircraft, and more particularly to a fixed-wing aircraft.
  • the fixed-wing aircraft has the advantages of high speed, long range, heavy load and high efficiency. However, compared with helicopter aircraft, the requirements for landing and landing are high. On the other hand, helicopters can achieve vertical take-off and landing, and have low requirements for landing and landing sites, but helicopters also have shortcomings such as slow flight speed and short flight range. Based on this, there is also a tilting rotorcraft in the prior art, in which the rotor is arranged according to the rotor structure of the helicopter when taking off, realizing the vertical take-off and landing of the aircraft, and the rotor rotates in flight according to the rotor structure of the fixed wing aircraft.
  • the tilt-rotor aircraft combines the characteristics of fixed-wing and helicopter, and has the advantages of vertical take-off and landing, fast speed, long range and heavy load. However, it also has the defects of high technical difficulty, complicated structure, poor stability, complicated control and operation. .
  • the present invention provides a vertical take-off and landing fixed-wing aircraft.
  • a vertical take-off and landing fixed-wing aircraft comprising a fuselage, a wing symmetrically distributed with respect to the fuselage, and a vertical tail that is symmetrically distributed with respect to the wing, and a rotor is disposed on the wing and the vertical tail, and At least the rotor on the vertical tail rotates independently.
  • the flight steps of the aircraft include a vertical take-off phase, a pre-cruise adjustment phase of the tilting flight after the take-off phase, a cruise phase after the pre-cruise adjustment phase, and a pre-landing adjustment phase after the cruise phase tilting of the fuselage and The vertical landing phase after the pre-landing adjustment phase.
  • the fuselage and the rotor are vertically distributed in the take-off phase and the landing phase.
  • the rotors located on the vertical tail rotate at different rotational speeds.
  • the landing gear provided at the lower end of the wing and the vertical tail is included.
  • the ailerons provided on the wing and the rudder provided on the vertical tail are included.
  • the length of the vertical tail is shorter than the length of the wing, the rotor on the vertical tail is disposed at the end corresponding to the vertical tail, and the rotor on the wing is disposed at the middle of the corresponding wing.
  • the invention has the advantages of fixed wing and helicopter aircraft, can realize vertical take-off and landing, reduce the requirements on the site, and at the same time, the speed, the range and the load capacity are greatly improved, and further, the invention passes through the whole fuselage
  • the tilting of the flight mode is compared with the tilting rotorcraft, which has the advantages of low technical difficulty, simple structure, good stability and simple operation.
  • Figure 1 is a perspective view of an embodiment of the present invention
  • Figure 2 is a front elevational view of one embodiment of the present invention.
  • Figure 3 is a plan view of an embodiment of the present invention.
  • Figure 4 is a flight trajectory diagram of the aircraft of the present invention.
  • the aircraft includes a fuselage 100, a wing 210, an aileron 220, a vertical tail 310, and a rudder 320.
  • the wings 210 are symmetrically distributed with respect to the body 100, and the vertical tails 310 are also symmetrically distributed with respect to the body 100, and the wires are perpendicular to the lines of the wings 210, that is, the body 100, the wings 210, and the vertical tails 310 are A cross-shaped structure is formed as shown in Figs. 1 and 2.
  • the length of the vertical tail 310 is preferably shorter than the length of the wing 210, the wing 210 with a larger wing area is mainly used to generate lift, and the vertical tail 310 is mainly used to achieve attitude adjustment of the fuselage.
  • the rotor 410 is driven by the motor 420.
  • one end of the motor 420 is connected to the rotor 410, and the other end is connected to the landing gear 500. More specifically, the motor 420 is fixed on the wing 210 or the vertical tail 310.
  • the rotor 410 is located on the wing 210 or the vertical wing 410.
  • the landing gear 500 is disposed at the lower end of the wing 210 or the vertical tail 310 (as shown in FIG. 3), and the fuselage 100 and the motor 420 preferably adopt a streamlined structure to reduce air resistance.
  • the rotor 410 on the vertical tail 310 is disposed at the end of the corresponding vertical tail 310, and the rotor 410 on the wing 210 is disposed at the middle of the corresponding wing 210.
  • the rotors 410 on the vertical tail 310 can be independently rotated. As for whether the rotors 410 on the wing 210 need to be independently rotated, they can be adjusted according to actual needs.
  • the ailerons 220 are disposed on the wing 210, the rudders 320 are disposed on the vertical tails 310, and the ailerons 220 and the rudders 320 are oscillated by the corresponding steering gear 600 to adjust the flight direction of the aircraft.
  • a flight trajectory diagram of the aircraft of the present invention is shown.
  • the flight steps of the aircraft include a vertical take-off phase, a pre-cruise adjustment phase of the slanted flight after the take-off phase, and a cruise phase after the pre-cruise adjustment phase, After the cruise phase, the pre-landing adjustment phase of the fuselage tilt and the vertical landing phase after the pre-landing adjustment phase are described in detail below:
  • the aircraft Before the take-off phase, the aircraft is placed vertically on the take-off plane by the landing gear, and the fuselage and the rotor are vertically distributed. As the motor is driven, the rotor provides vertical lift, which causes the aircraft to take off vertically in a cruciform quadrotor mode.
  • the rotors on the vertical tail rotate at different speeds. Because the lift provided by the two rotors is different, the fuselage gradually tilts toward the side with less lift. At this time, the wing and the horizontal plane will have a temperature less than 90 degrees.
  • the angle (angle of attack) the initial angle of attack is larger, the lift coefficient is smaller, and the wing can only produce a certain lift. As the aircraft further flies, the attitude of the fuselage is more inclined, the angle of attack becomes smaller and close to the critical value, and the lift generated by the wing is gradually increased.
  • the aircraft When the flight speed of the aircraft reaches a certain set value while maintaining a certain angle of attack, the aircraft is switched from the cruciform quadrotor mode to the fixed-wing flight mode. At this time, the wing and the rotor on the vertical tail rotate at the same speed, while the aileron and the aileron The rudder starts to control the aircraft.
  • the fuselage and the rotor in the cruising phase are distributed horizontally.
  • the aircraft When the aircraft is ready to land, the aircraft is placed in a rising tilt state by the ailerons, and the angle of attack is gradually increased until the aircraft is in a vertical climb state.
  • the aileron and the rudder stop working.
  • the aircraft is operated by controlling the speed of the rotor.
  • the aircraft is switched from the fixed wing mode to the cross quadrotor mode and vertically descended in a cross quadrotor mode.
  • the invention has the advantages of fixed wing and helicopter aircraft, can realize vertical take-off and landing, reduce the requirements on the site, and at the same time, the speed, the range and the load capacity are greatly improved, and further, the invention passes through the whole fuselage
  • the tilting of the flight mode is compared with the tilting rotorcraft, which has the advantages of low technical difficulty, simple structure, good stability and simple operation.

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

Abstract

L'invention concerne un aéronef à décollage et atterrissage verticaux à voilure fixe, comprenant un fuselage (100), des ailes (210) réparties symétriquement par rapport au fuselage (100), et des queues verticales (310) reliées verticalement aux ailes (210) et réparties symétriquement par rapport au fuselage (100). Des rotors (410) sont disposés sur les ailes (210) et les queues verticales (310), et au moins les rotors (410) situés sur les queues verticales (310) tournent de manière indépendante. L'aéronef présente aussi bien les avantages d'un aéronef à voilure fixe que ceux d'un hélicoptère, et peut effectuer un décollage et un atterrissage verticaux, réduisant ainsi les exigences pour un site, tandis que d'autre part, sa vitesse, son rayon d'action et sa charge utile sont considérablement améliorés. En outre, le mode de vol est commuté au moyen de l'inclinaison de l'ensemble du fuselage (100), de sorte que l'aéronef présente un faible niveau de difficulté technique, une structure simple, une bonne stabilité et est simple à piloter par rapport à un aéronef à ailes tournantes.
PCT/CN2017/079204 2017-02-13 2017-04-01 Aéronef à décollage et atterrissage verticaux à voilure fixe WO2018145355A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CN201720130129.3 2017-02-13
CN201720130129.3U CN206511122U (zh) 2017-02-13 2017-02-13 一种垂直起降固定翼飞行器

Publications (1)

Publication Number Publication Date
WO2018145355A1 true WO2018145355A1 (fr) 2018-08-16

Family

ID=59867587

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/CN2017/079204 WO2018145355A1 (fr) 2017-02-13 2017-04-01 Aéronef à décollage et atterrissage verticaux à voilure fixe

Country Status (2)

Country Link
CN (1) CN206511122U (fr)
WO (1) WO2018145355A1 (fr)

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN108284950A (zh) * 2017-11-30 2018-07-17 湖北航天飞行器研究所 四涵道螺旋桨动力方式的可垂直起降固定翼无人飞行器
WO2019116101A1 (fr) * 2017-12-12 2019-06-20 Spencer Cameron Système d'aéronef à décollage et atterrissage verticaux (vtol) à géométrie variable
CN108583869B (zh) * 2018-06-15 2024-03-29 西安航空学院 一种x形后掠翼无人机
CN109159890B (zh) * 2018-10-29 2023-06-09 南京拓兴智控科技有限公司 一种单旋翼垂直起降飞行器
CN110356553B (zh) * 2019-08-29 2023-06-20 吕福瑞 一种全旋翼飞行器
CN110562433A (zh) * 2019-09-16 2019-12-13 北京理工大学珠海学院 X翼无人机
CN110683030A (zh) * 2019-10-25 2020-01-14 中国航空工业集团公司西安飞行自动控制研究所 一种可垂直起降无人飞行器

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5516060A (en) * 1993-03-29 1996-05-14 Mcdonnell; William R. Vertical take off and landing and horizontal flight aircraft
US20140217229A1 (en) * 2011-09-27 2014-08-07 Singapore Technologies Aerospace Ltd Unmanned aerial vehicle
CN105329441A (zh) * 2015-11-30 2016-02-17 保定维特瑞交通设施工程有限责任公司 一种组合式四轴飞翼飞行器
CN106143898A (zh) * 2016-08-08 2016-11-23 北京奇正数元科技股份有限公司 一种垂直起降倾转旋翼固定翼飞机

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5516060A (en) * 1993-03-29 1996-05-14 Mcdonnell; William R. Vertical take off and landing and horizontal flight aircraft
US20140217229A1 (en) * 2011-09-27 2014-08-07 Singapore Technologies Aerospace Ltd Unmanned aerial vehicle
CN105329441A (zh) * 2015-11-30 2016-02-17 保定维特瑞交通设施工程有限责任公司 一种组合式四轴飞翼飞行器
CN106143898A (zh) * 2016-08-08 2016-11-23 北京奇正数元科技股份有限公司 一种垂直起降倾转旋翼固定翼飞机

Also Published As

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