WO2009149592A1 - Avion à décollage et atterrissage à la verticale - Google Patents

Avion à décollage et atterrissage à la verticale Download PDF

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Publication number
WO2009149592A1
WO2009149592A1 PCT/CN2008/002094 CN2008002094W WO2009149592A1 WO 2009149592 A1 WO2009149592 A1 WO 2009149592A1 CN 2008002094 W CN2008002094 W CN 2008002094W WO 2009149592 A1 WO2009149592 A1 WO 2009149592A1
Authority
WO
WIPO (PCT)
Prior art keywords
rotor
shaft
cabin
rotor shaft
aircraft
Prior art date
Application number
PCT/CN2008/002094
Other languages
English (en)
Chinese (zh)
Inventor
张庆柳
Original Assignee
Zhang Qingliu
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 Zhang Qingliu filed Critical Zhang Qingliu
Publication of WO2009149592A1 publication Critical patent/WO2009149592A1/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
    • B64C27/30—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with provision for reducing drag of inoperative rotor
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/04—Helicopters
    • B64C27/08—Helicopters with two or more rotors

Definitions

  • the present invention relates to an aircraft, and more particularly to a vertical takeoff and landing aircraft. Background technique
  • the vertical take-off and landing aircraft have developed five major types: tailstock type, tilting force device type, thrust steering type, special lift power unit type and the above three types of hybrid configuration, typical representatives such as Boeing Company of the United States V-22 tilt-rotor aircraft, British " ⁇ "-type deflection nozzle vertical take-off and landing aircraft, the US Lockheed Martin F-35B uses a lift fan and an afterburning turbofan engine with a steering vector nozzle Short takeoff / vertical landing aircraft.
  • Several of these vertical take-off and take-off/vertical landing aircraft have been put into use, as they do not require special airports and runways, making them more effective in increasing maneuverability and flexibility in warfare. But at the same time, there are also many major shortcomings.
  • the speed of the tilting rotorcraft can only be within 400 km/h during the leveling, and the " ⁇ " type deflection nozzle is used for vertical take-off and landing.
  • the take-off weight of the aircraft can only be 83%-85% of the engine thrust, which greatly limits the aircraft's payload, affecting the aircraft's fuel load and range.
  • the engine works at its maximum state when the aircraft takes off vertically.
  • the amount of oil is extremely large, which limits the operational radius of the aircraft.
  • the F-35B developed by Lockheed Martin of the United States uses a lift fan and a short-range take-off/vertical landing aircraft with a steering vector nozzle, due to the lift fan and belt steering.
  • the lift generated by the vector nozzle is not enough to make the aircraft take off and land vertically. It can only change the pain to short takeoff/vertical takeoff and landing, which greatly reduces the maneuverability of the aircraft.
  • the increase of engine power is very much under current technical conditions. hard. Summary of the invention The invention overcomes the deficiencies of the prior art, and provides a vertical take-off and landing aircraft which has a simple structure, is easy to manufacture, can take off and land vertically, and can fly at a high speed.
  • the top of the aircraft is equipped with an openable and rotatable rotor cabin. When the aircraft moves up and down, the rotor cabin is opened.
  • the rotor shaft expansion device extends the rotor shaft and the rotor connected to the rotor shaft out of the rotor cabin.
  • the rotor automatic positioning device automatically closes the rotor and opens the rotor cabin.
  • the rotor shaft expansion device shrinks the rotor shaft and the rotor into the rotor cabin, the rotor cabin is closed, and the aircraft enters a normal level flight state.
  • a vertical take-off and landing aircraft including a cockpit, a fuselage, an aeroengine, a wing, a horizontal tail, a vertical tail, a speed reducer and a control system, and an aeroengine through a drive shaft
  • the clutch is connected to the reducer, the rear of the aircraft engine is equipped with a steering vector tail nozzle, and the upper part of the fuselage is equipped with a rotor, and the rotor is connected with a rotor shaft, and the vertical takeoff and landing aircraft is further provided with a rotor shaft expansion device and can be accommodated
  • An openable and rotatable rotor nacelle of the gathered rotor, the openable and rotatable rotor nacelle is disposed on a top of the fuselage, the rotor shaft is coupled to the reducer and the rotor shaft telescopic device, and the rotor is equipped with a rotor
  • the automatic positioning device is provided with a rotor
  • the rotor automatic positioning device is composed of an elastic member and a limiting member for automatically positioning the rotor in a position parallel to the body.
  • the rotor shaft automatic positioning device is constituted by a positioning member and a locking member, and when the rotor is folded, the rotor shaft is fixed at a position parallel to the rotor capsule after the rotor is gathered.
  • the rotor shaft expansion device includes a hydraulic telescopic member for extending the rotor shaft, the rotor, or the contraction into the rotor module.
  • the rotor cabin is provided with a rotor wing cover plate, and when the aircraft is vertically taken off and landing, the rotor wing cover plate is folded and folded to the left and right sides, so that the gathered rotor can extend or retract into the rotor cabin, when the aircraft When flying flat, the rotor gathers and retracts into the rotor cabin.
  • the rotor pod cover is closed toward the middle to close the rotor pod.
  • the rotor structure at the upper portion of the fuselage may be a coaxial reversing double rotor, and the rotor shaft is a coaxial reversing rotor shaft.
  • the reducer is coupled to a plurality of aircraft engines via a corresponding drive shaft and clutch, and an auxiliary aeroengine is mounted on the vertical tail.
  • the aero-engine is equipped with a propeller in front of it, and the auxiliary aero-engine is equipped with a propeller.
  • the front and rear parts of the rotor cabin are respectively equipped with rotors with opposite rotation directions and corresponding automatic positioning devices for the rotors, rotor shafts, reducers, automatic positioning devices for the rotor shafts, rotor shaft expansion devices, transmission shafts, and aero engines.
  • the vertical tail is installed downwards.
  • the rotor structure of the upper part of the vertical take-off and landing aircraft fuselage is a coaxial double-rotor, the rotor shaft is a coaxial reversing rotor shaft, the front part of the aero-engine is connected with the propeller through the clutch and the transmission shaft, and the rear is driven by the clutch and the transmission shaft.
  • the rear of the fuselage is equipped with an adjustable rotor fixed rod.
  • the utility of the vertical take-off and landing aircraft provided by the invention has the advantages of simple and reliable structure, and the use efficiency of the aero-engine is greatly improved.
  • the lift generated by the rotor at the same power during vertical take-off and landing is the existing other form of vertical take-off and landing aircraft. Several times or even ten times, the vertical take-off and landing can be easily achieved.
  • the rotor When the plane is turned into the plane, the rotor can be retracted into the rotor cabin to make it fly normally at the same speed as a normal airplane. If necessary, the flight speed can reach or exceed. The speed of sound without having to add significantly to the aero engine power.
  • FIG. 1 is a schematic structural view of a first embodiment of the present invention
  • FIG. 2 is a schematic structural view of a second embodiment of the present invention.
  • Figure 3 is a schematic structural view of a third embodiment of the present invention
  • 4 is a schematic structural view of a fourth embodiment of the present invention
  • FIG. 5 is a schematic structural view of a fifth embodiment of the present invention
  • Figure 6 is a schematic view showing the structure of a sixth embodiment of the present invention.
  • the vertical take-off and landing aircraft is composed of a driving compartment 1, a fuselage 16, an aero engine 10, a wing 9, a horizontal tail 7, a vertical tail 6 and a control system, and the upper part of the fuselage 16 is equipped with a rotor 5, a rotor 5
  • the rotor automatic positioning device 4 is mounted thereon, the rotor 5 is connected with the rotor shaft 3, the rotor shaft 3 is connected with the speed reducer 13 and the rotor shaft expansion device 14, and the rotor shaft 3 is equipped with a rotor shaft automatic positioning device 15, and the top of the fuselage 16 is equipped with
  • the aerodynamic engine 10 is connected to the reducer 13 via a transmission shaft 11, a clutch 12, and a steering vector tail pipe 8 at the rear of the aircraft engine 10.
  • the shape design of the aircraft is basically similar to that of a normal aircraft design.
  • At the top of the aircraft there is an openable and rotatable rotor cabin 2.
  • the rotor cabin 2 is opened, and the rotor shaft expansion device 14 connects the rotor shaft 3 with the rotor shaft.
  • the rotor 5 extends out of the rotor cabin 2, and the left and right rotor wing covers of the rotor cabin 2 can be folded and folded to the left and right when opened, and the rotor hatch of the rotor cabin 2 is opened, so that the gathered rotor 5 can be extended or Indented into the rotor cabin 2, when the plane is flying flat, the rotor 5 gathers and retracts into the rotor cabin, and the left and right rotor cabin covers are closed toward the middle to close the rotor cabin 2.
  • the rotor shaft 3 is a retractable spline shaft transmission structure.
  • the aero engine 10 is operated, and the rotor shaft 3 and the rotor 5 connected to the rotor shaft 3 are rotated by the transmission shaft 11, the clutch 12, and the speed reducer 13, and the rotor 5 is coupled to the rotor shaft 3
  • the two ends are symmetrically arranged and connected to each other, and two sets of symmetrically arranged rotor blades are arranged.
  • the corresponding two rotors are equipped with a rotor automatic positioning device 4, and the rotor automatic positioning device 4 is composed of an elastic member and a limiting member.
  • the rotor automatic positioning device 4 is composed of a spring between two rotors corresponding to the rotor 5 and a limiting member positioned at a position parallel to the fuselage when the corresponding two rotors are folded, the limiting component can
  • the positioning block may also be a positioning bayonet.
  • the rotor 5 When the rotor 5 rotates, it generates a rising force, which drives the aircraft to take off and land vertically, and generates a reaction force to the aircraft.
  • the reaction is detected by a snail. Force, and thereby control the balance of the reaction vector tail nozzle 8 in the opposite direction of the reaction force and the reaction force generated by the downward jet, stabilizing the aircraft Ascending and advancing, the counteracting force can also be offset by the steering vector tail pipe 8 to the left or right of the front, depending on the reaction force generated by the rotation direction of the rotor 5, and a controllable closed nozzle is provided through
  • the snail controls the thrust of the auxiliary nozzle to counteract this reaction force.
  • the auxiliary nozzle When the aircraft is flying flat, the auxiliary nozzle is closed.
  • the steering vector tail nozzle 8 only needs to generate thrust downward and backward without having to (left or right) The left and right thrusts are generated.
  • the speed reducer 13 is disconnected from the transmission shaft 11 via the clutch 12, and the steering vector tail nozzle 8 is turned rearward to propel the aircraft to accelerate flight, the speed reducer 13 and the transmission.
  • the rotor shaft automatic positioning device 15 is composed of a positioning member and a locking member, and the rotor shaft automatic positioning device 15 rotates the rotor
  • the shaft 3 is fixed at a position parallel to the rotor cabin 2 after the rotor 5 is closed, and then the rotor cabin 2 is opened, and the rotor shaft expansion device 14 causes the rotor shaft 3 and the rotor 5 to contract into the rotor 2, the rotor cabin 2 is closed, the aircraft enters a normal level flight state, the rotor shaft expansion device 14 is composed of a hydraulic expansion member and its related components, the telescopic and torque transmission is a spline transmission structure, and the rotor 5 and the rotor shaft 3 are horizontally hinged. And vertical hinge The chain connection, the horizontal hinge connection and the helicopter rotor are connected to the rotor shaft in the same
  • the rotor 5 of the vertical take-off and landing aircraft mounted on the upper part of the fuselage 16 is in the form of a coaxial double-rotor, and the rotor shaft 3 is a coaxial reverse-rotating rotor shaft.
  • the reaction force generated by the rotor is due to the use of the coaxial reversing double-rotor. They cancel each other out, so that the aircraft can smoothly take off and land smoothly.
  • the steering vector tail pipe 8 only needs to turn downward and rear to provide auxiliary lift and forward thrust for the aircraft.
  • the speed reducer 13 can be coupled to a plurality of aero engines, the aero engine 10 is coupled to the clutch 12, and the steerable vertical tail 20 is provided with an auxiliary aero engine 17, via the corresponding two transmission shafts 11, clutch 12 and The two aero engines 10 are arranged in parallel, and the clutches 12 are respectively mounted on the two aero engines 10.
  • the vertical working principle of the lifting and lowering is the same as that of FIG. 1, and the reaction force generated by the rotor 5 is detected by the snail and controlled thereby.
  • the auxiliary aeroengine 17 (thrust and direction) on the traversable vertical tail 20 is controlled to balance and generate forward thrust. After the airplane is leveled, the auxiliary aeroengine 17 nozzle mounted on the steerable vertical tail 20 is adjusted. The thrust is then generated to assist the aircraft in advancing, and steering the direction of the auxiliary aeroengine 17 mounted on the steerable vertical tail 20 also assists in steering the aircraft.
  • the front side of the four aeroengines 10 are provided with a propeller 18, and the auxiliary aeroengine 17 is provided with a propeller 18 at the rear, and the working principle of vertical take-off and landing, leveling and the embodiment shown in Fig. 3
  • the rotor 5 is composed of six rotors that are symmetrically placed up and down. If the number of rotor blades is increased, it must be increased in pairs so that the rotors can be staggered when folded.
  • the rotor cabin 2 of the vertical take-off and landing aircraft is respectively provided with two sets of rotors 5 having opposite rotation directions and rotor automatic positioning devices 4 corresponding to the rotors 5, a rotor shaft expansion device 14, a speed reducer 13, a transmission shaft 11, and Clutch 12, aero engine 10, aero engine 10 are divided into two groups, the former group is two parallel aero engines 10, providing the front rotor 5 vertical take-off and landing power and front flying power, followed by a single aero engine 10 installed at the rear of the aircraft, providing the rear rotor 5 vertical take-off and landing power and front flying power, the front and rear rotors 5 due to the opposite direction of rotation, The reaction forces generated by the front and rear rotors 5 cancel each other out, so that the vertical take-off and landing aircraft can smoothly take off and land. Since the rotor 5 is rearward, the vertical tail 6 is installed downward.
  • the rotor 5 of the vertical take-off and landing aircraft mounted on the upper part of the fuselage 16 is in the form of a coaxial double-rotor, and the rotor shaft 3 is a coaxial reversing rotor shaft.
  • the reaction of the rotor is caused by the use of the coaxial reversing double rotor. The forces cancel each other out, allowing the aircraft to smoothly take off and land vertically.
  • the front part of the aero engine 10 is connected to the propeller 18 via the clutch 12 and the transmission shaft 11.
  • the rear part is connected to the reducer 13 via the clutch 12 and the transmission shaft 11.
  • the adjustable rotor support rod 19 is mounted on the top of the fuselage 16 and the adjustable rotor
  • the fixed rod 19 is retracted when the vertical take-off and landing aircraft is vertically taken off and landing, and protrudes at the rear of the fixed rotor 5 when the aircraft is flying flat, so that the rotor 5 does not swing when the aircraft is flying flat.

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

Un avion à décollage et atterrissage à la verticale comprend une cabine de pilotage (1), un fuselage (16), un moteur d’aéronef (10), une aile (9), une queue horizontale (7), une queue verticale (6), un réducteur (13) et un système de commande. Le moteur d’aéronef (10) est relié au réducteur (13) par l’intermédiaire d’un arbre d’entraînement (11) et d’un embrayage (12). Une tubulure de propulsion de queue de vecteur d’orientation (8) est assemblée sur la partie arrière du moteur d’aéronef (10). Une pale de rotor (5) est assemblée sur le dessus du fuselage (6), et ladite pale de rotor (5) est reliée à un arbre de pale de rotor (3). L’avion à décollage et atterrissage à la verticale comporte un dispositif de rétraction (14) de l’arbre de pale de rotor (3) et un habitacle de pale de rotor ouvert/fermé (2) qui peut contenir la pale de rotor ferlée (5). Ledit habitacle de pale de rotor ouvert-fermé (2) se situe sur le dessus du fuselage (6). L’arbre de pale de rotor (3) est relié au réducteur (13) et au dispositif de rétraction (14) de l’arbre de pale de rotor (3). Un dispositif de positionnement automatique (4) est assemblé sur la pale de rotor (5), et un dispositif de positionnement automatique (4) de l’arbre de pale de rotor (3) est assemblé sur l’arbre de pale de rotor (3).
PCT/CN2008/002094 2008-06-12 2008-12-26 Avion à décollage et atterrissage à la verticale WO2009149592A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CN200810058521.7 2008-06-12
CNA2008100585217A CN101602403A (zh) 2008-06-12 2008-06-12 垂直起降飞机

Publications (1)

Publication Number Publication Date
WO2009149592A1 true WO2009149592A1 (fr) 2009-12-17

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PCT/CN2008/002094 WO2009149592A1 (fr) 2008-06-12 2008-12-26 Avion à décollage et atterrissage à la verticale

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Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3303123A4 (fr) * 2015-05-28 2019-01-23 Vetter, Eugene, H. Dispositifs et procédés pour des structures d'aéronef hybrides adav à transition en vol/à voilure fixe et modes de vol
CN110775264A (zh) * 2019-10-28 2020-02-11 上海交通大学 水空两栖无人航行器及其控制方法
EP3617067A1 (fr) * 2018-08-27 2020-03-04 Bell Helicopter Textron Inc. Configuration de propulsion de giravion à grande vitesse
WO2023242448A1 (fr) 2022-06-17 2023-12-21 Podadera Dominguez Francisco Module support pour aéronefs de décollage et d'atterrissage verticaux et aéronef comprenant ce module

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104290906B (zh) * 2014-11-04 2016-05-25 中国人民解放军国防科学技术大学 一种垂直起降飞行器
CN205113706U (zh) * 2015-08-12 2016-03-30 刘十一 一种带可自动收放多旋翼的垂直起降固定翼飞机
CN105173060B (zh) * 2015-11-02 2017-03-29 佛山市神风航空科技有限公司 一种双桨垂直升降飞机
CN108502167A (zh) * 2017-02-24 2018-09-07 罗傲 一种具有旋翼的固定翼旋桨飞机
CN106904266A (zh) * 2017-03-21 2017-06-30 张宏 一种新型固定翼飞机
CN107745808A (zh) * 2017-11-15 2018-03-02 孙林青 一种复合直升机
CN109552618A (zh) * 2018-12-01 2019-04-02 江苏鸿鹄无人机应用科技有限公司 一种无人机用备用飞行装置
CN114194388A (zh) * 2021-11-23 2022-03-18 上海羽天航空科技有限公司 一种新型垂直起降固定翼飞机

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2953319A (en) * 1955-01-05 1960-09-20 United Aircraft Corp Convertiplane
US3370809A (en) * 1965-06-29 1968-02-27 United Aircraft Corp Convertiplane
CN1281409A (zh) * 1997-12-10 2001-01-24 佛朗哥·卡潘纳 将水平起飞和自持水平飞行的飞机转变成自持水平飞行垂直起落的混合式飞机的系统
US6622962B1 (en) * 2002-04-29 2003-09-23 Bruce D. White Fixed wing aircraft having powered rotor VTOL capability with rotor blades stowable during horizontal flight
DE10241732A1 (de) * 2002-09-06 2004-03-25 Hinüber, Edgar v. Senkrecht und horizontal start-, flug- und landefähiges Kombinationsflugzeug

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2953319A (en) * 1955-01-05 1960-09-20 United Aircraft Corp Convertiplane
US3370809A (en) * 1965-06-29 1968-02-27 United Aircraft Corp Convertiplane
CN1281409A (zh) * 1997-12-10 2001-01-24 佛朗哥·卡潘纳 将水平起飞和自持水平飞行的飞机转变成自持水平飞行垂直起落的混合式飞机的系统
US6622962B1 (en) * 2002-04-29 2003-09-23 Bruce D. White Fixed wing aircraft having powered rotor VTOL capability with rotor blades stowable during horizontal flight
DE10241732A1 (de) * 2002-09-06 2004-03-25 Hinüber, Edgar v. Senkrecht und horizontal start-, flug- und landefähiges Kombinationsflugzeug

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3303123A4 (fr) * 2015-05-28 2019-01-23 Vetter, Eugene, H. Dispositifs et procédés pour des structures d'aéronef hybrides adav à transition en vol/à voilure fixe et modes de vol
EP3617067A1 (fr) * 2018-08-27 2020-03-04 Bell Helicopter Textron Inc. Configuration de propulsion de giravion à grande vitesse
US11167845B2 (en) 2018-08-27 2021-11-09 Textron Innovations Inc. High speed rotorcraft propulsion configuration
US11577831B2 (en) 2018-08-27 2023-02-14 Textron Innovations Inc. High speed rotorcraft propulsion configuration
CN110775264A (zh) * 2019-10-28 2020-02-11 上海交通大学 水空两栖无人航行器及其控制方法
CN110775264B (zh) * 2019-10-28 2022-10-18 上海交通大学 水空两栖无人航行器及其控制方法
WO2023242448A1 (fr) 2022-06-17 2023-12-21 Podadera Dominguez Francisco Module support pour aéronefs de décollage et d'atterrissage verticaux et aéronef comprenant ce module

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