WO2015116015A1 - Aéronef à soufflante - Google Patents

Aéronef à soufflante Download PDF

Info

Publication number
WO2015116015A1
WO2015116015A1 PCT/UA2014/000017 UA2014000017W WO2015116015A1 WO 2015116015 A1 WO2015116015 A1 WO 2015116015A1 UA 2014000017 W UA2014000017 W UA 2014000017W WO 2015116015 A1 WO2015116015 A1 WO 2015116015A1
Authority
WO
WIPO (PCT)
Prior art keywords
deflectors
rotor
air
aircraft
blades
Prior art date
Application number
PCT/UA2014/000017
Other languages
English (en)
Russian (ru)
Inventor
Анатолий Викторович КОНДРАТЮК
Original Assignee
Анатолий Викторович КОНДРАТЮК
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 Анатолий Викторович КОНДРАТЮК filed Critical Анатолий Викторович КОНДРАТЮК
Priority to PCT/UA2014/000017 priority Critical patent/WO2015116015A1/fr
Publication of WO2015116015A1 publication Critical patent/WO2015116015A1/fr

Links

Classifications

    • 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
    • B64D17/00—Parachutes
    • B64D17/02—Canopy arrangement or construction
    • B64D17/18—Vent arrangement or construction
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C39/00—Aircraft not otherwise provided for
    • B64C39/02—Aircraft not otherwise provided for characterised by special use
    • B64C39/026—Aircraft not otherwise provided for characterised by special use for use as personal propulsion unit
    • 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
    • B64D17/00—Parachutes
    • B64D17/02—Canopy arrangement or construction
    • B64D17/12—Canopy arrangement or construction constructed to provide variable or non-uniform porosity over area of canopy

Definitions

  • the invention relates to aircraft with vertical take-off and landing (VTOL).
  • VTOL vertical take-off and landing
  • the aim of the invention is the creation of a portable aircraft with vertical take-off and landing and the ability to hang motionless in the air, which,
  • SUBSTITUTE SHEET (RULE 26) in the event of engine failure or rotor failure, it would provide a reduction at a safe speed.
  • the only rigid part of the proposed apparatus is the central unit 1, containing the engine, transmission, fuel, control devices, as well as the disk 2 located in the upper part of the indicated unit, by means of which the torque is transmitted from the engine and transmission to the rotor, made, for example, as shown in FIG. 2.
  • the rotor blades are made according to the design that has been repeatedly proposed for the inflatable wings of aircraft, namely: a set of cylindrical or conical inflatable elements 3 which have different diameters, thus forming
  • a rod 7 is attached, which, passing through a hole in the disk 2 to a mechanism similar to the blade swash plate used on helicopters, and located between the disk 2 and the central unit 1, allows you to change the angle of attack of each blade.
  • the central unit is in the center of ring 8,
  • deflectors 10 are attached to it,
  • thrusts 1 1 are attached to the deflectors, deflecting the deflectors from a position strictly along the air flow. Air flow
  • the circle on which the deflectors are located is divided into sectors with independent traction systems.
  • the ends of the rods of each sector are connected together, and through a common control rod 12 are connected to the ring 8.
  • SUBSTITUTE SHEET (RULE 26) deflectors occupy only the outer part of the grid. In the central part of the grid 9 instead of deflectors
  • valves 13 are located, which are arranged similarly to deflectors, except that the lower sides of the tapes are left free, which allows the tapes to be located along the air flow, providing
  • a pilot or other payload is suspended from the bottom of the unit on slings.
  • the main load falls on the central slings 14 connected directly to the central block 1. This can significantly reduce the load on the ring 8.
  • Side slings 15 in this mode are needed only to stabilize the pilot's position.
  • the horizontal acceleration of the apparatus is carried out similarly to helicopters, by cyclically changing the angle of attack of the rotor blades. In this case, only the central unit with the rotor is rotated. The appearance of the horizontal component of the lift vector causes horizontal acceleration. Uneven blades blowing during horizontal flight
  • the apparatus In the event of engine failure or destruction of the rotor, the apparatus begins to fall and the air flow through the grid 9 reverses direction. Under the influence of the reverse flow, the deflectors 10 add up as
  • valves 13 are rotated by a reverse air flow in an arbitrary direction and, while occupying a horizontal position, are also pressed against the grid 9 to form an airtight surface.
  • the entire surface of the net acts like a canopy of a parachute, reducing the rate of descent to
  • the lower part of the central unit 1 can be covered with an air bag.
  • FIG. 1 general view and position of the deflectors in normal flight mode.
  • FIG. 2 propeller based on inflatable elements.
  • FIG. 3 bottom view, the location of the control rods
  • FIG. 4 general view and position of the deflectors in emergency reduction mode.

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Transmission Devices (AREA)

Abstract

L'invention concerne un aéronef à décollage et atterrissage vertical pour une utilisation individuelle, dans lequel la force de sustentation est créée par une hélice dont le moment rotatif résultant de sa rotation est compensé par des déflecteurs qui dévient le flux d'air de l'hélice. En outre, en cas de panne du moteur ou de casse de l'hélice porteuse, les déflecteurs empêche le passage de l'air dans la direction inverse de sorte que, en cas de descente d'urgence, on crée une résistance aérodynamique importante qui réduit la vitesse de descente jusqu'à une altitude de sécurité, l'appareil se comportant ainsi comme n parachute. L'utilisation dans la structure comportant une hélice d'éléments soufflants permet de stocker et de transporter l'aéronef à l'état replié.
PCT/UA2014/000017 2014-02-03 2014-02-03 Aéronef à soufflante WO2015116015A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PCT/UA2014/000017 WO2015116015A1 (fr) 2014-02-03 2014-02-03 Aéronef à soufflante

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/UA2014/000017 WO2015116015A1 (fr) 2014-02-03 2014-02-03 Aéronef à soufflante

Publications (1)

Publication Number Publication Date
WO2015116015A1 true WO2015116015A1 (fr) 2015-08-06

Family

ID=53757435

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/UA2014/000017 WO2015116015A1 (fr) 2014-02-03 2014-02-03 Aéronef à soufflante

Country Status (1)

Country Link
WO (1) WO2015116015A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106081107A (zh) * 2016-06-24 2016-11-09 阮惠春 未来飞机的设计
WO2019033691A1 (fr) * 2017-08-15 2019-02-21 罗琮贵 Procédé de vol à grande vitesse et aéronef à voilure annulaire

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU4732U1 (ru) * 1996-06-07 1997-08-16 Анатолий Аркадьевич Татаринов Несущая аэродинамическая поверхность
RU2299156C1 (ru) * 2005-09-28 2007-05-20 Юрий Алексеевич Аксенов Механизм, создающий подъемную силу летательного аппарата
US20110163198A1 (en) * 2010-01-04 2011-07-07 Glenn Leaver Safety flier--a parachute-glider air-vehicle with vertical take-off and landing capability

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU4732U1 (ru) * 1996-06-07 1997-08-16 Анатолий Аркадьевич Татаринов Несущая аэродинамическая поверхность
RU2299156C1 (ru) * 2005-09-28 2007-05-20 Юрий Алексеевич Аксенов Механизм, создающий подъемную силу летательного аппарата
US20110163198A1 (en) * 2010-01-04 2011-07-07 Glenn Leaver Safety flier--a parachute-glider air-vehicle with vertical take-off and landing capability

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
IZAKSON A.M.: "Sovetskoe vertoletostroenie. M.", MASHINOSTROENIE, 1964, pages 66 *

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106081107A (zh) * 2016-06-24 2016-11-09 阮惠春 未来飞机的设计
WO2019033691A1 (fr) * 2017-08-15 2019-02-21 罗琮贵 Procédé de vol à grande vitesse et aéronef à voilure annulaire
US11472547B2 (en) 2017-08-15 2022-10-18 Luo Conggui High-speed flight method and coleopter

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