WO2017180020A1 - Aéronef - Google Patents

Aéronef Download PDF

Info

Publication number
WO2017180020A1
WO2017180020A1 PCT/RU2016/000860 RU2016000860W WO2017180020A1 WO 2017180020 A1 WO2017180020 A1 WO 2017180020A1 RU 2016000860 W RU2016000860 W RU 2016000860W WO 2017180020 A1 WO2017180020 A1 WO 2017180020A1
Authority
WO
WIPO (PCT)
Prior art keywords
aircraft
fan wheel
jet engine
mode
blade
Prior art date
Legal status (The legal status 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 status listed.)
Ceased
Application number
PCT/RU2016/000860
Other languages
English (en)
Russian (ru)
Inventor
Светослав Владимирович ЗАНЕГИН
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Individual
Original Assignee
Individual
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 Individual filed Critical Individual
Publication of WO2017180020A1 publication Critical patent/WO2017180020A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

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
    • 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C39/00—Aircraft not otherwise provided for
    • B64C39/06—Aircraft not otherwise provided for having disc- or ring-shaped wings

Definitions

  • the present invention relates to the field of aircraft (LA) and can serve as an alternative to a helicopter fleet.
  • Aircraft are known, disclosed, for example, in patents RU 2495795, published April 10, 2005 and RU 2348567, published March 10, 2009, the hull of which is made in the form of bodies of revolution. Moreover, the cockpit, control systems, landing systems are located inside the hull.
  • the aim of the present invention is to provide an aircraft in which a sparing mode of operation of the blades of the fan wheel (VK) is provided, unlike the blades of a helicopter, since a swash plate is not used and a larger number of blades of the fan wheel (VK) reduce the voltage in the blades.
  • the technical result consists in increasing the reliability of the operation of the aircraft, as well as its safety and maneuverability.
  • the aircraft contains a housing made in the form of a disk-shaped body of revolution, in which, as the propulsors connected to the housing, an annular fan wheel that creates the main lifting force and an air-jet engine (WFD) of opposite rotation are used, moreover the annular fan wheel (VK) has controllable blade vanes, while the aircraft also contains a first blade apparatus directing air flow to the blade vanes of the VK and a second vane apparatus, which ensures the rectification of the air flow discharged by the VC, and the lenticular housing has the ability to accommodate the cockpit, control system, landing system and fan wheel drive, the jet engine is configured to provide two functions, including generating electricity for the fan drive wheels, control systems and electricity consumers installed on board the aircraft apparatus, and is also configured to provide additional lifting thrust at the start mode or hovering mode using a rotary nozzle with the provision of further marching thrust.
  • WFD air-jet engine
  • the principle of equality of the momentum of the moment of force of the fan wheel and the jet engine is used, controlled by the on-board computer with a coaxial arrangement of propulsion devices (for example, as in a helicopter). Flight control is additionally carried out by pitch and roll control windows, by passing air from the dorsal region to the dorsal region.
  • the fan wheel is driven by three drives, each mounted on a three-pointed star-shaped power beam in the body of the aircraft.
  • drives their installation is carried out either on the power ring or, for example, 4 drives - on the X-shaped beam.
  • Figure 1 shows a General view of the aircraft.
  • the proposed aircraft has the appearance of a "flying saucer.”
  • the apparatus has a circular disk-shaped body, in which an annular fan wheel 2 with controlled vanes-blades located between the inner and outer rims of the VK, creating the main lifting force, and an opposite-rotation air-jet engine (WFD) are used as a propeller 4 - coaxial circuit, a guide vane apparatus 1, which improves the parameters of the air flow entering the VK, a second straightening vane apparatus 3, which organizes the air flow after the VC, a round cranial fuselage (in figure It is presented as flat), in which there is a pilot cabin 7 (2 pilots are shown in the figure), control systems, landing systems 8 (telescopic racks), fan wheel drive (PVC) 6.
  • WFD opposite-rotation air-jet engine
  • WFD 4 has two functions: generating electricity for PVC and for control systems, as well as other consumers of electricity, and the creation of additional lifting thrust at the starting or hovering mode and with the help of a rotary nozzle, which creates a thrust of marching mode. To ensure exchange rate stability, the principle of equality is used.
  • Impulse moment of force VK and WFD controlled by the on-board computer. Controlled mismatch of rotation allows you to choose the course of flight.
  • Other flight control functions are provided by the pitch and roll control windows 6 by air bypass from the dorsal region to the dorsal region or by other special control methods.
  • the proposed flight of the aircraft is as follows: 1) the aircraft is initially located on the ground with the help of retractable landing gears 8, 2) the WFD 4 is launched with a rotary nozzle 5, with the thrust vector set vertically, 3) upon receipt of the necessary electric power of the PVC, which can be both gear and hydraulic type (in the figure their number is 3 pcs.) they spin the fan wheel 2, while the WFD 4 and VK 2 rotations, carried out in opposite directions, are controlled by the control system, ensuring equal TVO torques.
  • the air flow passing through the guide vanes 1 is sucked in by a fan wheel 2 with installed adjustable vanes, similar to shortened rotor blades of the helicopter (the number of vanes is determined experimentally) in the “lift” mode and passing through the air vanes of the second vanes 3, creates aircraft lift together with the WFD 4, 4) when climbing, landing gear 8 is removed and a negative aircraft pitch is set to start the marching movement, 5) to select of the required marching mode, the nozzle is rotated 5 to 90 ° to the axis of the aircraft; 6) aircraft maneuvering is carried out: along the course - by mismatching the torque of the WFD, by pitch - by opening-closing the front control windows 9 and by turning the nozzle 5, by roll - by opening-closing left or right pair of windows 9 of the aircraft.
  • the rotation of the fan wheel occurs around the cockpit structure, i.e. the cockpit is located in the central part of the aircraft.
  • the use of this invention provides a more sparing mode of operation of VK blades, in contrast to helicopter blades, since a swash plate is not used and a larger number of VK blades reduce stress in the blades.
  • the blades are located inside the rim of the fan wheel and the hull of the aircraft and cannot be destroyed when the aircraft comes into contact with trees, houses, power lines, etc.
  • it is easier to organize the evacuation of the flight crew (there are no chopping blades of the helicopter ) and the device itself is capable of parachuting, providing a non-rigid landing, while the controlled blades VK 2 can be installed in a transverse air flow position.
  • the device of the proposed device allows you to install standard rescue parachutes.
  • the streamlined shape of the "flying saucer" and the rotary nozzle make it possible to obtain speeds more substantial than those of helicopters.

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Toys (AREA)

Abstract

L'invention concerne un aéronef comprenant un corps se présentant comme un corps de rotation en forme de disque dans lequel on utilise en qualité de propulseur une roue de soufflante annulaire créant une force de sustentation principale, et un moteur à réaction à air ayant un sens de rotation inverse. La roue de soufflante annulaire comprend des aubes-pales commandées, et l'aéronef comprend également un premier appareil à aubes guidant le flux d'air, et un second appareil à aubes assurant le redressement du flux d'air rejeté par la roue annulaire; le corps peut recevoir une cabine de pilotage,un système de commande, des systèmes d'atterrissage et d'actionnement de la roue de soufflante; le moteur à réaction à air peut assurer deux fonctions comprenant la génération d'énergie électrique lors de l'actionnement de la roue de soufflante, des systèmes de commande et de consommateur d'électricité disposés à bord de l'aéronef, et peut également fournir une poussée de sustentation supplémentaire en mode de démarrage ou en mode de sur-place à l'aide de la poussée d'une buse rotative du mode de marche. Le résultat technique consiste en une meilleure sécurité, une meilleure manœuvrabilité et une,meilleure fiabilité lors de l'exploitation de l'aéronef. FIG. 1: A-O-A
PCT/RU2016/000860 2016-04-11 2016-12-09 Aéronef Ceased WO2017180020A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
RU2016113740A RU2617014C1 (ru) 2016-04-11 2016-04-11 Летательный аппарат
RU2016113740 2016-04-11

Publications (1)

Publication Number Publication Date
WO2017180020A1 true WO2017180020A1 (fr) 2017-10-19

Family

ID=58642882

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/RU2016/000860 Ceased WO2017180020A1 (fr) 2016-04-11 2016-12-09 Aéronef

Country Status (2)

Country Link
RU (1) RU2617014C1 (fr)
WO (1) WO2017180020A1 (fr)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10464668B2 (en) 2015-09-02 2019-11-05 Jetoptera, Inc. Configuration for vertical take-off and landing system for aerial vehicles
CN110588974A (zh) * 2019-09-30 2019-12-20 合肥中科重明科技有限公司 一种基于地面旋转储能的高效推进装置
CN111377059A (zh) * 2020-05-19 2020-07-07 重庆宇矛航空科技有限公司 高提升力无翼飞行器动力系统
US10875658B2 (en) 2015-09-02 2020-12-29 Jetoptera, Inc. Ejector and airfoil configurations
US11001378B2 (en) 2016-08-08 2021-05-11 Jetoptera, Inc. Configuration for vertical take-off and landing system for aerial vehicles
US11148801B2 (en) 2017-06-27 2021-10-19 Jetoptera, Inc. Configuration for vertical take-off and landing system for aerial vehicles

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2668541C1 (ru) * 2017-10-12 2018-10-01 Светослав Владимирович Занегин Летательный аппарат
RU2708775C1 (ru) * 2018-12-17 2019-12-11 Николай Борисович Болотин Вертолет
RU2714090C1 (ru) * 2018-12-17 2020-02-11 Николай Борисович Болотин Винтокрылый летательный аппарат
RU2759060C1 (ru) * 2020-12-18 2021-11-09 Сергей Федорович Таранов Транспортное устройство многоразового использования

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6575401B1 (en) * 2001-08-07 2003-06-10 Howard J. Carver Vertical-lift and horizontal flight aircraft
US20070215748A1 (en) * 2006-03-20 2007-09-20 Robbins Brent A VTOL UA V with lift fans in joined wings
RU2365522C1 (ru) * 2008-01-21 2009-08-27 Кравченко Виктор Александрович Летающая тарелка
RU2530906C1 (ru) * 2013-10-18 2014-10-20 Общество с ограниченной ответственностью "ФАН ФЛАЙТ" Беспилотный летательный аппарат

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6575401B1 (en) * 2001-08-07 2003-06-10 Howard J. Carver Vertical-lift and horizontal flight aircraft
US20070215748A1 (en) * 2006-03-20 2007-09-20 Robbins Brent A VTOL UA V with lift fans in joined wings
RU2365522C1 (ru) * 2008-01-21 2009-08-27 Кравченко Виктор Александрович Летающая тарелка
RU2530906C1 (ru) * 2013-10-18 2014-10-20 Общество с ограниченной ответственностью "ФАН ФЛАЙТ" Беспилотный летательный аппарат

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10464668B2 (en) 2015-09-02 2019-11-05 Jetoptera, Inc. Configuration for vertical take-off and landing system for aerial vehicles
US10875658B2 (en) 2015-09-02 2020-12-29 Jetoptera, Inc. Ejector and airfoil configurations
US11001378B2 (en) 2016-08-08 2021-05-11 Jetoptera, Inc. Configuration for vertical take-off and landing system for aerial vehicles
US11148801B2 (en) 2017-06-27 2021-10-19 Jetoptera, Inc. Configuration for vertical take-off and landing system for aerial vehicles
CN110588974A (zh) * 2019-09-30 2019-12-20 合肥中科重明科技有限公司 一种基于地面旋转储能的高效推进装置
CN110588974B (zh) * 2019-09-30 2021-04-27 中国科学院力学研究所 一种基于地面旋转储能的高效推进装置
CN111377059A (zh) * 2020-05-19 2020-07-07 重庆宇矛航空科技有限公司 高提升力无翼飞行器动力系统

Also Published As

Publication number Publication date
RU2617014C1 (ru) 2017-04-19

Similar Documents

Publication Publication Date Title
RU2617014C1 (ru) Летательный аппарат
EP3486168B1 (fr) Aéronef à rotors basculants à portée étenduek
EP3386856B1 (fr) Aéronef sans pilote doté d'assemblages de plaques d'aile qui assurent une capacité à décollage et d'atterrissage verticaux efficaces
JP6825050B2 (ja) 航空機
CN109305357B (zh) 具有四边形连杆机构的双倾转翼飞行器
EP3140190B1 (fr) Aéronef à décollage et atterrissage verticaux
US8733690B2 (en) Lightweight vertical take-off and landing aircraft and flight control paradigm using thrust differentials
US10029785B2 (en) Aircraft capable of vertical takeoff
EP3140188B1 (fr) Véhicule aérien sans pilote (uav) de type à décollage et atterrissage verticaux (adav)
RU2670356C2 (ru) Выполненный с возможностью вертикального взлета летательный аппарат
CN101965217B (zh) 特技旋转翼玩具直升机
CN110683044A (zh) 飞行器
KR20090057504A (ko) 가변형 회전익을 이용한 수직이착륙기
US20090039206A1 (en) Bird vortex flying machine
US20180072408A9 (en) Torque balanced, lift rotor module providing increased lift with few or no moving parts
US9840323B1 (en) Drone aircraft
WO2019172804A1 (fr) Avion convertible
US20190016453A1 (en) Vertical take-off and landing (vtol) aircraft and a propulsion system for a vehicle vertical take-off and landing (vtol)
WO2017036080A1 (fr) Autogire équipé d'un parachute et procédé de fabrication
KR20070001117U (fr) Décollage et atterrissage d'aéronef utilisant une voilure tournante variable
CN204956905U (zh) 伞降自转旋翼机
WO2005037644A1 (fr) Aeronef vtol
RU2668541C1 (ru) Летательный аппарат
CN105438464A (zh) 一种飞行器及其控制方法
KR20240124062A (ko) 가변익 드론

Legal Events

Date Code Title Description
NENP Non-entry into the national phase

Ref country code: DE

121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 16898778

Country of ref document: EP

Kind code of ref document: A1

122 Ep: pct application non-entry in european phase

Ref document number: 16898778

Country of ref document: EP

Kind code of ref document: A1