WO2009025632A1 - Aéronef à atterrissage et décollage vertical - Google Patents

Aéronef à atterrissage et décollage vertical Download PDF

Info

Publication number
WO2009025632A1
WO2009025632A1 PCT/UA2008/000046 UA2008000046W WO2009025632A1 WO 2009025632 A1 WO2009025632 A1 WO 2009025632A1 UA 2008000046 W UA2008000046 W UA 2008000046W WO 2009025632 A1 WO2009025632 A1 WO 2009025632A1
Authority
WO
WIPO (PCT)
Prior art keywords
wing
fuselage
aircraft
power plant
takeoff
Prior art date
Application number
PCT/UA2008/000046
Other languages
English (en)
Russian (ru)
Inventor
Oleg Leonidovych Tytarenko
Original Assignee
Oleg Leonidovych Tytarenko
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 Oleg Leonidovych Tytarenko filed Critical Oleg Leonidovych Tytarenko
Publication of WO2009025632A1 publication Critical patent/WO2009025632A1/fr

Links

Classifications

    • 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
    • B64C39/062—Aircraft not otherwise provided for having disc- or ring-shaped wings having annular wings
    • B64C39/064—Aircraft not otherwise provided for having disc- or ring-shaped wings having annular wings with radial airflow

Definitions

  • the invention relates to aircraft, in particular to aircraft such as a flying saucer with vertical take-off and landing, and can be used to transport passengers and goods.
  • a vertical take-off and landing aircraft comprising a main and additional ring wings located below it, a cockpit, a fan located in the center of the wing, and an engine (A. S. USSR Jfe 1446836, IPC 7 B64C 39/06, op. 10/27/2004).
  • the closest analogue of the claimed device selected as a prototype, is an aircraft of vertical take-off and landing, containing a convex profile wing bent into the contour, inside of which is fixed with a gap fuselage. Fan blades are inserted into the gap, turning with the help of an engine (Application of Germany Xo 4037472, IPC 6 B64C 29/02, 39/06, op. 16.01.92).
  • Common essential features of the known and claimed devices are the wing bent into the contour, inside of which the fuselage is installed with a gap, and the power plant.
  • the fan pumps air through the gap under the convex wing, forming a zone of high pressure, i.e. the so-called an air cushion, which, however, is not able to lift the unit to a great height.
  • an air cushion i.e. the so-called an air cushion
  • the basis of the invention is the task of improving the aircraft of vertical take-off and landing, in which by changing the wing profile and directivity of the air flow pumped by the power plant, the efficient use of air flow is ensured, due to which the technical result is achieved: increasing the efficiency of the power plant, improving aerodynamic and operational characteristics of the aircraft.
  • the problem is solved in that in an aircraft of vertical take-off and landing, comprising a wing bent into the contour, inside of which the fuselage is mounted with a gap, and a power plant, in accordance with the invention, the wing has an airplane wing profile, and the power plant is installed so that it pumps the air flow is predominantly in the plane of the wing in the direction mainly from the center of the fuselage to the wing.
  • the louvers of the intake manifold are located on the outer edge of the wing through the wing connected to the power unit, and on the upper surface of the fuselage are the louvers of the intake manifold through the fuselage connected to the power unit.
  • An engine nozzle or propulsion engine nozzles are flattened at the edge. At the bottom of the wing mounted with the ability to open the wing flaps.
  • the gap between the wing contour and the fuselage is configured to vary. Between the totality of the essential features of the claimed invention and the achieved technical result there is the following causal relationship.
  • the presence on the outer edge of the wing of the louvre of the intake manifold, through the wing connected to the power plant, allows the use of a swirling air flow generated above the outer edge of the wing, which is directed along the intake manifold to the turbine of the power plant to enhance air flow, to increase the vacuum above the wing and increase the lift strength.
  • the presence on the upper surface of the fuselage of the louvers of the suction manifold, through the fuselage connected to the power unit provides an increase in vacuum over the fuselage and an increase in lift. Performing a flattened nozzle at the edge of the engine nozzle or nozzles of the propulsion engine forcing air flow contributes to a more complete airflow of the wing area.
  • a wing liner in the lower part of the wing with the possibility of opening helps to facilitate and more efficient take-off and a softer landing by increasing the air pressure under the aircraft while lowering the wing liner down.
  • the gap between the wing contour and the fuselage with the ability to change allows you to adjust the lifting force depending on changes in engine power.
  • the need to turn off the engine, its failure, lack of fuel, reducing the gap to zero allows you to use the effect of a parachute, due to a sharp increase in air pressure under the device, which provides a softer landing without impacts.
  • the invention and in specific forms of execution contributes to the achievement of the specified technical result.
  • FIG. 1 shows a top view of an aircraft
  • FIG. 2 - section A - A in FIG. one in FIG. 3
  • FIG. 4 is a photograph of a general view of an experimental sample of an aircraft.
  • the aircraft of vertical take-off and landing (Fig. 1) contains a wing 1 bent into the contour with an airplane wing profile, inside of which is fixed with a gap, the size of which can vary, the fuselage 2 with the cockpit and control system, and a power plant, which is installed mainly in the bottom of the fuselage 2 and may have one or more engines 3, depending on the type and purpose of the aircraft. It can be piston, turboprop, turbofan, turbojet engines, etc. It is optimal to use three star-shaped engines 3, nozzles 4 of which pump air flow in the plane of the wing 1 in the direction from the center of the fuselage 2 to the wing 1, to its inner edge (Fig. 2).
  • the wing circuit 1 may be closed in the case of a subsonic aircraft or open in the case of a supersonic aircraft.
  • a suction manifold 5 with shutters 6 on the outer edge of the wing 1 may be connected, connected to the power unit.
  • the power unit In the upper part of the fuselage 2 can also be located blinds 7 of the intake manifold 8, also connected to the power plant (Fig. 3).
  • the nozzles 4 of the engines 3 along the edge can be made flattened.
  • fenders 9 Fig. 3).
  • ailerons 10 rudders of turns mounted on the wing 1 on the sides and a tail nozzle 11 moving down and to the right (Fig. 1).
  • ailerons 10 rudders of turns mounted on the wing 1 on the sides and a tail nozzle 11 moving down and to the right (Fig. 1).
  • the side parts of the wing 1 can be made movable relative to the fuselage 2.
  • gateway shaft 12 (Fig. 3) for installing, for example, docking units above and below. This will allow in space to assemble aircraft in sections, forming an orbital station.
  • BEST MODE FOR CARRYING OUT THE INVENTION Engines 3 through nozzles 4 inject air flow in the wing plane 1 from the center of the fuselage 2 to the inner edge of the wing 1 around the entire circumference of the wing contour.
  • the inner edge of the wing 1 divides the air flow into two flows - the upper and lower ones, which flow through the gap between the wing 1 and the fuselage 2 around the upper and lower surfaces of the wing 1. Due to the fact that the wing 1 has the profile of an airplane wing, an increased pressure zone appears under the wing 1, and above the wing 1 - a rarefaction zone, as a result of which an upward lifting force is formed, and the aircraft gains altitude.
  • the nozzle 4 tapered along the edge provides a more complete airflow of the area of the wing 1 along the inner perimeter of its contour.
  • an intake manifold 5 Given the presence of an intake manifold 5, the swirling air flow generated above the upper surface of the wing 1 from the outside through the louvers 6 is sucked into the manifold 5 and through the wing 1 again enters the turbine of the engine 3, which eliminates the stall and increases the negative pressure above the wing 1, and accordingly, lift.
  • the air flow from the top of the fuselage 2 enters the power plant, increasing the vacuum above the upper surface of the fuselage 2 and wing 1 and providing the engines with clean air for the smooth operation of the aircraft.

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Wind Motors (AREA)
  • Jet Pumps And Other Pumps (AREA)
  • Toys (AREA)

Abstract

L'invention concerne un aéronef à atterrissage et décollage vertical et qui est destiné au transport de passagers et de fret et permet d'améliorer le rendement du groupe propulseur et d'améliorer les qualités aérodynamiques et d'usage. L'appareil comprend une aile (1) présentant un contour possédant le profil d'une aile d'avion à l'intérieur de laquelle on a monté un fuselage (2) avec un intervalle variable et un groupe propulseur monté de manière à amener un flux d'air au niveau du plan de l'aile (1) dans une direction allant du centre du fuselage (2) vers l'aile (1). Sur le bord supérieur de l'aile (1) et à la surface supérieure du fuselage (2) on a prévu des jalousies (6, 7) du collecteur d'aspiration (5, 8). Les buses (4) des moteurs (3) du groupe propulseur sont comprimées sur les bords, et des volets auxiliaires (9) sont montés du côté inférieur de l'aile (1) de manière à pouvoir s'ouvrir.
PCT/UA2008/000046 2007-07-30 2008-07-29 Aéronef à atterrissage et décollage vertical WO2009025632A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
UAU200708756 2007-07-30
UAU200708756U UA28455U (en) 2007-07-30 2007-07-30 Vertical take-off and landing flight vehicle

Publications (1)

Publication Number Publication Date
WO2009025632A1 true WO2009025632A1 (fr) 2009-02-26

Family

ID=39228935

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/UA2008/000046 WO2009025632A1 (fr) 2007-07-30 2008-07-29 Aéronef à atterrissage et décollage vertical

Country Status (2)

Country Link
UA (1) UA28455U (fr)
WO (1) WO2009025632A1 (fr)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102319989A (zh) * 2011-09-06 2012-01-18 上海交通大学 一种飞机水平尾翼梁缘条的制造方法
CN103419935A (zh) * 2013-07-24 2013-12-04 南京航空航天大学 基于新型增升装置的碟形布局垂直起降飞行器
CN103419923A (zh) * 2013-07-24 2013-12-04 南京航空航天大学 高速附壁流动的推力增益装置
CN105015780A (zh) * 2014-04-29 2015-11-04 沈增 飞碟的制造方法
CN116654256A (zh) * 2023-07-18 2023-08-29 北京舯迦科技有限公司 一种吹气升力环及其应用方法

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105667793A (zh) * 2016-03-31 2016-06-15 池金良 一种圆周翼反重力装置及悬浮装置
RU2670361C1 (ru) * 2017-06-06 2018-10-22 Борис Никифорович Сушенцев Самолет с укороченным либо вертикальным взлетом и посадкой с винтомоторными, либо турбовинтовыми, либо турбовинтовентиляторными двигателями (варианты)

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4037472A1 (de) * 1990-11-24 1992-01-16 Roland Piek Luftkissenflugscheibe
US5170963A (en) * 1991-09-24 1992-12-15 August H. Beck Foundation Company VTOL aircraft
RU2151717C1 (ru) * 1998-03-02 2000-06-27 Безруков Юрий Иванович Летающая тарелка
US6572053B2 (en) * 2000-09-19 2003-06-03 Americo Salas Flying vehicle of inverse sustentation (FVIS)
RU2264952C1 (ru) * 2003-05-12 2005-11-27 Александр Владимирович Петренко Летательный аппарат типа "летающей тарелки"

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4037472A1 (de) * 1990-11-24 1992-01-16 Roland Piek Luftkissenflugscheibe
US5170963A (en) * 1991-09-24 1992-12-15 August H. Beck Foundation Company VTOL aircraft
RU2151717C1 (ru) * 1998-03-02 2000-06-27 Безруков Юрий Иванович Летающая тарелка
US6572053B2 (en) * 2000-09-19 2003-06-03 Americo Salas Flying vehicle of inverse sustentation (FVIS)
RU2264952C1 (ru) * 2003-05-12 2005-11-27 Александр Владимирович Петренко Летательный аппарат типа "летающей тарелки"

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102319989A (zh) * 2011-09-06 2012-01-18 上海交通大学 一种飞机水平尾翼梁缘条的制造方法
CN103419935A (zh) * 2013-07-24 2013-12-04 南京航空航天大学 基于新型增升装置的碟形布局垂直起降飞行器
CN103419923A (zh) * 2013-07-24 2013-12-04 南京航空航天大学 高速附壁流动的推力增益装置
CN105015780A (zh) * 2014-04-29 2015-11-04 沈增 飞碟的制造方法
CN116654256A (zh) * 2023-07-18 2023-08-29 北京舯迦科技有限公司 一种吹气升力环及其应用方法

Also Published As

Publication number Publication date
UA28455U (en) 2007-12-10

Similar Documents

Publication Publication Date Title
EP3363732B1 (fr) Configurations d'éjecteur et de profil aérodynamique
US8448905B2 (en) Aircraft with aerodynamic lift generating device
EP2219942B1 (fr) Systèmes et procédés de commande d'écoulement d'échappement de moteur
JP5779643B2 (ja) 周辺制御イジェクタ
RU2635023C2 (ru) Пилон для установки двигателя на конструкции летательного аппарата
WO2009025632A1 (fr) Aéronef à atterrissage et décollage vertical
US9045227B1 (en) Dual fan aerodynamic lift device
US3065928A (en) Multiple drive for aircraft having wings provided with transverse flow blowers
CA2934346A1 (fr) Vehicule aerien a courte distance de decollage et d'atterrissage
RU86560U1 (ru) Летательный аппарат вертикального взлета и посадки
US10829237B2 (en) Tiltrotor aircraft inlet-barrier filter method and apparatus
WO2009068835A1 (fr) Aile statique pour un aéronef
GB2438848A (en) Static wing for an aircraft
RU2212358C1 (ru) Летательный аппарат
US20180186449A1 (en) Annular lift fan vtol aircraft
GB2351271A (en) Aircraft with annular wing
CN1944188A (zh) 一种带离心风扇可垂直起落的飞行器
GB2088521A (en) Inducing lift on a stationary wing
RU2605466C1 (ru) Самолет вертикального взлета и посадки
JP5211381B2 (ja) 飛行体
JP7217272B2 (ja) ウィングレットエジェクタ構成
RU180623U1 (ru) Самолет вертикального взлета и посадки
RU2149124C1 (ru) Самолет вертикального взлета и посадки "аэроджип"
RU2209746C1 (ru) Летательный аппарат
WO2024112314A1 (fr) Procédé de déviation de flux par effet coanda inverse

Legal Events

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

Ref document number: 08779538

Country of ref document: EP

Kind code of ref document: A1

NENP Non-entry into the national phase

Ref country code: DE

122 Ep: pct application non-entry in european phase

Ref document number: 08779538

Country of ref document: EP

Kind code of ref document: A1