WO1988005011A1 - Vertical take-off and landing aircraft - Google Patents

Vertical take-off and landing aircraft Download PDF

Info

Publication number
WO1988005011A1
WO1988005011A1 PCT/CH1988/000001 CH8800001W WO8805011A1 WO 1988005011 A1 WO1988005011 A1 WO 1988005011A1 CH 8800001 W CH8800001 W CH 8800001W WO 8805011 A1 WO8805011 A1 WO 8805011A1
Authority
WO
WIPO (PCT)
Prior art keywords
wings
flow
flaps
control surfaces
airplane
Prior art date
Application number
PCT/CH1988/000001
Other languages
French (fr)
Inventor
Christian Taramasco
Original Assignee
Christian Taramasco
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 Christian Taramasco filed Critical Christian Taramasco
Publication of WO1988005011A1 publication Critical patent/WO1988005011A1/en

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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
    • B64C39/00—Aircraft not otherwise provided for
    • B64C39/08—Aircraft not otherwise provided for having multiple wings

Definitions

  • the present invention uses both the lift of the wings blown by the propellers and the traction force of the latter by means of their breath deflected by the flaps.
  • Figure 1 is an axonometric view of the aircraft.
  • Figure 2. is a side view and in transparency of the air supply system of the control surfaces.
  • Figure 3 is a plan view and transparency of the air supply system of the control surfaces.
  • Figure 4. is an axonometric view of the air supply device of the control air blowing system.
  • Figure 5. is an axonometric view of the air diffusion device of the control air blowing system.
  • Figure 6. is a sectional view of an air diffusion device.
  • Figure 7. is an axonometric view of a version derived from the plane of Figure 1.
  • Figure 1 shows the position of the propellers 1 relative to the three offset wing planes 2.
  • the offset arrangement was chosen in order to reduce the interactions between the wing planes, especially when the flaps are lowered.
  • These three wing planes are joined to their ex ⁇ ends by vertical surfaces 3 which stiffen all of these planes and reduce the induced drag of these by preventing the air from the lower faces from passing over the upper faces.
  • ' s.
  • Behind these planes are the cooling air inlets of the motors 4, the outlets 5 of which are at the level of the motors located inside the aircraft. 'This arrangement makes it possible to avoid disturbing the flow air on the wings.
  • Behind the air inlets are the air supply hatches 6 of the control air blowing system 7
  • Figures 2. and 3. show the positions of the air supply device 9 and air diffusion devices 10 of the air supply system.
  • the flaps 8 are in the lowered position and the offset angle of 45 is noted, making it possible to maintain the speed of the flow of the propellers when the flaps are lowered.
  • Figure 4. shows the way in which part of the flow of propellers is captured by the supply hatches 6, then that in which this flow is distributed to the diffusion devices via the supply channels 11.
  • the power of this device can be increased by the addition of a turbine at the power supply device.
  • FIG. 5. shows the shape and the positions of the diffusion channels 12, and of the diffusion flap 13, the operation of which is indicated in FIG. 6. This makes it possible to direct the flow on one or the other of the faces of each control surface 7, and its movement is controlled by that of the control surfaces to which it is connected.
  • Figure 7 shows a different device from that of fig-re 1. by the number of its plans reduced to two and by its system of power transmission of the engines whose propeller carrying arms are no longer attached to the fuselage but to the wings. Depending on the position of the motors, these arms are attached to the lower or upper planes

Abstract

The wings (2) are washed by the propeller (1) of which the totality of the stream is deviated by flaps (8). The control surfaces remain usable during hovering and transition flight by means of a system for blowing the control surfaces (7).

Description

Avion à décollage et atterrissage verticaux Vertical takeoff and landing aircraft
De nombreux appareils ont tenté le décollage vertical en faisant basculer les ailes sur lesquelles se trouvent les hélices tractives de la position horizontale à la position verticale . Une fois dans cette position , le décollage se fait grâce à la seule force des hélices tractives devenues sustentatrices . De cette façon , on n'utilise pas la por- tance des ailes soufflées par celles-ci .Many aircraft have attempted vertical takeoff by tilting the wings on which the propellers are located from the horizontal position to the vertical position. Once in this position, takeoff takes place thanks to the sole force of the propellers that have become lifted. In this way, the lift of the wings blown by them is not used.
D'autres appareils en soufflant une grande partie ou la totalité de leur surface alaire ne dévient pas la tota¬ lité du flux des hélices par leurs volets et ne décollent donc pas verticalement .Other devices by blowing a large part or all of their wing surface do not deflect the totality of the flow of the propellers by their flaps and therefore do not take off vertically.
II
La présente invention , définie dans la revendication 1. , utilise à la fois la portance des ailes soufflées par les hélices et la force de traction de celles—ci par l'inter¬ médiaire de leur souffle dévié par les volets .The present invention, defined in claim 1., uses both the lift of the wings blown by the propellers and the traction force of the latter by means of their breath deflected by the flaps.
Les dessins suivants montrent les dispositions et le fonctionnement des divers éléments de l'invention .The following drawings show the arrangements and the operation of the various elements of the invention.
La figure 1. est une vue axono ètrique de l'avion .Figure 1. is an axonometric view of the aircraft.
La figure 2. est une vue de profil et en transparence du système de soufflage des gouvernes.Figure 2. is a side view and in transparency of the air supply system of the control surfaces.
La figure 3. est une vue en plan et en transparence du système de soufflage des gouvernes .Figure 3. is a plan view and transparency of the air supply system of the control surfaces.
La figure 4. est un vue axonomètrique du dispositif d' alimentation d'air du système de soufflage des gouvernes .Figure 4. is an axonometric view of the air supply device of the control air blowing system.
La figure 5. est une vue axonomètrique du dispositif de diffusion d'air du système de soufflage des gouvernes . La figure 6. est une vue en coupe d'un dispositif de diffusion d'air .Figure 5. is an axonometric view of the air diffusion device of the control air blowing system. Figure 6. is a sectional view of an air diffusion device.
La figure 7. est une vue axonomètrique d'une version dérivée de l'avion de la figure 1.Figure 7. is an axonometric view of a version derived from the plane of Figure 1.
La figure 1. montre la position des hélices 1 par rap¬ port aux trois plans d'ailes 2 décalées . La disposition décalée a été choisie afin de réduire les interactions entre les plans d'aile , notamment lorsque les volets sont baissés . Ces trois plans d'ailes sont joints à leur ex¬ trémité par des surfaces verticales 3 qui rigidifient l' ensemble de ces plans et diminuent la traînée induite de ceux-ci en évitant à l'air des faces inférieures de passer sur les faces supérieure's . Derrière ces pla'ns se trouvent les entrées d'air de ref oidissement des moteurs 4 dont les sorties 5 se trouvent au niveau des moteurs situés à l' intérieur de l'avion .'Cette disposition permet d' éviter de perturber l'écoulement de l'air sur les ailes .Derrière les entrées d'air se trouvent les trappes d' alimentation d'air 6 du système de soufflage des gouvernes 7Figure 1. shows the position of the propellers 1 relative to the three offset wing planes 2. The offset arrangement was chosen in order to reduce the interactions between the wing planes, especially when the flaps are lowered. These three wing planes are joined to their ex¬ ends by vertical surfaces 3 which stiffen all of these planes and reduce the induced drag of these by preventing the air from the lower faces from passing over the upper faces. ' s. Behind these planes are the cooling air inlets of the motors 4, the outlets 5 of which are at the level of the motors located inside the aircraft. 'This arrangement makes it possible to avoid disturbing the flow air on the wings. Behind the air inlets are the air supply hatches 6 of the control air blowing system 7
Les figures 2. et 3. indiquent les positions du disposi¬ tif d'alimentation d'air 9 et des dispositifs de diffusion d'air 10 du système de soufflage des gouvernes . Sur la figure 2. , les volets 8 sont en position baissée et l'on note l'angle de décalage de 45 permettant de conserver la vitesse du flux des hélices lorsque les volets sont baissés . La figure 4. indique la manière dont est capté une partie du flux des hélices par les trappes d'alimentation 6 , puis celle dont ce flux est distribué aux dispositifs de diffusion par l'intermédiaire des canaux d'alimentation 11. La puissance de ce dispositif peut être augmentée par l' adjonction d'une turbine au niveau du dispositif d'alimenta¬ tion .Figures 2. and 3. show the positions of the air supply device 9 and air diffusion devices 10 of the air supply system. In FIG. 2, the flaps 8 are in the lowered position and the offset angle of 45 is noted, making it possible to maintain the speed of the flow of the propellers when the flaps are lowered. Figure 4. shows the way in which part of the flow of propellers is captured by the supply hatches 6, then that in which this flow is distributed to the diffusion devices via the supply channels 11. The power of this device can be increased by the addition of a turbine at the power supply device.
La figure 5. montre la forme et les positions des canaux de diffusion 12 , et du volet de diffusion 13 , dont le fonctionnement est indiqué sur la figure 6. Celui-ci permet de diriger le flux sur l'une ou l'autre des faces de chaque gouverne 7 , et son mouvement est commandé par celui des gouvernes auxquelles il se trouve relié .FIG. 5. shows the shape and the positions of the diffusion channels 12, and of the diffusion flap 13, the operation of which is indicated in FIG. 6. This makes it possible to direct the flow on one or the other of the faces of each control surface 7, and its movement is controlled by that of the control surfaces to which it is connected.
La figure 7. montre un appareil différent de celui de la figu-re 1. par le nombre de ses plans ramené à deux et par son système de transmission de la puissance des moteurs dont les bras porteur des hélices ne sont plus accolés au fuselage mais aux ailes . Suivant la position des moteurs , ces bras sont accolés sur les plans inférieurs ou supérieurs Figure 7. shows a different device from that of fig-re 1. by the number of its plans reduced to two and by its system of power transmission of the engines whose propeller carrying arms are no longer attached to the fuselage but to the wings. Depending on the position of the motors, these arms are attached to the lower or upper planes

Claims

RevendicationsClaims
1) Avion caractérisé en ce que ses ailes sont disposées dans plusieurs plans et sont décallées dans la direc¬ tion longitudinale de l'avion , les ailes inférieures se trouvant en avant des ailes supérieures , de mani¬ ère à placer la plus grande surface alaire possible dans le flux d'hélices ou de soufflantes de diamètre donné et en ce qu'il comporte des volets pour dévier ce .flux , afin de réaliser des décollages et des atterrissages verticaux .1) Airplane characterized in that its wings are arranged in several planes and are offset in the longitudinal direction of the airplane, the lower wings being in front of the upper wings, so as to place the largest wing surface possible in the flow of propellers or blowers of given diameter and in that it has flaps to deflect this .flux, in order to achieve takeoffs and vertical landings.
2 ) Avion selon revendication I., caractérisé en ce qu'il comporte un dispositif de soufflage des gouvernes constitué de canaux dirigeant un flux d'air sur les gouvernes et de volets placés devant celles-ci et dé¬ viant ce flux sur l'une OU l'autre face de chaque gouverne , permettant de les rendre utilisables lors des vols stationnaires et de transition . 2) Airplane according to claim I., characterized in that it comprises a device for blowing the control surfaces consisting of channels directing an air flow on the control surfaces and flaps placed in front thereof and deflecting this flow on the one OR the other side of each control surface, making it usable during stationary and transitional flights.
PCT/CH1988/000001 1987-01-03 1988-01-04 Vertical take-off and landing aircraft WO1988005011A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH287 1987-01-03
CH2/87-3 1987-01-03

Publications (1)

Publication Number Publication Date
WO1988005011A1 true WO1988005011A1 (en) 1988-07-14

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/CH1988/000001 WO1988005011A1 (en) 1987-01-03 1988-01-04 Vertical take-off and landing aircraft

Country Status (2)

Country Link
AU (1) AU1057688A (en)
WO (1) WO1988005011A1 (en)

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3917973A1 (en) * 1989-06-02 1990-12-06 Istvan Horvath Double decker wing for aircraft - has upper and lower surfaces connected by vertical ribs
DE4237873A1 (en) * 1992-11-10 1994-05-19 Hans Dipl Ing Wirtz Vertical take-off aircraft with active drive and control torque - has drive gas collected in gas channel and conducted via special outlets over complete wing and tailplane surfaces
WO1998012106A1 (en) * 1996-09-19 1998-03-26 S.C.I. Chaneac Et Fils Aircraft with vertical take-off and landing
GB2318558A (en) * 1996-10-23 1998-04-29 Everitt Ray Vehicle with lift producing arrangement
FR2758790A1 (en) * 1997-01-27 1998-07-31 Sci Chaneac Et Fils VTOL aircraft
EP1104741A1 (en) * 1999-12-01 2001-06-06 Manuel Munoz Saiz Aircraft lift arrangement
WO2003059736A3 (en) * 2002-01-14 2004-02-26 Carr Robert Jonathan An aircraft internal wing and design
GB2399324A (en) * 2003-03-14 2004-09-15 John Edward Randell A propulsion arrangement for vertical takeoff aircraft
WO2005058696A1 (en) * 2003-12-18 2005-06-30 Tangshan Da Tang Power Machinery Co., Ltd A device capable of taking-off vertically without rotors
US7147183B1 (en) 2004-01-22 2006-12-12 Robert Jonathan Carr Lift system for an aerial crane and propulsion system for a vehicle
ES2438009A1 (en) * 2012-07-12 2014-01-15 Fº JAVIER PORRAS VILA Plane wings with stabilizer tubes (Machine-translation by Google Translate, not legally binding)
CN103803057A (en) * 2013-12-20 2014-05-21 中国航天空气动力技术研究院 Tandem-wing solar unmanned plane pneumatic configuration structure
WO2020040671A1 (en) * 2018-08-19 2020-02-27 Hernadi Andras Methods for improvements of the closed wing aircraft concept and corresponding aircraft configurations

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR496833A (en) * 1918-09-03 1919-11-18 Le Colonel Romeo Frassinetti Improvements in large airplanes
FR671552A (en) * 1928-03-22 1929-12-14 Improvements to airplanes
US2974904A (en) * 1958-12-15 1961-03-14 Lockheed Aircraft Corp Control means for a blowing airflow over a control surface
FR1388795A (en) * 1963-11-30 1965-02-12 Improvements made to the lifting surface of aircraft
FR2076030A1 (en) * 1970-01-12 1971-10-15 Mc Donnell Douglas Corp
US3790107A (en) * 1973-03-16 1974-02-05 Lockheed Aircraft Corp Boundary layer air control mechanism for aircraft

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR496833A (en) * 1918-09-03 1919-11-18 Le Colonel Romeo Frassinetti Improvements in large airplanes
FR671552A (en) * 1928-03-22 1929-12-14 Improvements to airplanes
US2974904A (en) * 1958-12-15 1961-03-14 Lockheed Aircraft Corp Control means for a blowing airflow over a control surface
FR1388795A (en) * 1963-11-30 1965-02-12 Improvements made to the lifting surface of aircraft
FR2076030A1 (en) * 1970-01-12 1971-10-15 Mc Donnell Douglas Corp
US3790107A (en) * 1973-03-16 1974-02-05 Lockheed Aircraft Corp Boundary layer air control mechanism for aircraft

Cited By (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3917973A1 (en) * 1989-06-02 1990-12-06 Istvan Horvath Double decker wing for aircraft - has upper and lower surfaces connected by vertical ribs
DE4237873A1 (en) * 1992-11-10 1994-05-19 Hans Dipl Ing Wirtz Vertical take-off aircraft with active drive and control torque - has drive gas collected in gas channel and conducted via special outlets over complete wing and tailplane surfaces
WO1998012106A1 (en) * 1996-09-19 1998-03-26 S.C.I. Chaneac Et Fils Aircraft with vertical take-off and landing
GB2318558A (en) * 1996-10-23 1998-04-29 Everitt Ray Vehicle with lift producing arrangement
FR2758790A1 (en) * 1997-01-27 1998-07-31 Sci Chaneac Et Fils VTOL aircraft
EP1104741A1 (en) * 1999-12-01 2001-06-06 Manuel Munoz Saiz Aircraft lift arrangement
ES2174690A1 (en) * 1999-12-01 2002-11-01 Saiz Manuel Munoz Aircraft lift arrangement
US7258302B2 (en) 2002-01-14 2007-08-21 Robert Jonathan Carr Aircraft internal wing and design
WO2003059736A3 (en) * 2002-01-14 2004-02-26 Carr Robert Jonathan An aircraft internal wing and design
US6840478B2 (en) * 2002-01-14 2005-01-11 Robert Jonathan Carr Aircraft internal wing and design
GB2399324A (en) * 2003-03-14 2004-09-15 John Edward Randell A propulsion arrangement for vertical takeoff aircraft
GB2399324B (en) * 2003-03-14 2005-08-03 John Edward Randell A propulsion arrangement for a vertical take-off aircraft
WO2005058696A1 (en) * 2003-12-18 2005-06-30 Tangshan Da Tang Power Machinery Co., Ltd A device capable of taking-off vertically without rotors
US7147183B1 (en) 2004-01-22 2006-12-12 Robert Jonathan Carr Lift system for an aerial crane and propulsion system for a vehicle
ES2438009A1 (en) * 2012-07-12 2014-01-15 Fº JAVIER PORRAS VILA Plane wings with stabilizer tubes (Machine-translation by Google Translate, not legally binding)
CN103803057A (en) * 2013-12-20 2014-05-21 中国航天空气动力技术研究院 Tandem-wing solar unmanned plane pneumatic configuration structure
WO2020040671A1 (en) * 2018-08-19 2020-02-27 Hernadi Andras Methods for improvements of the closed wing aircraft concept and corresponding aircraft configurations

Also Published As

Publication number Publication date
AU1057688A (en) 1988-07-27

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