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FR2906222A1 - Vehicle e.g. helicopter, for transporting passengers, has turbine generating air stream on front wing upper surface, and rear wing with upper surface on which flue gas stream is applied to produce air lift force to allow takeoff and landing - Google Patents

Vehicle e.g. helicopter, for transporting passengers, has turbine generating air stream on front wing upper surface, and rear wing with upper surface on which flue gas stream is applied to produce air lift force to allow takeoff and landing Download PDF

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Publication number
FR2906222A1
FR2906222A1 FR0608353A FR0608353A FR2906222A1 FR 2906222 A1 FR2906222 A1 FR 2906222A1 FR 0608353 A FR0608353 A FR 0608353A FR 0608353 A FR0608353 A FR 0608353A FR 2906222 A1 FR2906222 A1 FR 2906222A1
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FR
France
Prior art keywords
wing
landing
vehicle according
vehicle
compressor
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.)
Granted
Application number
FR0608353A
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French (fr)
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FR2906222B1 (en
Inventor
Michel Aguilar
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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
Priority to FR0608353A priority Critical patent/FR2906222B1/en
Application filed by Individual filed Critical Individual
Priority to EP07823490A priority patent/EP2066564B1/en
Priority to CA002664424A priority patent/CA2664424A1/en
Priority to PCT/FR2007/001452 priority patent/WO2008037865A1/en
Priority to AT07823490T priority patent/ATE481318T1/en
Priority to JP2009529729A priority patent/JP2010504249A/en
Priority to US12/442,778 priority patent/US20100006695A1/en
Priority to DE602007009270T priority patent/DE602007009270D1/en
Priority to ES07823490T priority patent/ES2353029T3/en
Publication of FR2906222A1 publication Critical patent/FR2906222A1/en
Application granted granted Critical
Publication of FR2906222B1 publication Critical patent/FR2906222B1/en
Expired - Fee Related legal-status Critical Current
Anticipated expiration legal-status Critical

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
    • B64C29/0008—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded
    • B64C29/0041—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by jet motors
    • B64C29/005—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by jet motors the motors being fixed relative to the fuselage
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C21/00—Influencing air flow over aircraft surfaces by affecting boundary layer flow
    • B64C21/01—Boundary layer ingestion [BLI] propulsion
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C21/00—Influencing air flow over aircraft surfaces by affecting boundary layer flow
    • B64C21/02—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like
    • B64C21/04—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like for blowing
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/38—Adjustment of complete wings or parts thereof
    • B64C3/385—Variable incidence wings
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/38—Adjustment of complete wings or parts thereof
    • B64C3/44—Varying camber
    • B64C3/48—Varying camber by relatively-movable parts of wing structures
    • 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
    • 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
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/02—Aircraft characterised by the type or position of power plants
    • B64D27/16—Aircraft characterised by the type or position of power plants of jet type
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C2230/00—Boundary layer controls
    • B64C2230/04—Boundary layer controls by actively generating fluid flow
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/10—Drag reduction

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

The vehicle has a turbine (3) that generates air stream on an upper surface of a front wing (1) that is positioned in an inlet of a compressor. The wing (1) is constituted of the upper surface that is adjustable for providing air lift in takeoff phase, and a rigid lower surface. A rear wing (2) is positioned on an outlet of a pipe (11) and has another upper surface on which flue gas stream is applied for producing air lift force to allow takeoff and landing. The wings are arranged around the turbomachine. Injectors (7, 8) take air from the compressor.

Description

1 La présente invention concerne un véhicule à décollage et atterrissageThe present invention relates to a vehicle for take-off and landing

vertical ne présentant aucune voilure tournante. A ce jour, seuls les véhicules à voilure tournante (hélicoptères), les aéronefs à voilure propulsive basculante, dits Convertibles, et les aéronefs à réaction dont au moins une tuyère est orientable vers le bas, permettent un décollage et un atterrissage vertical, ainsi que le vol stationnaire (sustentation). Le déplacement horizontal étant assuré par un léger basculement vers l'avant du rotor principal pour l'hélicoptère, une rotation de 90 degrés vers l'avant de l'ensemble voilure-force propulsive pour les Convertibles, et une orientation quasi horizontale de la tuyère pour les avions à réaction. Le véhicule selon l'invention permet de s'affranchir de ces mouvements de rotation et d'orientation mécaniquement complexes pour assurer le décollage et l'atterrissage vertical. Il est fondé sur le constat suivant : - la turbomachine (réacteur) utilisée pour générer la force propulsive des aéronefs aspire de l'air dans un collecteur dit d'entrée d'air, le comprime, le mélange à un carburant (kérosène...), provoque sa combustion, et rejette à grande vitesse ces gaz brûlés à haute température au travers d'une tuyère. - la force propulsive étant le produit du débit massique (quasiment le nombre de kg d'air aspiré par seconde) par la différence de vitesses entrée-sortie des gaz.  vertical having no rotary wing. To date, only rotary wing vehicles (helicopters), tilting propulsion-type aircraft, so-called Convertibles, and jet aircraft with at least one nozzle that can be tilted downwards, allow a vertical take-off and landing, as well as the hover (sustenance). The horizontal displacement being ensured by a slight tilting towards the front of the main rotor for the helicopter, a 90-degree rotation towards the front of the wing-force propulsion system for the Convertibles, and an almost horizontal orientation of the nozzle for jet aircraft. The vehicle according to the invention eliminates these movements of rotation and orientation mechanically complex to ensure the take-off and vertical landing. It is based on the following observation: - the turbomachine (reactor) used to generate the propulsive force of the aircraft sucks air into a so-called air inlet manifold, compresses it, mixes it with a fuel (kerosene). .), causes its combustion, and rejects at high speed these gases burned at high temperature through a nozzle. the propulsive force being the product of the mass flow rate (almost the number of kg of air sucked per second) by the difference in gas input-output velocities.

Dès lors, en positionnant une voilure fixe aux caractéristiques adaptées (épaisseur, profil, dimensions, matériaux...) en entrée d'air compresseur de la turbomachine et une autre voilure fixe en sortie tuyère tout en ne présentant que les extrados, la vitesse du fluide ainsi produit par la turbomachine créera une portance (force sustentatrice) qui assurera alors le décollage et l'atterrissage.  Therefore, by positioning a fixed wing with the appropriate characteristics (thickness, profile, dimensions, materials, etc.) at the compressor air intake of the turbomachine and another fixed wing at the nozzle exit while presenting only the extrados, the speed fluid thus produced by the turbomachine will create a lift (lift force) which will then ensure takeoff and landing.

Selon les différentes phases de Décollage, d'Atterrissage et cle Croisière, les voilures avant-arrière présenteront les propriétés suivantes : 1 û Voilure avant au décollage : Attendu qu'au décollage, le profil à la plus grande portance est prioritairement recherché, cette voilure sera constituée de deux profils juxtaposés. Son extrados ajustable sera conçu de telle sorte à présenter une portance maximale, alors que l'intrados sera dessiné pour offrir une traînée minimale en phase Croisière (90% du temps de déplacement). De plus, et afin d'amplifier l'effet Coanda , des injecteurs d'air prélevé sur le compresseur seront judicieusement positionnés au-dessus de l'extrados, et orientés vers l'entrée d'air compresseur.  According to the different phases of take-off, landing and cruising, the front-to-back wings will have the following properties: 1 - Wing before take-off: Whereas at take-off, the profile with the greatest lift is primarily sought, this wing will consist of two juxtaposed profiles. Its adjustable extrados will be designed so as to have maximum lift, while the intrados will be designed to offer minimal drag in the Cruising phase (90% of the travel time). In addition, and in order to amplify the Coanda effect, air injectors taken from the compressor will be judiciously positioned above the extrados, and oriented towards the air compressor inlet.

2906222 2 Lors du déplacement horizontal progressif du véhicule, l'extrados ajustable sera réglé de façon à présenter avec son intrados un profil à traînée minimale. Enfin, cette même voilure sera calée pour une incidence optimisée en vitesses de Croisière 5 2 ù Voilure arrière au décollage : Comme les gaz éjectés en sortie tuyère sont à grande vitesse et haute température, il convient de veiller à Ila fatigabilité des matériaux qui composent cet extrados arrière. Pour ce faire, une écope sera aménagée en sortie tuyère de telle sorte à orienter un flux d'air frais (extrait ou non du compresseur), et ainsi s'insérer entre les gaz chauds et l'extrados.2906222 2 During the progressive horizontal movement of the vehicle, the adjustable extrados will be adjusted so as to present with its intrados a profile with minimal drag. Finally, this same wing will be wedged for an optimized incidence in cruising speeds. 5 2 - Rear wing at takeoff: As the ejected gases at the nozzle exit are at high speed and high temperature, it must be ensured that the exhausts of the materials which make up this rear extrados. To do this, a scoop will be fitted as a nozzle outlet so as to direct a flow of fresh air (extracted or not the compressor), and thus be inserted between the hot gas and the extrados.

10 En conséquence, la voilure arrière présentera un profil rigide. Enfin, en phase Croisière, et toujours pour prolonger la vie du matériaux, cette voilure sera légèrement déplacé vers le bas et orienté de façon à assurer la sustentation avec une traînée minimale. L'effet Coanda bien que réduit sera toujours actif augmentant ainsi la sustentation arrière.Consequently, the rear wing will have a rigid profile. Finally, in the Cruising phase, and always to extend the life of the materials, this wing will be slightly moved down and oriented to ensure the lift with minimal drag. The Coanda effect though reduced will still be active thus increasing the rear levitation.

15 La propulsion sera assurée par une turbomachine spécialement conçue en ce qu'elle ne comportera pas une turbine classique dont la fonction est de prélever de l'énergie sur le flux des gaz chauds pour entraîner le compresseur. La chambre de combustion sera orientée bien plus efficacement vers la tuyère d'éjection. Cette nouvelle architecture, affranchie de la turbine, augmentera grandement 20 la durée de vie de ce groupe propulseur. De plus, la consommation de carburant sera nettement moindre que pour une même turbomachine avec sa turbine, d'autant que les vitesses d'éjection recherchées (inférieures à 150 m/s) induiront des températures de combustion bien plus basses, et donc des quantités de carburant plus réduites.The propulsion will be provided by a turbine engine specially designed in that it will not include a conventional turbine whose function is to take energy from the flow of hot gases to drive the compressor. The combustion chamber will be oriented much more efficiently towards the ejection nozzle. This new architecture, freed from the turbine, will greatly increase the life of this powertrain. In addition, the fuel consumption will be significantly lower than for the same turbine engine with its turbine, especially as the desired ejection speeds (less than 150 m / s) will induce much lower combustion temperatures, and therefore quantities less fuel.

25 Le compresseur étant alors entraîné par un moteur extérieur (piston ou autre) dont la fiabilité et la maintenance sont maintenant éprouvées. Au regard des puissances recherchées, la consommation de ce moteur extérieur en sera que plus réduite. Enfin, l'énergie utilisée sera prioritairement renouvelable (huiles végétales...) 2906222 3 Les dessins annexés illustrent l'invention : La figure 1 représente en perspective l'agencement des voilures-avant (1) et arrière (2) autour de la turbomachine (3), ainsi que la partie avant (4) où se tiendront le pilote et ses passagers.The compressor is then driven by an external motor (piston or other) whose reliability and maintenance are now proven. In view of the powers sought, the consumption of this external engine will be reduced. Finally, the energy used will be primarily renewable (vegetable oils ...). The attached drawings illustrate the invention: FIG. 1 represents in perspective the arrangement of the front-wing (1) and the rear-wing (2) around the turbomachine (3), as well as the front part (4) where will be held the pilot and his passengers.

5 La figure 2a représente la voilure-avant (1) constituée de ses deux profils complémentaires : l'extrados (5) ajustable avec son profil offrant une portance maximale en phase Décollage, et son intrados (6) rigide. Des injecteurs (7) et (8) - actifs durant la phase Décollage et Atterrissage - soufflant l'air prélevé sur le compresseur (10) afin d'entretenir et amplifier l'effet Coanda.FIG. 2a shows the front wing (1) consisting of its two complementary profiles: the extrados (5) adjustable with its profile offering maximum lift in the take-off phase, and its intrados (6) rigid. Injectors (7) and (8) - active during the Takeoff and Landing phase - blow the air drawn from the compressor (10) to maintain and amplify the Coanda effect.

10 La figure 2b représente la voilure-avant (1) en phase Croisière dont l'extrados (5), par l'action d'un mécanisme (9), est ramené à une courbure (5') offrant ainsi une traînée minimale ; ladite voilure est ensuite orientée de façon à réduire la traînée globale. La figure 2c représente la voilure-arrière rigide (2) en phase Décollage 15 positionnée derrière la tuyère d'éjection (11) ainsi que l'écope (13) évoquée supra. La figure 2d représente la voilure-arrière (2) en phase Croisière, positionnée en (2') et orientée de façon à minimiser les forces de traînée globale. La figure 3 représente le groupe motopropulseur constitué du compresseur (10), des chambres de combustion, de la tuyère d'éjection (11) et du moteur 20 extérieur (14) pour l'entraînement le compresseur (10).FIG. 2b shows the forward wing (1) in the Cruising phase whose extrados (5), by the action of a mechanism (9), is reduced to a curvature (5 ') thus providing minimal drag; said canopy is then oriented to reduce overall drag. Figure 2c shows the rigid rear wing (2) in the take-off phase 15 positioned behind the ejection nozzle (11) and the bailer (13) mentioned above. Figure 2d shows the cruising rear wing (2), positioned at (2 ') and oriented to minimize overall drag forces. FIG. 3 shows the power unit consisting of the compressor (10), the combustion chambers, the exhaust nozzle (11) and the external motor (14) for driving the compressor (10).

Claims (6)

REVENDICATIONS 1) Véhicule à voilure fixe à décollage et atterrissage vertical caractérisé en ce que le flux d'air généré par une turbomachine (3) sur l'extrados (5) d'une voilure (1) positionnée en entrée compresseur (10), et le flux de ses gaz brûlés soufflant sur l'extrados d'une voilure (2) positionnée en sortie tuyère (11) produisent des forces de portance assurant le décollage et l'atterrissage.  1) Fixed wing vertical take-off and landing vehicle characterized in that the air flow generated by a turbomachine (3) on the upper surface (5) of a wing (1) positioned at the compressor inlet (10), and the flow of its flue gases blowing on the extrados of a wing (2) positioned at the nozzle outlet (11) produces lift forces ensuring take-off and landing. 2) Véhicule selon la revendication 1 caractérisé en ce que, en phase Décollage et Atterrissage, des injecteurs (7) et (8) d'air prélevé sur le compresseur (10) favorisent et amplifient l'effet de portance. En phase Croisière, lesdits injecteurs devenus inactifs présentent un profils et une orientation 1:elle qu'ils participent à l'effet de portance.  2) A vehicle according to claim 1 characterized in that, in the take-off and landing phase, the injectors (7) and (8) of air taken from the compressor (10) promote and amplify the lift effect. In cruise phase, said injectors become inactive have a profile and orientation 1: they participate in the lift effect. 3) Véhicule selon la revendication 1 caractérisé en ce que, en phase Décollage ou Atterrissage, par l'action d'un mécanisme (9), l'extrados (5) de la voilure (1) présente un profil tel que le coefficient de portance (Cz) soit maximale ; l'intrados (6) restant rigide. En phase Croisière, l'extrados (5) est ramené par le même mécanisme (9) en position (5') de façon à présenter cette fois un profil à traînée minimale.  3) Vehicle according to claim 1 characterized in that, in the takeoff or landing phase, by the action of a mechanism (9), the extrados (5) of the wing (1) has a profile such that the coefficient of lift (Cz) is maximum; the intrados (6) remaining rigid. In the Cruising phase, the upper surface (5) is brought back by the same mechanism (9) in position (5 ') so as to present this time a profile with minimal drag. 4) Véhicule selon la revendication 1 caractérisé en ce que une écope (13), située en sortie basse de la tuyère (Il) oriente un flux d'air frais sur l'extrados de la voilure (2) afin d'y réduire fortement la température.  4) Vehicle according to claim 1 characterized in that a scoop (13), located at the bottom outlet of the nozzle (II) orients a flow of fresh air on the upper surface of the wing (2) in order to reduce strongly temperature. 5) Véhicule selon l'une quelconque des revendications précédentes caractérisé en ce que, en phase Croisière, les voilures (1) et (2) sont orientée progressivement vers une position offrant le meilleurs compromis entre force de portance et force de traînée.  5) A vehicle according to any one of the preceding claims characterized in that, in the Cruising phase, the wings (1) and (2) are gradually oriented towards a position offering the best compromise between lift force and drag force. 6) Véhicule selon la revendication 1 caractérisé en ce que le compresseur (10) de la turbomachine (3) est entraîné par un moteur extérieur (14) autorisant dès alors la suppression de la turbine.  6) Vehicle according to claim 1 characterized in that the compressor (10) of the turbomachine (3) is driven by an external motor (14) allowing the removal of the turbine.
FR0608353A 2006-09-25 2006-09-25 VEHICLE WITH A FIXED VEHICLE WITH TAKE-OFF AND VERTICAL LANDING Expired - Fee Related FR2906222B1 (en)

Priority Applications (9)

Application Number Priority Date Filing Date Title
FR0608353A FR2906222B1 (en) 2006-09-25 2006-09-25 VEHICLE WITH A FIXED VEHICLE WITH TAKE-OFF AND VERTICAL LANDING
CA002664424A CA2664424A1 (en) 2006-09-25 2007-09-10 Vertical take-off and landing vehicle which does not have a rotary wing
PCT/FR2007/001452 WO2008037865A1 (en) 2006-09-25 2007-09-10 Vertical take-off and landing vehicle which does not have a rotary wing
AT07823490T ATE481318T1 (en) 2006-09-25 2007-09-10 VERTICAL TAKE-OFF AND LANDING AIRCRAFT WITHOUT ROTARY WINGS
EP07823490A EP2066564B1 (en) 2006-09-25 2007-09-10 Vertical take-off and landing vehicle which does not have a rotary wing
JP2009529729A JP2010504249A (en) 2006-09-25 2007-09-10 Vertical take-off and landing aircraft without rotor blades
US12/442,778 US20100006695A1 (en) 2006-09-25 2007-09-10 Vertical take-off and landing vehicle which does not have a rotary wing
DE602007009270T DE602007009270D1 (en) 2006-09-25 2007-09-10 SENKRECHT STARTING AND LANDING AIRPLANE WITHOUT ROTATING WINGS
ES07823490T ES2353029T3 (en) 2006-09-25 2007-09-10 VERTICAL TAKE-OFF AND LANDING VEHICLE WITHOUT ROTATING SUSTAINATION PLANS.

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0608353A FR2906222B1 (en) 2006-09-25 2006-09-25 VEHICLE WITH A FIXED VEHICLE WITH TAKE-OFF AND VERTICAL LANDING

Publications (2)

Publication Number Publication Date
FR2906222A1 true FR2906222A1 (en) 2008-03-28
FR2906222B1 FR2906222B1 (en) 2009-08-21

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FR0608353A Expired - Fee Related FR2906222B1 (en) 2006-09-25 2006-09-25 VEHICLE WITH A FIXED VEHICLE WITH TAKE-OFF AND VERTICAL LANDING

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Country Link
ES (1) ES2353029T3 (en)
FR (1) FR2906222B1 (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2953808A1 (en) * 2009-12-11 2011-06-17 li jing Chen AN AIRCRAFT WHOSE PUSH-WEIGHT RATIO IS LESS THAN 1 ARRIVES TO TAKE OFF AND VERTICALLY LAND
WO2012146931A1 (en) * 2011-04-27 2012-11-01 Volerian Ltd Lift generating device
CN103419933A (en) * 2013-07-24 2013-12-04 南京航空航天大学 Vertical take-off and landing aircraft with front wings and rear wings on basis of novel high-lift devices

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB862032A (en) * 1958-10-03 1961-03-01 Power Jets Res & Dev Ltd Aircraft
GB955845A (en) * 1960-03-18 1964-04-22 Robert Pouit Improvements in vertical take-off and landing aircraft
GB1465412A (en) * 1975-02-14 1977-02-23 Coxon J Aircraft
US4848701A (en) * 1987-06-22 1989-07-18 Belloso Gregorio M Vertical take-off and landing aircraft

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB862032A (en) * 1958-10-03 1961-03-01 Power Jets Res & Dev Ltd Aircraft
GB955845A (en) * 1960-03-18 1964-04-22 Robert Pouit Improvements in vertical take-off and landing aircraft
GB1465412A (en) * 1975-02-14 1977-02-23 Coxon J Aircraft
US4848701A (en) * 1987-06-22 1989-07-18 Belloso Gregorio M Vertical take-off and landing aircraft

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2953808A1 (en) * 2009-12-11 2011-06-17 li jing Chen AN AIRCRAFT WHOSE PUSH-WEIGHT RATIO IS LESS THAN 1 ARRIVES TO TAKE OFF AND VERTICALLY LAND
EP2338790A1 (en) * 2009-12-11 2011-06-29 Li Jing Chen VTOL aircraft with a thrust-to-weight ratio smaller than 1
WO2012010965A3 (en) * 2009-12-11 2012-03-15 Chen li jing Vtol aircraft with a thrust-to-weight ratio smaller than 1
WO2012146931A1 (en) * 2011-04-27 2012-11-01 Volerian Ltd Lift generating device
CN103419933A (en) * 2013-07-24 2013-12-04 南京航空航天大学 Vertical take-off and landing aircraft with front wings and rear wings on basis of novel high-lift devices

Also Published As

Publication number Publication date
FR2906222B1 (en) 2009-08-21
ES2353029T3 (en) 2011-02-24

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