WO1997001481A1 - Systeme de conduites d'echappement pour avion a decollage et a atterrissage verticaux - Google Patents

Systeme de conduites d'echappement pour avion a decollage et a atterrissage verticaux Download PDF

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Publication number
WO1997001481A1
WO1997001481A1 PCT/AU1996/000392 AU9600392W WO9701481A1 WO 1997001481 A1 WO1997001481 A1 WO 1997001481A1 AU 9600392 W AU9600392 W AU 9600392W WO 9701481 A1 WO9701481 A1 WO 9701481A1
Authority
WO
WIPO (PCT)
Prior art keywords
exhaust
vtol aircraft
lift
wing
nozzle
Prior art date
Application number
PCT/AU1996/000392
Other languages
English (en)
Inventor
Kimberley Vere Sadleir
Original Assignee
Kimberley Vere Sadleir
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 Kimberley Vere Sadleir filed Critical Kimberley Vere Sadleir
Priority to AU61163/96A priority Critical patent/AU6116396A/en
Publication of WO1997001481A1 publication Critical patent/WO1997001481A1/fr

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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
    • 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
    • B64C29/0016—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 free or ducted propellers or by blowers
    • B64C29/0025—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 free or ducted propellers or by blowers the propellers being fixed relative to the fuselage

Definitions

  • the present invention relates to a VTOL aircraft exhaust ducting system particularly, although not exclusively, envisaged for use in improving the controllability of the VTOL aircraft wen in vertical flight.
  • Circular wings are inherently unstable and of little practical use.
  • Conventional wings have substantially straight leading and trailing edges and have a bulbous front section and a tapered rear section. This shape does not lend itself to the tubular exhaust of a circular wing since the tubular exhaust requires a large number of doors to seal the ducts form operation in conventional flight.
  • VTOL aircraft have lift ducts which typically have tight radii on the final downward bend. For efficiency of operation this requires a relatively large number of deflector vanes.
  • the exhaust duct is used of thrust in more than one direction, such as for providing lateral and vertical movement, then it is desirable for the duct to face as much as possible in the opposite direction to the desired force.
  • a VTOL aircraft exhaust ducting system for a wing of a VTOL aircraft, the exhaust ducting system comprising: at least one forward lift duct and at least one rear lift duct each including a nozzle located respectively proximate the leading edge and the trailing edge ofthe wing, the nozzle being moveable from a first position in which the nozzle moves to close off an exhaust from a lift fan ofthe VTOL aircraft, and conforms to the shape of the wing and a second position in which the nozzle moves to opens up for directing air downwardly for providing vertical lift, the nozzles increasing the length of the exhaust path so as to improve the pitch, roll and yaw control which can be exercised over the VTOL aircraft.
  • the exhaust ducting system also includes control ducts which have a constant cross- section as they are moved between directing 100% of exhaust gases downwardly and directing 100% of the exhaust gases upwardly so as to achieve an continuous degree of control during manoeuvring ofthe VTOL aircraft.
  • Figure 1.1 is a lower plan view of a VTOL aircraft inco ⁇ orating an exhaust ducting system in accordance with the preset invention
  • Figures 1.2 and 1.3 are cross-sectional perspective views taken on line 1-1 of Figure 1.1, and respectively show the nature of passage of exhaust gases from the VTOL aircraft through the exhaust ducting system, and the VTOL aircraft without the exhaust gas flows;
  • Figures 2.1 to 2.3 are respectively cross-sectional view on a longitudinal slice of the VTOL aircraft of Figure 1.1 showing the orientation of lift control ducts for controlling the VTOL aircraft;
  • Figure 3 is a comparison between the exhaust ducting system of the present invention and that of my US Patent 5,407,150, showing how much longer the exhaust path is in the case ofthe present invention.
  • Figures 4.1 and 4.2 are longitudinal cross-sectional views showing a set of control ducts of the exhaust ducting system ofthe present invention.
  • FIG 1.1 there is shown a VTOL aircraft 10 having a delta wing 12 under which is located a cabin 14.
  • the wing 12 includes forward lift duct exhausts 20, rear lift duct exhausts 22, forward control duct exhausts 24 and rear control duct exhausts 26 - as more particularly shown in Figures 2.1 to 2.3 and Figures 4.1 and 4.2.
  • the exhausts 20 to 26 each have an exhaust air masses flowing through them as shown in Figure 1.2.
  • the larger air masses represent the flow of air through the lift duct exhausts 20 and 22 and the smaller air masses represent the flow of air through the control duct exhausts 24 and 26.
  • the footprint of the forward lift control exhausts 20 is outside the shadow of the wing 12 which produces a relatively large leverage effect to achieve good stability when in vertical hover and flight mode and to improve pitch yaw and roll control.
  • the relative sizes is also shown in the size ofthe air masses 30, 32,34 and 36 respectively which each ofthe ducts 20 to 26 produces in response to air intake masses 38..
  • the wing 12 has a leading edge 40 and a trailing edge 42.
  • An upper surface of the wing 12 is closed off by gull wing doors 44, below which is located a lift fan 46 and four lift ducts 48 and 50.
  • the lift ducts 48 are disposed towards the leading edge 40 and the lift ducts 50 are disposed towards the trailing edge 42.
  • the lift ducts each have a nozzle 60 which is hinged to the wing 12 for pivoting from a closed position as shown in Figure 2.1 and an open position as shown in Figure 2.3.
  • the nozzle 60 ofthe forward lift duct exhausts 20 are hinged at one end ofthe nozzle 60 so as to allow the nozzle 60 to hinge out of the wing 12, whereas the nozzle 60 of the rear lift duct exhausts 22 hinge intermediate the length of the nozzle 60.
  • the nozzle 60 ofthe rear lift duct exhausts 22 opens at an acute angle to air passing over the underside of the wing 12 so as to avoid scooping air into the lift duct 50.
  • the rear lift duct nozzles 60 can act as an air brake.
  • those nozzles 60 serve to produce a venturi effect when the exhaust 22 is first opened. This has the effect of drawing air through the lift ducts 50 which initiates rotation ofthe lift fan 46 for easing the load that a drive motor experiences when the lift fan 46 is turned on.
  • the forward exhausts 20 have exhaust deflecting vanes 64, an air deflecting vane 66 and a double hinged door 68.
  • the angle of the vanes 64 is controllable for controlling the direction of the exhaust air masses 30 for propelling the VTOL aircraft 10 in forward and reverse flight.
  • the air deflecting vanes 64 assist the smooth flow of air around the bend of the nozzles 60.
  • the double hinged doors 68 maintain the seal of the lift duct 48 regardless of the disposition of the nozzle 60 of the forward exhausts 20.
  • the forward exhausts 20 have the effect of conducting the exhaust gases further outward from the lift fan 46 which produces the improvements in control and handling as described hereinabove
  • the rear exhausts 20 are similar in construction to the forward exhausts and like numerals denote like parts
  • the main difference is that the nozzles 60 of the rear exhausts 22 has a door 70 which is substantially planar and capable of acting as an air brake
  • the control duct exhausts 24 each comprise a pair of duct doors 80, and an upper vane 82 and a lower vane 84
  • the duct dors 80 pivot at their juncture and pivot outwardly in the direction of arrows 88 to allow air to flow from the fan to an upward or a downward direction or an combination of both
  • the vanes 82 and 84 are hinged to the control duct at their upstream end and are coupled together proximate their downstream end The coupling ensures that the cross-sectional area of the control duct exhaust 24 remains constant even when the direction ofthe flow of air is being altered
  • the control duct exhaust 26 is conveniently in the form of a rotary splitter 90 with an upwardly disposed conduit 92 and a downwardly disposed conduit 94 Rotation of the splitter 90 can block air as shown in Figure 4 2 and allow the flow of air as shown in Figure 4 1 - for the purposes of controlling the attitude ofthe VTOL aircraft 10
  • the VTOL aircraft 10 In use, when taking off from the ground, the VTOL aircraft 10 has the lift exhausts 20 and 22 set down as shown in Figure 2 3 Air then flows through the ducts 48 and 50 and out of he exhausts 20 and 22 at a relatively large distance form the lift fan 46 for achieving better stability when in vertical flight During transition to horizontal flight the nozzles 60 are angled backwardly as shown in Figure 2.2 As the forward speed ofthe VTOL aircraft 10 increases the angle of the nozzles 60 can be set less until they are closed as shown in Figure 2 1 (at which time the gull wings doors 44 are also closed)
  • the exhaust ducting system of the present invention has the advantage that the exhaust gases are directed to a relatively large distance from the lift fan so as to achieve better stability for the VTOL aircraft when in vertical flight It also has the advantage that the amount of forward thrust from the lift exhausts 20 and 22 during transition decreases gradually and controllably Further the exhausts 24 have a constant cross-section regardless of their disposition which ensures smooth transfer of air between up and down exhausting modes which results in more confident control ofthe VTOL aircraft 10

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Ventilation (AREA)

Abstract

On décrit un système de conduites d'échappement destiné notamment à une aile (12) d'avion à décollage et à atterrissage verticaux (de type VTOL), ce système comprenant: au moins un conduit (20) de sustentation avant ainsi qu'au moins un conduit (22) de sustentation arrière, chacun comportant une buse (60) placée respectivement à proximité du bord (40) d'attaque et du bord (42) de fuite de l'aile (12), la buse (60) étant mobile entre une première position dans laquelle elle se déplace pour fermer l'échappement provenant d'une soufflante (46) de sustentation de l'avion de type VTOL et se conforme à la forme de l'aile (12), et une seconde position dans laquelle elle se déplace pour ouvrir cet échappement, afin de diriger l'air vers le bas et produire une sustentation verticale, ces buses augmentant la longueur du trajet d'échappement de manière à améliorer la régulation du tangage, du roulis et des lacets que l'on peut expérimenter à bord d'un avion de type VTOL. Ce système de conduites d'échappement comporte également des conduites de commande présentant une section constante lorsqu'on déplace ces dernières entre une position dans laquelle elles dirigent 100 % des gaz d'échappement vers le bas et une position dans laquelle elles dirigent 100 % de ces gaz vers le haut, afin d'obtenir un degré continu de commande lors de la manoeuvre d'un avion de type VTOL.
PCT/AU1996/000392 1995-06-26 1996-06-26 Systeme de conduites d'echappement pour avion a decollage et a atterrissage verticaux WO1997001481A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AU61163/96A AU6116396A (en) 1995-06-26 1996-06-26 Vtol aircraft exhaust ducting system

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
AUPN3746A AUPN374695A0 (en) 1995-06-26 1995-06-26 Improved vtol aircraft exhaust ducting system
AUPN3746 1995-06-26

Publications (1)

Publication Number Publication Date
WO1997001481A1 true WO1997001481A1 (fr) 1997-01-16

Family

ID=3788085

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/AU1996/000392 WO1997001481A1 (fr) 1995-06-26 1996-06-26 Systeme de conduites d'echappement pour avion a decollage et a atterrissage verticaux

Country Status (2)

Country Link
AU (1) AUPN374695A0 (fr)
WO (1) WO1997001481A1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2018136844A1 (fr) * 2017-01-20 2018-07-26 Vedamanikam Maran John Aéronef vtol ayant une poussée canalisée à partir d'un ventilateur central
WO2020076608A1 (fr) * 2018-10-09 2020-04-16 Rivellini Stefano Drone à soufflante canalisée à tube coudé
WO2021034783A1 (fr) * 2019-08-19 2021-02-25 Mark Holtzapple Systèmes de propulsion et poussée-portance améliorées

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3915411A (en) * 1974-07-24 1975-10-28 Distler Paul R Discoidal aircraft
GB2050260A (en) * 1979-05-29 1981-01-07 Rolls Royce V/stol aircraft
US4301980A (en) * 1978-12-29 1981-11-24 General Dynamics Corporation Propulsion system for a V/STOL airplane
US4773618A (en) * 1987-01-21 1988-09-27 Ow Gordon J W High speed vertical take-off and landing aircraft
GB2229408A (en) * 1989-02-08 1990-09-26 Boeing Canada Ltd Jet engine thrust deflector
WO1992001603A1 (fr) * 1990-07-25 1992-02-06 Sadleir Vtol Aircraft Co. Pty. Ltd. Unite de propulsion pour avion a decollage vertical et a atterrissage vertical
US5312069A (en) * 1992-07-15 1994-05-17 Lockheed Corporation Propulsion system for an aircraft providing V/STOL capability
DE4237873A1 (de) * 1992-11-10 1994-05-19 Hans Dipl Ing Wirtz Senkrechtstartflugzeug mit aktiver Auftriebserzeugung und aktiver Steuermomenterzeugung

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3915411A (en) * 1974-07-24 1975-10-28 Distler Paul R Discoidal aircraft
US4301980A (en) * 1978-12-29 1981-11-24 General Dynamics Corporation Propulsion system for a V/STOL airplane
GB2050260A (en) * 1979-05-29 1981-01-07 Rolls Royce V/stol aircraft
US4773618A (en) * 1987-01-21 1988-09-27 Ow Gordon J W High speed vertical take-off and landing aircraft
GB2229408A (en) * 1989-02-08 1990-09-26 Boeing Canada Ltd Jet engine thrust deflector
WO1992001603A1 (fr) * 1990-07-25 1992-02-06 Sadleir Vtol Aircraft Co. Pty. Ltd. Unite de propulsion pour avion a decollage vertical et a atterrissage vertical
US5312069A (en) * 1992-07-15 1994-05-17 Lockheed Corporation Propulsion system for an aircraft providing V/STOL capability
DE4237873A1 (de) * 1992-11-10 1994-05-19 Hans Dipl Ing Wirtz Senkrechtstartflugzeug mit aktiver Auftriebserzeugung und aktiver Steuermomenterzeugung

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2018136844A1 (fr) * 2017-01-20 2018-07-26 Vedamanikam Maran John Aéronef vtol ayant une poussée canalisée à partir d'un ventilateur central
GB2575565A (en) * 2017-01-20 2020-01-15 John Vedamanikam Maran VTOL aircraft having ducted thrust from a central fan
EP3589541A4 (fr) * 2017-01-20 2021-01-13 Vedamanikam, Maran John Aéronef vtol ayant une poussée canalisée à partir d'un ventilateur central
GB2575565B (en) * 2017-01-20 2022-07-20 John Vedamanikam Maran VTOL aircraft having ducted thrust from a central fan
WO2020076608A1 (fr) * 2018-10-09 2020-04-16 Rivellini Stefano Drone à soufflante canalisée à tube coudé
US11104432B2 (en) 2018-10-09 2021-08-31 Stefano Rivellini Bent tube ducted fan drone
WO2021034783A1 (fr) * 2019-08-19 2021-02-25 Mark Holtzapple Systèmes de propulsion et poussée-portance améliorées

Also Published As

Publication number Publication date
AUPN374695A0 (en) 1995-07-13

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