WO2009068835A1 - Aile statique pour un aéronef - Google Patents

Aile statique pour un aéronef Download PDF

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Publication number
WO2009068835A1
WO2009068835A1 PCT/GB2007/004530 GB2007004530W WO2009068835A1 WO 2009068835 A1 WO2009068835 A1 WO 2009068835A1 GB 2007004530 W GB2007004530 W GB 2007004530W WO 2009068835 A1 WO2009068835 A1 WO 2009068835A1
Authority
WO
WIPO (PCT)
Prior art keywords
ring portion
aircraft
wing
diffuser plate
static wing
Prior art date
Application number
PCT/GB2007/004530
Other languages
English (en)
Inventor
Peter Frost-Gaskin
Original Assignee
Peter Frost-Gaskin
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 Peter Frost-Gaskin filed Critical Peter Frost-Gaskin
Priority to PCT/GB2007/004530 priority Critical patent/WO2009068835A1/fr
Publication of WO2009068835A1 publication Critical patent/WO2009068835A1/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

  • This invention relates to aircraft and in particular to a novel design of wing for aircraft.
  • Rotary wing aircraft are also known, for example helicopters/autogyros. Again the wings have an aerofoil shape in cross section, however, lift is generated by rotating the wings at speed through air rather than moving the whole vehicle forward through air as is the case with aeroplanes.
  • the firm GFS Projects of the UK have recently demonstrated an operational flying saucer proposed to be used as an unmanned aerial vehicle in military reconnaissance.
  • the GFS Projects' vehicle comprises an inverted dome shaped canopy with a centrally located vent and incorporates a single axial fan driven by an electric motor to provide propulsion.
  • a series of flaps at the base of the canopy can be manipulated to affect the air flow over the canopy and thereby control yaw pitch and roll movements of the vehicle.
  • Stators provided on the canopy serve as counter rotation devices and make use of the Coanda effect to provide stability and lift.
  • the Coanda effect is a B2007/004530
  • the present invention utilises both the Bernoulli and Coanda effects in a substantially ring shaped static wing to which a fuselage can be attached to provide an aircraft of novel configuration.
  • the static wing of the invention comprises a ring portion having an aerofoil shaped cross section.
  • the leading edge of the aerofoil defines the inner circumference of the ring and trailing edge of the aerofoil the outer circumference of the ring.
  • a diffuser plate is provided over the aperture of the ring portion, the diffuser is larger than the aperture of the ring portion.
  • the diffuser plate has an upper surface whose curvature substantially follows the curvature of the ring portion; the underside of the diffuser plate is similarly curved.
  • the diffuser plate may be rigidly fixed to the ring portion, but desirably is moveable between an open operating position and a closed operating position.
  • an air duct arises between the upper surface of the aerofoil and the underside of the diffuser plate. Air flow hitting the underside of the diffuser plate in the open configuration is entrained toward the upper surface of the ring portion spreading across the upper surface and creating lift of the static wing.
  • the air duct is closed, the upper surfaces of the diffuser plate and ring portions providing a substantially continuous surface for forward travel.
  • Air can be directed to the wing from a main power supply via ducting located beneath the wing.
  • the ducting delivers air to the aperture and over the surfaces of the ring portion.
  • an air intake duct is opened in the ducting.
  • the air intake is open during lift off (when the diffuser plate is in the open operating position).
  • the ring portion is provided with a plurality of elevators positioned around the outer circumference of the ring portion. These can be manoeuvred to provide extra lift during take off and landing and to control pitch movements of the air craft.
  • the upper surface of the ring portion may be provided with a plurality of ailerons or trim controls spaced radially, and desirably symmetrically, about the upper surface.
  • the ailerons/trim controls may be used to provide roll and banking movements of the air craft and to slow the aircraft on landing.
  • the elevators/ailerons/trim controls may be operated by any known means, including but not strictly limited to pneumatic, electromechanical (fly by wire) or hydraulic means.
  • annular diffuser arranged within the aperture of the ring portion and communicating with the underside of the diffuser plate is an annular diffuser which serves to provide an even flow of air over and under the ring portion.
  • the diffuser restricts the volume of air in the centre of the wing, thus controlling air flow.
  • the annular diffuser is desirably incorporated into the diffuser plate.
  • the wing of the invention can be propelled by air flow generated by two counter rotating fans or a compressor which force air through the ducting and over the ring portion to provide the lift. Whilst hot essential, the use of two counter rotating fans is beneficial in that they prevent the need for an anti-torque system.
  • the arrangement of counter-rotating fans supplied by the same power source is achieved by use of a differential gear box. The differential takes power from the engine of the propulsion system and feeds this to two propeller shafts, one is rotated clockwise and the other counter clockwise, counter rotating blades negate the need for tail rotors. It is to be understood, that this is simply one option for propelling the wing of the invention, others of which will no doubt occur to the skilled addressee.
  • Some alternatives include compressors or electrical motors. It will be appreciated that size of airframe will be a limiting factor for some options.
  • the fans are carried in the main fuselage or air frame of the aircraft carried by the wing and are not an essential part of the wing itself.
  • the wing of the invention can be configured to be removable from an aircraft for ease of transport, maintenance and repair.
  • Various advantages result from the use of the wing of the invention on aircraft.
  • the wing enables vertical take off of an aircraft much like a rotary wing aircraft but does not suffer from many of the drawbacks of rotary wing aircraft, for example; retreating blade stall, low speeds, noise, vibration, high maintenance costs due to multiple moving parts and downwash.
  • These features enable aircraft carried by the wing of the invention to be operated from woodland, undergrowth and urban environments and can travel through wooded areas with minimal risk of damage to the static wing, whereas rotary blades would likely be damaged in such applications due to debris interfering with the moving parts of the rotary wing mechanism.
  • Elevator/ailerons where present in the wing may be connected to the fuselage of the air craft by simple electrical/hydraulic/mechanical or pneumatic connections for operating the diffuser plate and similarly such connections can be provided to operate the air intake ducts. Such connections can be easily disconnected and consequently, the wing can very easily be detached from the aircraft. This permits easier transport of the craft and simplifies maintenance and repair of the wing or craft.
  • the invention provides a static wing for use on aircraft that can then be used in environments previously only accessible by rotary wing craft.
  • An aircraft bearing the static wing of the invention has many safety and practical advantages over a rotary wing aircraft.
  • Figure 1 shows schematically an embodiment of a wing in accordance with the invention incorporated with a propulsion system of an aircraft.
  • Figure 2 shows a face on view of the ring portion of the wing showing one of a number of suitable positions for ailerons/trim controls on the wing.
  • Figure 3 shows a cross section of an embodiment of a wing of the invention.
  • a static wing 1 comprises a ring portion 2 having an aerofoil shaped cross section. Positioned above the centre aperture of the ring portion 2 is a diffuser plate 3, the diffuser plate is arranged to be moveable vertically (as shown by the direction arrow) between a closed operational position and an open operational position. In the Figure, the plate is in a partially open position providing an air duct between the underside of the diffuser plate and the upper surface of the ring portion 2. At the outer circumference of the ring portion 2 there are provided a plurality of elevators 4 which are moveable in the directions shown by the arrows. The wing is connected with a propulsion system by means of a mechanical coupling 5.
  • the propulsion system comprises a pair of counter rotating fans 6a, 6b driven by a jet engine 7 to which they are coupled through a differential gear boxl2.
  • the diffuser plate 3 For vertical take off of the aircraft, the diffuser plate 3 is raised into the open operating position and air is drawn through air ducts 8 to the underside of the diffuser plate 3 and directed over the upper surface of the ring portion 2 generating lift.
  • the large air intake 8 is closed and the diffuser plate 3 lowered in to the closed operational position and the aircraft travels forward using traditional principles.
  • the air intake for the jet engine is situated on the engine housing. Stability in forward travel is assisted by dwarf wings (not shown) to the rear of the jet engine on the body of the propulsion system.
  • the propulsion system can be positioned to the rear of an aircraft fuselage and comprises a chamber 6 housing the counter- rotating fans 6a, 6b, jet engines can be symmetrically arranged either side of the chamber 6, a large air intake duct 8 positioned below the chamber 6, just forward of it and aligned centrally with the chamber 6 and fuselage.
  • Figure 2 shows a face on view of the ring portion 2 including a plurality of elevators 4 arranged adjacent its outer circumference and a plurality of ailerons/trim controls 11.
  • the ailerons are essentially flaps hinged along one edge and are typically maintained in a lowered position where they lie substantially against the surface of the ring portion. They may be lifted individually to varying degrees to assist in the turning, rolling or decelerating of the aircraft.
  • Both the elevators and ailerons are symmetrically arranged about an axis which defines the direction of flight of the wing.
  • Figure 3(a) shows the wing with the diffuser plate in an open operating position.
  • Figure 3(b) shows the wing with the diffuser plate in the closed operating position. It can be seen in the latter case that a substantially continuously curved surface is provided for level flying.

Landscapes

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

Abstract

L'invention concerne une aile statique (1) qui comprend une partie annulaire (2) à section transversale en forme de plan de sustentation. Une plaque diffuseur (3) est placée au-dessus de l'ouverture centrale de la partie annulaire (2), et la plaque diffuseur est éventuellement conçue pour être mobile verticalement (comme l'indique la flèche de direction) entre une position fonctionnelle fermée et une position fonctionnelle ouverte. Une pluralité de gouvernes de profondeur (4) est située sur la circonférence extérieure de la partie annulaire (2), lesdites gouvernes étant mobiles dans les directions indiquées par les flèches. L'aile peut être reliée à un système de propulsion au moyen d'un accouplement mécanique (5). Cette aile présente des applications potentielles à la fois sur des plates-formes militaires et sur des aéronefs civils.
PCT/GB2007/004530 2007-11-28 2007-11-28 Aile statique pour un aéronef WO2009068835A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PCT/GB2007/004530 WO2009068835A1 (fr) 2007-11-28 2007-11-28 Aile statique pour un aéronef

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/GB2007/004530 WO2009068835A1 (fr) 2007-11-28 2007-11-28 Aile statique pour un aéronef

Publications (1)

Publication Number Publication Date
WO2009068835A1 true WO2009068835A1 (fr) 2009-06-04

Family

ID=39575683

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/GB2007/004530 WO2009068835A1 (fr) 2007-11-28 2007-11-28 Aile statique pour un aéronef

Country Status (1)

Country Link
WO (1) WO2009068835A1 (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
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
DE102019000682B4 (de) 2019-01-30 2022-07-14 Kmtc Vortifer Projektgesellschaft Mbh Flugkörper für Transport und Verkehr
DE102019210417B4 (de) 2019-01-30 2022-07-14 Kmtc Vortifer Projektgesellschaft Mbh Flugkörper sowie Verfahren zum Betreiben eines Flugkörpers

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB422621A (en) * 1933-08-22 1935-01-15 Hirohisa Nishi Improvements in arrangements for starting flight requiring no gliding
US2547266A (en) * 1947-10-02 1951-04-03 Irving M Hoglin Fluid-jet-sustained aircraft
US2718364A (en) * 1953-07-30 1955-09-20 Ernest L Crabtree Fluid sustained and propelled aircraft having annular shaped body
US3034747A (en) * 1957-01-08 1962-05-15 Constantin P Lent Aircraft with discoid sustaining airfoil
US3397853A (en) * 1966-10-05 1968-08-20 William B. Richardson Sr. Fluid sustained vehicle
US3785592A (en) * 1971-10-04 1974-01-15 K Kerruish Vtol aircraft
WO1990013478A1 (fr) * 1989-05-12 1990-11-15 Terence Robert Day Aeronef de forme annulaire
DE4112585A1 (de) * 1991-04-17 1991-08-29 Hans Geschka Ringfluegel-luftfahrzeug
GB2438848A (en) * 2006-06-07 2007-12-12 Peter Frost-Gaskin Static wing for an aircraft

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB422621A (en) * 1933-08-22 1935-01-15 Hirohisa Nishi Improvements in arrangements for starting flight requiring no gliding
US2547266A (en) * 1947-10-02 1951-04-03 Irving M Hoglin Fluid-jet-sustained aircraft
US2718364A (en) * 1953-07-30 1955-09-20 Ernest L Crabtree Fluid sustained and propelled aircraft having annular shaped body
US3034747A (en) * 1957-01-08 1962-05-15 Constantin P Lent Aircraft with discoid sustaining airfoil
US3397853A (en) * 1966-10-05 1968-08-20 William B. Richardson Sr. Fluid sustained vehicle
US3785592A (en) * 1971-10-04 1974-01-15 K Kerruish Vtol aircraft
WO1990013478A1 (fr) * 1989-05-12 1990-11-15 Terence Robert Day Aeronef de forme annulaire
DE4112585A1 (de) * 1991-04-17 1991-08-29 Hans Geschka Ringfluegel-luftfahrzeug
GB2438848A (en) * 2006-06-07 2007-12-12 Peter Frost-Gaskin Static wing for an aircraft

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
DE102019000682B4 (de) 2019-01-30 2022-07-14 Kmtc Vortifer Projektgesellschaft Mbh Flugkörper für Transport und Verkehr
DE102019210417B4 (de) 2019-01-30 2022-07-14 Kmtc Vortifer Projektgesellschaft Mbh Flugkörper sowie Verfahren zum Betreiben eines Flugkörpers
US11851182B2 (en) 2019-01-30 2023-12-26 Kmtc Vortifer Projektgesellschaft Mbh Aircraft and method for operating an aircraft

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