US3640486A - Flying wing having ground-effect takeoff and landing - Google Patents

Flying wing having ground-effect takeoff and landing Download PDF

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Publication number
US3640486A
US3640486A US22355A US3640486DA US3640486A US 3640486 A US3640486 A US 3640486A US 22355 A US22355 A US 22355A US 3640486D A US3640486D A US 3640486DA US 3640486 A US3640486 A US 3640486A
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US
United States
Prior art keywords
wing
leading edge
flaps
aerodyne
flap
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.)
Expired - Lifetime
Application number
US22355A
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English (en)
Inventor
Jean Henri Bertin
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Bertin Technologies SAS
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Bertin et Cie SA
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Filing date
Publication date
Application filed by Bertin et Cie SA filed Critical Bertin et Cie SA
Application granted granted Critical
Publication of US3640486A publication Critical patent/US3640486A/en
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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B60—VEHICLES IN GENERAL
    • B60V—AIR-CUSHION VEHICLES
    • B60V1/00—Air-cushion
    • B60V1/22—Air-cushion provided with hydrofoils

Definitions

  • This invention relates to an aerodyne consisting essentially of a flying wing arranged to take maximum advantage of the ground efiect for takeoff and landing, with the formation of an air cushion beneath the wing, the aerodyne being designed more particularly for freight transport over large expanses of sea, using large capacity craft (of several hundred tons but of a very simplified structure).
  • the aerodyne comprises a thick profile rectangular wing extending between thin longitudinal panels disposed in the normal direction of travel and provided at the bottom with movable transverse flaps which can be extended downwardly or retracted into the wing profile.
  • the downward movement of the flaps disposed near the leading edge of the wing uncovers a compressed gasirijection means acting as a static pump to supply cushions bounded by the undersurface of the wing, the longitudinal panels and the transverse flaps.
  • the combination of the flaps with the longitudinal panels bounds at least four, and preferably six chambers, whose independent supplies along the span and in series depending upon the depth of the wing provide outstanding trim stability and the possibility of obtaining suitable positioning of the ground effect thrust by actuating the flaps.
  • the pressure beneath the rear of the wing can thus be lower than in the forward compartments and this in combination with the possibly advanced position of an intermediate flap enables the thrust centers to coincide in every case of transitional flight.
  • the bottom and possibly submerged projecting parts can be thin.
  • the stability requires no direct reaction of the water on the structures either dynamically or statically.
  • the aerodyne is advantageously propelled by a plurality of free or faired screws situated, for example, towards the rear of I the wing, between its upper surface and a transverse horizontal profile.
  • the cushion starts at the front near the leading edge of the wing but can preferably terminate at the rear forwardly of the trailing edge to ensure that the thrust center of the cushion coincides with the thrust center of the wing.
  • FIGS. 1 and 2 are respectively diagrammatic front and top plan views of an aerodyne according to the invention.
  • FIG. 3 is a section on the line III-III in FIG. 2.
  • the aerodyne illustrated in FIGS. 1, 2 and 3 consists essentially of a thick rectangular wing 1, inside which are provided loading holds 2 for freight, an engine compartment 3, fuel tanks, and so on.
  • the longitudinal panels 4-4 are secured to the ends of the wing 1 in the normal direction of travel and project considerably around the entire profile of the wing I, and the panels 4 may terminate at the rear in rudders 5.
  • the craft When stationary, and at very low maneuvering speeds, the craft floats on the water by means of the bottom part of the wing.
  • transverse flaps l0, l1 and 12 respectively disposed near the leading edge of the wing, forwardly of its trailing edge, and an intermediate position between these positions, are extended downwardly as will be apparent from FIG. 3.
  • These transverse flaps extend between the longitudinal panels 44 and the bulkheads 7 and 7, the front and rear flaps l0 and 11 closing the bottom longitudinal chambers 8, 8', 8" at the ends, while the intermediate flaps l2 subdivide said chambers into four or six juxtaposed compartments intended for stability of the craft in respect of rolling and pitching.
  • the six-chamber arrangement is preferable for transverse stability.
  • the transverse flaps are retracted into the wing profile, as shown in FIG. 4 in respect of the front flap 10. It will be seen that the upstream part of the static pump 13 is concealed by this flap 10 which restores the profile of the wing 1 when the craft assumes the aerodyne configuration.
  • the rear flaps 11 are preferably disposed forwardly of its trailing edge as indicated hereinbefore and as will be apparent from FIG. 3.
  • the object of this arrangement is to bring the thrust center of the air cushion into coincidence with the aerodynamic thrust center of the wing I in order to avoid any disturbance on transition from skimming flight to free flight and vice versa, by using in combination the differential pressure effect produced between the front and rear compartments of the air cushion by the set of flaps l2 and 11.
  • said air-inducing injector comprises, when unmasked, a downwardly extending openended duct for the flow of induced air, said duct having an upper air intake end adjacent said wing leading edge the rear surface of said leading edge flap when in downwardly extended position.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Transportation (AREA)
  • Mechanical Engineering (AREA)
  • Tires In General (AREA)
  • Catching Or Destruction (AREA)
US22355A 1969-03-24 1970-03-24 Flying wing having ground-effect takeoff and landing Expired - Lifetime US3640486A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR6908543A FR2061519A1 (cs) 1969-03-24 1969-03-24

Publications (1)

Publication Number Publication Date
US3640486A true US3640486A (en) 1972-02-08

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ID=9031147

Family Applications (1)

Application Number Title Priority Date Filing Date
US22355A Expired - Lifetime US3640486A (en) 1969-03-24 1970-03-24 Flying wing having ground-effect takeoff and landing

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US (1) US3640486A (cs)
FR (1) FR2061519A1 (cs)
GB (1) GB1300423A (cs)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4442986A (en) * 1982-08-30 1984-04-17 The United States Of America As Represented By The Secretary Of The Navy Leading edge augmentor wing-in-ground effect vehicle
DE4405152A1 (de) * 1993-02-25 1994-09-01 Fischer Flugmechanik Bodeneffektfahrzeug
RU2209746C1 (ru) * 2002-07-23 2003-08-10 Макаров Игорь Альбертович Летательный аппарат
RU2297951C1 (ru) * 2005-08-31 2007-04-27 Сустин Иван Филимонович Самолет с плоским фюзеляжем
RU2349495C2 (ru) * 2006-10-02 2009-03-20 Хамзат Исхакович Геграев Летательный аппарат

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2575123B2 (fr) * 1983-05-09 1988-07-15 Chaneac Henri Vehicule a coussin d'air
FR2578214B2 (fr) * 1983-05-09 1989-05-12 Chaneac Henri Vehicule a coussin d'air
EP0229536A1 (fr) * 1986-01-09 1987-07-22 André Chaneac Véhicule à coussin d'air et à effet de sol
GB2192372A (en) * 1986-07-08 1988-01-13 Robert Douglas Forb Millington Vehicles and vehicle propulsion systems
DE295652T1 (de) * 1987-06-16 1989-05-11 Mitsubishi Jukogyo K.K., Tokio/Tokyo Flugzeug mit bodeneffekt-fluegeln.
WO1993018950A1 (fr) * 1992-03-25 1993-09-30 Viktor Nikolaevich Kizilov Aeronef a coussin d'air

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2978205A (en) * 1958-09-29 1961-04-04 Ryan Aeronautical Co Tip-jet driven ducted fan for aircraft
US3117643A (en) * 1959-02-13 1964-01-14 Hovercraft Dev Ltd Vehicles for travelling over land and/or water having fluid curtains formed by injector action
US3273826A (en) * 1965-03-03 1966-09-20 Gen Dynamics Corp Variable airfoil high-lift slat and slot for aircraft
US3275266A (en) * 1959-10-20 1966-09-27 Hovercraft Dev Ltd Foils for movement in a fluid
US3342278A (en) * 1965-08-02 1967-09-19 Cocksedge George Thomas Channel pressure control means for air cushion supported craft

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3220501A (en) * 1962-11-09 1965-11-30 Lockheed Aircraft Corp Ground effect machines
US3366195A (en) * 1965-03-24 1968-01-30 Douglas K. Warner Heavy load ground effect machines
US3390655A (en) * 1967-01-17 1968-07-02 Gen Dynamics Corp Patrol craft
FR1548297A (cs) * 1967-05-24 1968-12-06

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2978205A (en) * 1958-09-29 1961-04-04 Ryan Aeronautical Co Tip-jet driven ducted fan for aircraft
US3117643A (en) * 1959-02-13 1964-01-14 Hovercraft Dev Ltd Vehicles for travelling over land and/or water having fluid curtains formed by injector action
US3275266A (en) * 1959-10-20 1966-09-27 Hovercraft Dev Ltd Foils for movement in a fluid
US3273826A (en) * 1965-03-03 1966-09-20 Gen Dynamics Corp Variable airfoil high-lift slat and slot for aircraft
US3342278A (en) * 1965-08-02 1967-09-19 Cocksedge George Thomas Channel pressure control means for air cushion supported craft

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4442986A (en) * 1982-08-30 1984-04-17 The United States Of America As Represented By The Secretary Of The Navy Leading edge augmentor wing-in-ground effect vehicle
DE4405152A1 (de) * 1993-02-25 1994-09-01 Fischer Flugmechanik Bodeneffektfahrzeug
DE4405152C2 (de) * 1993-02-25 2000-03-02 Fischer Flugmechanik Bodeneffektfahrzeug
RU2209746C1 (ru) * 2002-07-23 2003-08-10 Макаров Игорь Альбертович Летательный аппарат
RU2297951C1 (ru) * 2005-08-31 2007-04-27 Сустин Иван Филимонович Самолет с плоским фюзеляжем
RU2349495C2 (ru) * 2006-10-02 2009-03-20 Хамзат Исхакович Геграев Летательный аппарат

Also Published As

Publication number Publication date
GB1300423A (en) 1972-12-20
FR2061519A1 (cs) 1971-06-25

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