Aeronautics and astronautics – Aircraft sustentation – Sustaining airfoils
Patent
1995-06-05
1998-03-24
Mojica, Virna Lissi
Aeronautics and astronautics
Aircraft sustentation
Sustaining airfoils
244 35A, 244 23C, 244218, 244130, 114 56, D12300, D12319, D12325, B64C 354, B64C 138, B63B 100
Patent
active
057303916
ABSTRACT:
A body configuration for improving the fluid-dynamic performance efficiency of aircraft and watercraft comprises a generally conical upper segment (54) and a generally conical lower segment (56) that are joined at a common base plane (53), achieved by inverting the conical lower segment (56). The slopes of the conical surfaces are determined by the prescribed planform of the craft or vehicle and by the height of the conical segments wherein the height of the conical upper segment (h.sub.u) is less than and typically two-thirds that of the conical lower segment (h.sub.L). Although not limited to elliptical planforms, a generally circular planform (52) is preferred for a vertical takeoff and landing aircraft operating in the subsonic flight regime and an elliptical planform (68), with a large aspect ratio for takeoff and low-speed flight, then rotating to a low-aspect-ratio orientation for supersonic flight operation, is preferred for supersonic transport and single-stage-to-orbit type aircraft. The unique conical configuration allows the aircraft to take off and operate at low-speeds with the high lift and efficiency of the large aspect ratio orientation, operate as an oblique all-wing aircraft during climb and acceleration to higher flight speeds, and then fully transition to the low aspect ratio orientation for high-speed operation, including transonic, supersonic, and hypersonic flight. Allowable modifications are defined to optimize and adapt the universal fluid-dynamic body to satisfy unique functional requirements of potential vehicle applications, including submersible and surface-effects type watercraft.
REFERENCES:
patent: D172112 (1954-05-01), Shoemaker
patent: 514835 (1894-02-01), Mills
patent: 2650780 (1953-09-01), Northrop et al.
patent: 2955776 (1960-10-01), Ziegler
patent: 2995104 (1961-08-01), Mills
patent: 3008669 (1961-11-01), Tanczos et al.
patent: 3073551 (1963-01-01), Bowersox
patent: 3123320 (1964-03-01), Slaughter
patent: 3195496 (1965-07-01), Skuce, II
patent: 3971535 (1976-07-01), Jones
patent: 4836470 (1989-06-01), Criwell
patent: 4955962 (1990-09-01), Mell
patent: 5064143 (1991-11-01), Bucher
patent: 5112120 (1992-05-01), Wood
patent: 5203521 (1993-04-01), Day
patent: 5259571 (1993-11-01), Blazquez
patent: 5538201 (1996-07-01), Gerhardt
National Advisory Committee for Aeronautics (NACA), TN 3183, "Minimum Wave Drag Sirfoil Sections for Arrwo Wings" Cooper et al. May 1954, May 1994.
AIAA 92-4220, M. Waters et al., "Structural & Aerodynamic Considerations for Oblique All-Wing Aircraft".
AIAA 92-4230, T. Galloway et al., "Oblique Wing Supersonic Transport" McGraw-Hill, Inc.
Aerospace Daily, p. 448, Jun. 20, 1994, "MTU Hypersonic Nozzle Test Paves Way For Full Engine Test by 1997".
Aerospace Daily, p. 120, 25 Jan. 95, "Ca Company Plans Frisbee-Like VTOL Aircraft".
Losey, deceased William A.
Losey, executor by Marion E.
Miller, Jr. John A.
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