Aeronautics and astronautics – Composite aircraft
Patent
1994-09-20
1996-07-02
Barefoot, Galen L.
Aeronautics and astronautics
Composite aircraft
244 15, 244 63, 244 55, B64C 3600, B64C 3702
Patent
active
055314007
DESCRIPTION:
BRIEF SUMMARY
TECHNICAL FIELD
The invention relates to aviation engineering and, more particularly, the technological purpose is aimed at carrying large-size cargoes, as well as erection, agriculture fire-fighting, and some other operations.
BACKGROUND ART
Known in the art is an airborne vehicle for long-distance non-stop flights at supersonic flight speeds,said vehicle comprising, a fuselage, a wing with a hinge joint for tilting the wing outboard panel in a horizontal plane, a gas-turbine power plant mounted on the tailplane, a landing gear, and flight controls.
The heretofore-known airborne vehicle Boeing 2707 has been developed by the Boeing Co. (cf. the journal "Technical information", Bureau of Technical Information under the CentraI-Hydrodynamic Institute, No. 15, 1967, pp. 11-29 (in Russian).
However, the known technical solution fails to reduce the operational expenses of such an airborne vehicle with a gas-turbine power plant operating on a hydrocarbon fuel for double-increased or more distances of the so-called "flight-range parameter" MIK, where M stands for the Mach number, I means the specific impulse of the power plant, and K indicates the L/D ratio, said parameter being used for assessing the efficiency of an airborne vehicle, while the value of said parameter is inversely proportional to the airborne vehicle operational costs (c.f. "Hypersonic transport aircraft" by Ya.N.Gaukman, Transport PH, 1967, pp. 17-22 (in Russian)
One more airborne vehicle for long-distance port-stop flights at supersonic speeds is known to comprise a fuselage,a wing with a hinge joint for tilting the outboard wing panel in a horizontal plane, an underwing hydrocarbon-fuel fired power plant, a landing gear, and flight controls (cf. B. Sweetmann and G. Warwick "Blackjack: Soviet B-1 or better?", journal Flight International, No. 12, 1982, pp. 1700-1704).
The aforementioned known technical solution, however, also fails to reduce the vehicle operational costs for increased range of non-stop flight and specified payload due to a low value of the "flight range parameter" MIK applied in the Ya.N.Gaukhman's technique for assessing the efficiency of an airborne vehicle.
DISCLOSURE OF THE INVENTION
The present invention has for its object to provide a longer flying range with a specified payload at reduced operational costs for an airborne vehicle.
As far as the vehicle construction is concerned, the foregoing object is accomplished due to the fact that the airborne vehicle comprises a fuselage, an underwing hydrocarbon-fuel fired power plant, a landing gear, and flight control. The vehicle is also provided with an external suspension unit consisting of shells of additional fuel reservoirs for, e.g., hydrogen. An additional power plant and cowlings form an airfoil capable of creating aerodynamic lift. The suspension unit is held to the fuselage and having a front opening and a rear opening, both has shaped side faces whose axes of symmetry are arranged in a vertical plane that passes through the fuselage center line, a ramjet engine as an additional power plant being interposed between said openings.
The vehicle power plant uses, e.g., hydrogen as a fuel,and features a variable ratio of compression of the air stream in the flow-through section thereof from a minimum value at subsonic flight speeds when the ramjet engine inlet device defined by the side shaped faces of the front opening of the suspension unit and the ramjet engine passage inlet section proper, is located in the "aerodynamic (wing) shadow" of the fuselage, up to a maximum value at high supersonic flight speeds. The degree of compression is varied by changing the position of the ram jet engine inlet device either through displacing the suspension unit downwards with respect to the fuselage center line or by displacing the fuselage center line, using the flight controls,relative to the velocity vector for the magnitude of the trimming angle of attack.
The ramjet engine exit device is established by the side faces of the rear opening of the suspension unit and the rear
REFERENCES:
patent: 2901499 (1961-04-01), Janney II
patent: 3093348 (1963-06-01), Schelp et al.
patent: 3103324 (1963-09-01), Price
patent: 4265416 (1981-05-01), Jackson et al.
Sanger, Sanger News, No. 1, Mar. 1990.
"Technical Information", Bureau of Technical Information under the Central-Hydrodynamic Institute, No. 15, 1967, pp. 11-29.
"Hypersonic transport aircraft" by Ya. N. Gaukman, Transport PH, 1967, pp. 17-22.
"Blackjack: Soviet B-1 or better?", B. Sweetmann and G. Warwick, Flight International, No. 12, 1982, pp. 1700-1704.
"Sverkhzvukovye samolety", Tsikhosh E., 1983, Mir (Moscow), pp. 138-140, pp. 399-402.
"Bezaerodromnaya aviatsiya", Ruzhitsky E. I., 1959, Gosudarstvennoe izdatelstvo oboronnoi promyshlennosti, (Moscow, pp. 53-54.
"Samolety osobykh skhem", Sobolev D. A., 1989, Mashinostroenie, (Moscow), pp. 153-154.
"Vkhodnye ustroistva sverkhzvukovykh samoletov", Nechaev Ju. N., 1963, Voennoe izdatelstvo Ministerstva oborony SSSR, (Moscow), pp. 7-11.
Demidov German V.
Osipov Eduard S.
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