Aeronautics and astronautics – Spacecraft – With fuel system details
Patent
1974-03-18
1976-05-11
Blix, Trygve M.
Aeronautics and astronautics
Spacecraft
With fuel system details
60245, 244 62, B64G 120
Patent
active
039557847
ABSTRACT:
An aerospace vehicle incorporates within the same stage two different main propulsion systems that are operated in sequence. The first system involves the use of high density-impulse propellants, and the second system involves the use of lower density-impulse propellants to achieve higher final velocities than would otherwise be the case if the total available volume were used for either set of propellants separately. In one arrangement, one stage of a propulsion aerospace vehicle incorporates provisions for carrying and burning three different propellants, --two fuels and a common oxidizer or two oxidizers and a common fuel. Certain of the wing and/or body structures are designed to serve as tankage volume for low pressure storage of at least one of the propellants, which is one that does not require special pressurized tanks. The use of common oxidizer or fuel, and common wing/body/tankage structure, simplifies and lightens the vehicle, thus enhancing its ability to realize the benefits of what is referred to as the mixed-mode propulsion principle. When one of the fuels is utilized in airbreathing engines, additional flexibility is provided for vehicle operation in the atmosphere as well as in space.
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Cushman, Robert H., "F-103 Demise Clouds Dual Cycle Future," Aviation Week, 9/9/57, p. 101.
Hill, Philip G. et al., Mechanics and Thermodynamics of Propulsion, Addison-Wesley Publishing Co., Reading, Massachusetts, 1965, pp. 322-335.
Blix Trygve M.
Kelmachter Barry L.
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