Cooling/fuel system for hypersonic flight

Aeronautics and astronautics – Aircraft structure

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244135R, 431 2, 60206, B64D 3734

Patent

active

052361527

ABSTRACT:
The present invention provides for the integration of structural cooling and fuel treatment within hypersonic vehicles. This is achieved by channeling a hydrocarbon fuel to a portion of the aircraft structure and imparting via the heat sink effect sufficient heat to cause a pyrolysis of the hydrocarbon fuel. After pyrolysis, the resulting fractions are then utilized as a fuel by the vehicle.

REFERENCES:
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patent: 3173247 (1965-03-01), Smith et al.
patent: 3263414 (1966-08-01), Herbst
patent: 4817890 (1989-04-01), Coffinberry
patent: 4919364 (1990-04-01), Helmut et al.
patent: 4934632 (1990-06-01), Kyusik et al.
Article entitled "Parametric Study of Airframe-Integrated Scramjet Cooling Requirement," Journal of Propulsion and Power, Authors: Takeshi Kanda, Goro Masuya, Yoshio Wakamatsu, Nobuo Chinzei, and Akio Kanmuri, vol. 7, No. 3, May-Jun. 1991, pp. 431-436.
Article entitled "Active Cooling of a Hydrogen-Fueled Scramjet Engine," Journal of Aircraft, Authors: L. L. Pagel and W. R. Warmbold, vol. 6, No. 5, Sep.-Oct. 1969, pp. 472-474.
Article entitled "Mach 2 Combustion Characteristics of Hydrogen-Hydrocarbon Fuel Mixtures," Johns Hopkins University, The 24th JANNAF Combustion Meeting, vol. 2, pp. 155-169.

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