Cooling system for high speed aircraft

Details Cooling system for high speed aircraft Cooling system for high speed aircraft

1979-01-31

1981-06-16

Barefoot, Galen L.

Aeronautics and astronautics

Aircraft structure

60730, 60267, 60259, 62DIG5, 16510414, 244163, B64D 3734, B64C 140

Patent

active

042733049

ABSTRACT:
The invention is for a system which provides total cooling for an aircraft airframe which is designed to fly in the speed range of Mach 2 to Mach 8. The system eliminates the necessity of shielding an aircraft airframe constructed of material such as aluminum. Cooling is accomplished by passing a coolant through the aircraft airframe, the coolant acting as a carrier to remove heat from the airframe. The coolant is circulated through a heat pump and a heat exchanger which together extract essentially all of the added heat from the coolant. The heat is transferred to the aircraft fuel system via the heat exchanger and the heat pump. The heat extracted from the coolant is utilized to power the heat pump. The heat pump has associated therewith power turbine mechanism which is also driven by the extracted heat. The power turbines are utilized to drive various aircraft subsystems, the compressor of the heat pump, and provide engine cooling. This system is accomplished with a small increase in aircraft weight and a total result of a small increase in performance.

REFERENCES:
patent: 2943828 (1960-07-01), Van Driest
patent: 2945653 (1960-07-01), Atkin
patent: 2979293 (1961-04-01), Mount
patent: 3093348 (1963-07-01), Schelp et al.
patent: 3128601 (1964-04-01), Abild

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