System for removing incident heat from aircraft during flight

Details System for removing incident heat from aircraft during flight System for removing incident heat from aircraft during flight

1996-11-15

1998-08-18

Mojica, Virna Lissi

Aeronautics and astronautics

Aircraft structure

244121, 244124, B69C 100

Patent

active

057948887

ABSTRACT:
The invention relates to a system for removing the heat that is incident upon an aircraft, and especially a supersonic aircraft, during flight. The incident heat is generated by the constant heating effect of aerodynamic friction on the outer skin of the fuselage, by compression heating at the ram or stagnation point and stagnation edges of the aircraft fuselage, and by the heating of external air as it is compressed to cabin pressure. In the present system, the used cabin air is exhausted out of the cabin through a space between the cabin interior panels and the fuselage outer skin, where the airflow absorbs the heat incident through the outer skin and is heated to approximately the temperature of the outer skin. Next, the heated airflow is preferably first filtered through a filter and is then expanded and cooled through an expansion turbine. The output shaft of the turbine can drive a generator to recover useful electrical energy. The cooled and expanded airflow is directed through hollow spaces located between the wing fuel tanks and the underside of the associated wing, to absorb and remove heat incident on the lower surface of the wings. In this manner, the system removes at least a portion of the heat incident on the outer skin of the fuselage and the wings, before the heat reaches the aircraft cabin or the fuel in the fuel tanks, respectively.

REFERENCES:
patent: 3015461 (1962-01-01), Fineblum
patent: 4057104 (1977-11-01), Altoz
patent: 4273304 (1981-06-01), Frosch et al.
patent: 4275857 (1981-06-01), Bergsten
patent: 5149018 (1992-09-01), Clark
patent: 5667168 (1997-09-01), Fluegel

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