Electric propulsion system for aircraft

Aeronautics and astronautics – Aircraft power plants

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244 62, 244 57, 429 14, 429 17, 429 26, B64D 2724

Patent

active

047098821

ABSTRACT:
An aircraft having a rotatively driven blade cooperating with an electrochemical power system for operating an electric drive system. The blade provides cooling heat transfer relative to the lithium/peroxide fuel system effecting desirable separation of the lithium-hydroxide monohydrate in a suitable filter/plenum provided as a portion of the power system. In one form, the cooling is effected by disposing a heat transfer portion of the power system in the path of air flow generated by the propulsion blade of the aircraft. In another form, the cooling is effected by flowing the electrolyte through the propulsion blade. Molarity of the electrolyte is maintained by separating the precipitated lithium-hydroxide monohydrate in solid form in the filter/plenum and addition of replacement hydrogen/peroxide solution from the reservoir thereof.

REFERENCES:
patent: 1605428 (1926-11-01), Dornier
patent: 2455313 (1948-11-01), Osofsky
patent: 3198664 (1965-08-01), Kunz
patent: 3843410 (1974-10-01), Spahrbier
patent: 3937424 (1976-02-01), Meier et al.
patent: 3957230 (1976-05-01), Boucher et al.
patent: 4349613 (1982-09-01), Winsel
Pub. entitled "Electric Propulsion for High Performance Light Aircraft," presented by A. D. Galbraith at AIAA/SAE/ASME 15th Joint Propulsion Conference--Jun. 18-20, 1979 at Las Vegas, Nevada.
Report entitled "Practical Feasibility Assessment of Electric Power Propulsion in Small Helicopters Using Lithium Hydroxide Battery Technology," prepared by P. T. Kirchen, D. R. Jacoby and A. D. Galbraith under Contract No. A84939--B for NASA--AMES Research Center, dated Dec. 1, 1981.

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