Dual liquid engine and rocket using the same

Power plants – Reaction motor – Turborocket

Reexamination Certificate

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C060S251000

Reexamination Certificate

active

06952917

ABSTRACT:
The engine for a rocket is suitable for using for an educational program. The engine uses a liquid phase propellant having a predetermined boiling point and a heating substance having a temperature higher than the boiling point. The engine has an inner wall having a circumferential surface; an outer wall surrounding the inner wall, the outer wall having an interior surface spaced from the circumferential surface of the inner wall by a predetermined distance such that the space between the circumferential surface and the interior surface form a mixing chamber having an opening; and injector for injecting the liquid-phase propellant and the heating substance into the mixing chamber so that the propellant is evaporated by the heating substance thereby creating a jet stream moving from the opening of the mixing chamber to the outside of the mixing chamber.

REFERENCES:
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patent: 3771313 (1973-11-01), Kaiho
patent: 4640794 (1987-02-01), Tomita
patent: 5090195 (1992-02-01), Boily
patent: 5794435 (1998-08-01), Jones
patent: 6003302 (1999-12-01), Feldman
patent: 6293091 (2001-09-01), Seymour et al.
patent: 11 04 355 (1961-04-01), None
patent: 2 186 237 (2002-07-01), None
E.V. Mukerjee et al., “Vaporizing liquid microthruster,”Sensors and Actuators A, vol. 83, No. 1-3 (Elseviier Sequoia S.A., Lausanne, Switzerland, May 2000), pp. 231-236.

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