Thrust termination device for solid rocket motor

Power plants – Reaction motor – With thrust direction modifying means

Reexamination Certificate

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Details

C060S254000, C239S265250

Reexamination Certificate

active

07578121

ABSTRACT:
Disclosed is a thrust termination device for a solid rocket motor, which terminates the net thrust by the reverse thrust of the rocket motor produced from the emission of the combustion gas in the reverse direction, when the stage separation signal is transferred at the normal thrust state of the rocket motor. An object of the present invention is to provide a thrust termination device for a rocket motor, which can contrive to accomplish the structural safety and mechanical sealing performance at the combustion chamber condition of the high temperature and high pressure, and easily remove the thrust termination device even at the low pressure state and open the trust termination ports successively with very small impacts when the thrust termination is commanded.

REFERENCES:
patent: 3052091 (1962-09-01), D'Ooge
patent: 3177655 (1965-04-01), White
patent: 3196610 (1965-07-01), Anderson
patent: 3442083 (1969-05-01), Klotz
patent: 3705550 (1972-12-01), Long
patent: 4171663 (1979-10-01), Day et al.
patent: 4484439 (1984-11-01), Singer et al.
patent: 4625649 (1986-12-01), Russell
patent: 5400713 (1995-03-01), Humiston et al.
patent: 5808231 (1998-09-01), Johnston et al.

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