Embedded pressurization system for hybrid rocket motor

Details Embedded pressurization system for hybrid rocket motor Embedded pressurization system for hybrid rocket motor

1989-11-03

1992-06-09

Bertsch, Richard A.

Power plants

Reaction motor

Solid and fluid propellant

60253, 60254, 102287, 102288, 102289, F02K 900

Patent

active

051196271

ABSTRACT:
A solid propellant component grain is supported in a combustion chamber. A liquid propellant component container is mounted forward of the combustion chamber. The liquid propellant component is supplied through conduits from the container into the combustion chamber, and ignited to form combustion gas which is discharged out the rear of the combustion chamber to generate thrust for propelling a rocket. A high pressure tank containing a non-flammable gas such as helium is at least partially embedded in the grain. A conduit leads from the tank into the container, such that the high pressure gas pressurizes the container and urges the liquid propellant component to flow from the container into the combustion chamber. The tank provides internal structural support for the grain, with the wall of the combustion chamber constituting a safety barrier in the event of structural failure of the tank after the tank is filled with high pressure gas.

REFERENCES:
patent: 2671312 (1954-03-01), Roy
patent: 2923126 (1960-02-01), Precoul
patent: 3068641 (1962-12-01), Fox
patent: 3214906 (1965-11-01), Coleal
patent: 3323308 (1967-06-01), Greco
patent: 3325998 (1965-04-01), Novotny
patent: 3457727 (1969-07-01), Munger
patent: 3613583 (1971-10-01), Lai
patent: 3715888 (1973-02-01), Massie
patent: 3789610 (1974-02-01), Stone
patent: 3812671 (1974-05-01), Burr et al.
patent: 3945203 (1976-03-01), Rayser

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