Solid-fuel, liquid oxidizer hybrid rocket turbopump auxiliary en

Details Solid-fuel, liquid oxidizer hybrid rocket turbopump auxiliary en Solid-fuel, liquid oxidizer hybrid rocket turbopump auxiliary en

1994-09-16

1996-11-12

Thorpe, Timothy S.

Power plants

Reaction motor

Method of operation

60251, F02K 928

Patent

active

055728642

ABSTRACT:
A propulsion thruster (10) includes a solid-fuel, liquid-oxidizer main rocket engine (11), a tank (22) of liquid oxygen, and a turbine (32)-driven pump (30) for pumping liquid oxygen to the main engine. A solid-fuel, liquid-oxidizer auxiliary engine (40) has its oxidizer input port (50) coupled to the output (30b) of the turbopump, for generating drive fluids for the turbine (32) of the turbopump. The temperature of the turbine drive fluids is reduced to prevent damage to the turbine, and the mass flow rate is increased, by injecting water from a tank (60) into the drive fluids at the output (48) of the auxiliary engine (40). Starting is enhanced by preventing cooling of the solid fuel by the liquid oxidizer, which is accomplished by applying gaseous oxygen from a tank (90) to the oxidizer input port (50) of the auxiliary engine (40).

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