Multiple-stage rocket motor nozzle throat

Details Multiple-stage rocket motor nozzle throat Multiple-stage rocket motor nozzle throat

1987-04-22

1989-04-18

Casaregola, Louis J.

Power plants

Reaction motor

Condition responsive thrust varying means

60253, 60271, 23926519, F02K 997

Patent

active

048215104

ABSTRACT:
The invention is concerned with reducing the effect of a progressive surface area versus web thickness relationship in a rocket motor and is particularly useful with center perforate propellant grains where the chamber pressure versus time history is generally progressive. In a very short action time rocket motor, it is desirable to keep the chamber pressure as close as practical to the peak during the entire burn to increase the propellant burn rate. The multiple-stage throat makes this possible in a motor that uses the cost effective center perforate propellant grain design and operates by allowing a first stage throat to erode at a predictable rate while the area of the propellant burning surface is increasing. The motor initial Kn (propellant surface area divided by nozzle area) is raised by using a relatively small initial size for the first stage throat and as a result the rocket motor reaches peak chamber pressure quickly. With the erosion of the first stage matching the increasing propellant surface area the chamber pressure remains nearly constant. Near the end of the burn the first stage throat erodes out to the diameter of a non-eroding second stage throat which then becomes the controlling throat.

REFERENCES:
patent: 3309874 (1967-03-01), Gould
patent: 4574586 (1986-03-01), Gabrysch

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