Nozzleless propulsion unit of low aspect ratio

Details Nozzleless propulsion unit of low aspect ratio Nozzleless propulsion unit of low aspect ratio

1990-10-23

1992-06-30

Bertsch, Richard A.

Power plants

Reaction motor

Plural propellants to burn sequentially

60253, 602701, F02K 910, F02K 928

Patent

active

051252295

ABSTRACT:
A propulsion unit for the acceleration of a self-propelled vehicle, such as a missile or a rocket, is loaded with a propellant block secured laterally to the body of the propulsion unit by means of a combustion inhibitor and has an aspect ratio of between 2.5 and 6. The propellant block has one axial duct and at least 6 peripheral ducts and, on its upstream face, is equipped with a fitting secured to the body of the propulsion unit. This fitting provides a free space between the upstream face of the propellant block and the bottom of the body of the propulsion unit, the axial duct and the peripheral ducts opening into this free space via orifices made in the fitting. The combustion gases are ejected rearward without being fed through a nozzle. Sonic velocity is achieved downstream of the ducts.

REFERENCES:
patent: 3535881 (1970-10-01), Schubert
patent: 3879942 (1975-04-01), Poin et al.
Sutton, G. et al. Rocket Propulsion Elements, John Wiley and Sons, NY. 1976. pp. 373-383.
Procinsky, I. M. et al. "Nozzleless Boosters for Integral Rocket Ramjet Systems" AIAA-80-1277. Jul., 1980.

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