Rocket exhaust disrupter

Details Rocket exhaust disrupter Rocket exhaust disrupter

1985-12-27

1988-03-29

Fuller, Benjamin R.

Acoustics

Sound-modifying means

Muffler, fluid conducting type

181218, B64F 126

Patent

active

047337516

ABSTRACT:
An apparatus for reducing the pressure and thermal impingement effects of a supersonic exhaust gas plume emanating from a rocket motor nozzle. A disrupter body positioned within the exhaust plume along the central longitudinal axis thereof disrupts and disperses the plume concentration. The body has a central passage through which a portion of the exhaust may pass. The body and passage are sized and shaped to provide a flow area normal to the exhaust flow less than the cross-sectional area of the exhaust plume at the position of the body. The reduced flow area causes the exhaust flow to undergo a normal shock wave upstream of the body before passing through and around the body at a subsonic velocity. The presence and configuration of the body disrupts and disperses the plume concentration, and the reduced flow velocity significantly reduces the downstream pressure and thermal effects of the exhaust gas plume.

REFERENCES:
patent: 318735 (1865-06-01), Smith
patent: 938101 (1909-10-01), Winters
patent: 1685701 (1928-09-01), Blanchard
patent: 2214770 (1940-09-01), McCurdy
patent: 2512823 (1950-06-01), Blundell
patent: 2957537 (1960-10-01), Morgan
patent: 3036653 (1962-05-01), Calabresi
patent: 3159238 (1964-12-01), Shearer
patent: 3455413 (1969-07-01), Henley
patent: 4244440 (1981-01-01), Matta et al.
patent: 4516660 (1985-05-01), Greenlaw

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