Rocket exhaust disrupter shapes

Acoustics – Sound-modifying means – Muffler – fluid conducting type

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181218, 137896, B64F 126

Patent

active

054224438

ABSTRACT:
Apparatus for reducing the pressure and thermal impingement effects of a supersonic exhaust gas plume emanating from a rocket motor nozzle. A pair of wedge-shaped pieces comprise a disrupter positioned on opposite sides of the central longitudinal axis of the rocket exhaust plume in order to disrupt and disperse the plume concentration. The positioning of these pieces is such that at least a portion of the exhaust gas plume may pass between them. The disrupter defines a flow area normal to the central axis of the exhaust flow which is less than the cross sectional area of the exhaust plume at the position of the disrupter pieces. The reduced flow area causes the exhaust flow to undergo a normal shock wave adjacent the position of the disrupter device before the exhaust gases pass between the disrupter body pieces at subsonic velocity. The presence and configuration of the disrupter device disrupts and disperses the plume concentration, and the reduced flow velocity significantly reduces downstream pressure and thermal effects of the exhaust gas plume.

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