Jetavator for rocket engine

Details Jetavator for rocket engine Jetavator for rocket engine

1996-03-21

1998-04-07

Weldon, Kevin

Fluid sprinkling, spraying, and diffusing

Reaction motor discharge nozzle

With means controlling amount, shape or direction of...

2393975, B64C 1506

Patent

active

057354634

ABSTRACT:
A jetavator rotatably installed to a nozzle exit of a rocket engine in order to control the thrust direction of the engine. The jetavator is generally in a hollow frustoconical shape and comprises a heat-resistant layer, a heat insulating layer and a reinforcing layer which are laminated one upon another. The heat-resistant layer is formed with a plurality of slits through which it is divided into a plurality of parts. Each slit is formed passing from the inner peripheral surface to the outer peripheral surface of the heat-resistant layer. Each slit is closed with a backplate which extends along the slit.

REFERENCES:
patent: 2900789 (1959-08-01), Philpot
patent: 3182452 (1965-05-01), Eldred
patent: 3224193 (1965-12-01), Loprete et al.
patent: 3291397 (1966-12-01), Johnson
patent: 3972475 (1976-08-01), Nelson et al.
patent: 4649701 (1987-03-01), Wendel
patent: 5392596 (1995-02-01), Holsapple et al.
"Second Edition--Aerospace Engineering Handbook" by Maruzen Co., Ltd. pp. 934-935, published Sep. 30, 1992.

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