Jetavator for rocket engine
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United States of America Patent
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-
Apr 7, 1998
Grant Date -
N/A
app pub date -
Mar 21, 1996
filing date -
Mar 31, 1995
priority date (Note) -
Expired
status (Latency Note)
Importance
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.
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