Jetevator for rocket engine

Citation

(1998), "Jetevator for rocket engine", Aircraft Engineering and Aerospace Technology, Vol. 70 No. 3. https://doi.org/10.1108/aeat.1998.12770cad.013

Jetevator for rocket engine

Jetevator for rocket engine

Keywords Aerospace industry, Nissan, Patents, Thrust

In British Patent 2299 558 Nissan Motor Co. Ltd describe a jetevator. It is rotatably installed at a nozzle exit of a rocket engine in order to control the thrust direction of the engine. The jetevator is generally of hollow frustoconical shape and comprises an inner heat resistant layer, an intermediate heat insulating layer, and an outer reinforcing layer. The heat-resistant layer is formed with one or more slits which may divide it into a number of parts. Each slit passes from the inner peripheral surface to the outer peripheral surface of the heat-resistant layer and may be closed with a backplate which extends along the slit. The slits may extend axially or circumferentially or be inclined. They may also comprise a tongue-and-groove-like joint.