| 摘要 |
A lightweight, relatively inexpensive rocket nozzle assembly which is heat resistant, ablative and electrically insulating. The body of the nozzle is molded in fibre reinforced thermosetting resin integrally with a forward metallic retaining ring, a rear metallic fin supporting ring and an electrical contact ring. A graphite throat insert is also provided and helical vanes are integrally molded into the rear portion of the nozzle to effect rotary motion of the exhaust gases. Wrap around fins are secured externally of the nozzle and provided with a retainer ring-shear pin assembly to hold the fins in the closed position for transport, and spring means to deploy the fins after firing and shearing of the shear pins. |
