Patent ID: 9200597
Filing Date: 2015-12-01
Classification: F02K

Abstract:
1. An extendable nozzle for a rocket engine comprising: a guide tube; a main combustion chamber and a throat and a main nozzle all contained within the guide tube; a first annular groove formed on an upper end of the nozzle extension of the guide tube; a second annular groove formed on a lower end of the guide tube; a nozzle extension secured to and axially moveable over the guide tube; the nozzle extension having a third annular groove formed on an upper end; a locking O-ring secured in the first annular groove to engage with the third annular groove and secure the nozzle extension in a stowed position; and, a locking split ring secured in the second annular groove to engage with the third annular groove to secure the nozzle extension in an extended position.