Extendable nozzle for rocket engine
An extendable nozzle for a rocket engine includes a chamber with a main combustion chamber and a throat and a main nozzle formed within a guide tube, where a nozzle extension slides over the guide tube from a stowed position to an extendable position. A locking O-ring secures the nozzle extension in a stowed position, and a locking split ring holds the nozzle extension in the extended position.
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.
2. The extendable nozzle of claim 1 , and further comprising:
a locking nut is threaded over the nozzle extension and forms part of the first annular groove to secure the locking O-ring.
3. The extendable nozzle of claim 1 , and further comprising:
the locking O-ring is a destructible O-ring that is crushed to allow for the nozzle extension to break free from the stowed position.
4. The extendable nozzle of claim 1 , and further comprising:
the locking O-ring is formed from an elastomeric or flexible material.
5. The extendable nozzle of claim 1 , and further comprising:
the split locking ring is a radial compressible ring.
6. The extendable nozzle of claim 1 , and further comprising:
the guide tube is cylindrical shaped.
7. The extendable nozzle of claim 1 , and further comprising:
a burst disk is secured to an open end of the nozzle extension that can be removed from combustion gas discharging from the main nozzle when the nozzle extension is locked in an extended position.
8. The extendable nozzle of claim 1 , and further comprising:
a chamber with the main combustion chamber and the throat and the main nozzle includes the guide tube formed outside of the chamber; and,
a main injector nozzle located in the chamber and opening into the main combustion chamber.
9. 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 first locking member secured in the first annular groove to engage with the third annular groove and secure the nozzle extension in a stowed position; and,
a second locking member secured in the second annular groove to engage with the third annular groove to secure the nozzle extension in an extended position.
10. The extendable nozzle of claim 9 , and further comprising:
the first locking member is a locking O-ring; and,
the second locking member is a locking split ring.
11. The extendable nozzle of claim 9 , and further comprising:
a locking nut is threaded over the nozzle extension and forms part of the first annular groove to secure the first locking member.
12. The extendable nozzle of claim 9 , and further comprising:
the first locking member is a destructible locking O-ring that is crushed to allow for the nozzle extension to break free from the stowed position.
13. The extendable nozzle of claim 9 , and further comprising:
the first locking member is a locking O-ring formed from an elastomeric or flexible material.