Thrust vector control system for a plug nozzle rocket engine
View Patent ↗A thrust vector control system for a plug nozzle rocket engine for propelling and maneuvering a vehicle is disclosed. The plug nozzle rocket engine includes a housing having a nozzle throat, a plug disposed within the housing and positioned within the nozzle throat to define a space between the plug and the nozzle throat, and a thrust diverter moveably disposed relative to the housing to define an asymmetric pressure distribution along the plug for thrust-vectoring. In one embodiment, the thrust diverter is normally biased to a non-thrust-vectoring position, but is moveable in a plane substantially perpendicular to an axis extending longitudinally through the plug.
1. A thrust vector control system for a plug nozzle rocket engine, comprising:
(a) a housing having a nozzle throat;
(b) a plug disposed relative to the housing and positioned within the nozzle throat to define a space between the plug and the nozzle throat; and
(c) a thrust diverter slideably disposed relative to the housing to provide an asymmetric surface pressure distribution along the plug for thrust-vectoring.
2. A thrust vector control system for a plug nozzle rocket engine, comprising:
(a) a housing having a nozzle throat;
(b) a plug disposed relative to the housing and positioned within the nozzle throat to define a space between the plug and the nozzle throat; and
(c) a thrust diverter moveably disposed relative to the housing to provide an asymmetric surface pressure distribution along the plug for thrust-vectoring, wherein the thrust diverter is slidably disposed relative to the nozzle throat.
3. The thrust vector control system of claim 1 , wherein the thrust diverter is normally biased to a non-thrust-vectoring position.
4. A thrust vector control system for a plug nozzle rocket engine, comprising:
(a) a housing having a nozzle throat;
(b) a plug disposed relative to the housing and positioned within the nozzle throat to define a space between the plug and the nozzle throat; and
(c) a thrust diverter moveably disposed relative to the housing to provide an asymmetric surface pressure distribution along the plug for thrust-vectoring, wherein the thrust diverter is moveable in a plane substantially perpendicular to an axis extending longitudinally through the plug.
5. The thrust vector control system of claim 4 , wherein the thrust diverter includes a plate with an opening having a diameter.
6. The thrust vector control system of claim 5 , wherein the plate includes channels for receiving fasteners.
7. The thrust vector control system of claim 5 , wherein the diameter of the opening is substantially equal to a diameter of the nozzle throat.
8. The thrust vector control system of claim 5 , wherein the thrust diverter is self-centering to reposition the plate to a non-thrust-vectoring position.
9. A thrust vector control system for a plug nozzle rocket engine, comprising:
(a) a housing having a nozzle throat;
(b) a plug disposed relative to the housing and positioned within the nozzle throat to define a space between the plug and the nozzle throat; and
(c) a thrust diverter moveably disposed relative to the housing to provide an asymmetric surface pressure distribution along the plug for thrust-vectoring further comprising a first actuator coupled to the thrust diverter, the first actuator selectively moving the thrust diverter relative to the plug.
10. The thrust vector control system of claim 9 , further comprising a second actuator coupled to the thrust diverter, the first and second actuators selectively moving the thrust diverter relative to the plug.
11. The thrust vector control system of claim 1 , wherein the plug has a first end and a second end, the first end tapering inwardly toward the second end.
12. The thrust vector control system of claim 11 , wherein the second end of the plug terminates downstream from the thrust diverter.
13. A thrust vector control system for a plug nozzle rocket engine, comprising:
(a) a housing having a nozzle throat;
(b) a plug disposed relative to the housing and positioned within the nozzle throat to define a space between the plug and the nozzle throat; and
(c) a thrust diverter moveably disposed relative to the housing to provide an asymmetric surface pressure distribution along the plug for thrust-vectoring, wherein the plug is moveable within the housing between an open position and a closed position relative to the nozzle throat.
14. A thrust vector control system for a plug nozzle rocket engine, comprising:
(a) a housing having a nozzle throat;
(b) a plug translationally mounted within the housing and positioned within the nozzle throat to define a space between the plug and the nozzle throat; and
(c) a thrust diverter slideably disposed relative to the housing to angularly deflect thrust relative to the plug for thrust-vectoring.
15. The thrust vector control system of claim 14 , wherein the thrust diverter is normally biased to a non-thrust-vectoring position.
16. A thrust vector control system for a plug nozzle rocket engine, comprising:
(a) a housing having a nozzle throat;
(b) a plug translationally mounted within the housing and positioned within the nozzle throat to define a space between the plug and the nozzle throat; and
(c) a thrust diverter moveably disposed relative to the housing to angularly deflect thrust relative to the plug for thrust-vectoring, wherein the thrust diverter is moveable in a plane substantially perpendicular to an axis extending longitudinally through the plug.
17. The thrust vector control system of claim 16 , wherein the thrust diverter includes a plate with an opening having a diameter.
18. The thrust vector control system of claim 17 , wherein the diameter of the opening is substantially equal to a diameter of the nozzle throat.
19. The thrust vector control system of claim 17 , wherein the thrust diverter is self-centering to reposition the plate to a non-thrust-vectoring position.
20. A thrust vector control system for a plug nozzle rocket engine, comprising:
(a) a housing having a nozzle throat;
(b) a plug translationally mounted within the housing and positioned within the nozzle throat to define a space between the plug and the nozzle throat; and
(c) a thrust diverter moveably disposed relative to the housing to angularly deflect thrust relative to the plug for thrust-vectoring, further comprising a first actuator coupled to the thrust diverter, the first actuator selectively moving the thrust diverter relative to the plug.
21. The thrust vector control system of claim 20 , further comprising a second actuator coupled to the thrust diverter, the first and second actuators selectively moving the thrust diverter relative to the plug.
22. A thrust vector control system for a plug nozzle rocket engine, comprising:
(a) a housing having a nozzle throat;
(b) a plug translationally mounted within the housing and positioned within the nozzle throat to define a space between the plug and the nozzle throat; and
(c) a thrust diverter moveably disposed relative to the housing to angularly deflect thrust relative to the plug for thrust-vectoring, wherein the plug is moveable within the housing between an open position and a closed position relative to the nozzle throat.
23. A thrust vector control system for a plug nozzle rocket engine, comprising:
(a) means for generating thrust;
(b) means for controlling the thrust, the means for controlling the thrust being operative between full on and full off flow positions; and
(c) means for thrust-vectoring, the means for thrust-vectoring slideably disposed relative to the housing to selectively produce an apparent angular thrust vector deflection by introducing surface pressure asymmetry along the length of a plug.
24. A thrust vector control system for a plug nozzle rocket engine, comprising:
(a) a housing having a nozzle throat;
(b) a plug disposed relative to the housing and positioned within the nozzle throat to define a space between the plug and the nozzle throat, wherein the plug is moveable within the housing between an open position and a closed position relative to the nozzle throat;
(c) a thrust diverter, including a plate having an opening with a diameter, a first actuator coupled to the plate, and a second actuator coupled to the plate;
(d) the plate being moveably disposed relative to the housing in a plane substantially perpendicular to an axis extending longitudinally through the plug;
(e) the plate being normally biased to a non-thrust-vectoring position;
(f) the first and second actuators selectively moving the plate relative to the housing; and
(g) the plate being moveable to a thrust-vectoring position, wherein when the plate is in a thrust-vectoring position, the plate defines an asymmetric surface pressure distribution along the plug.