초록 ▼

A missile includes a control system having divert and attitude control system thrusters with control valves. Each of the control valves has a nozzle plate having a plurality of small nozzles therein. The nozzle plate includes a pair of portions, one of which is rotatable relative to the other. Cont

A missile includes a control system having divert and attitude control system thrusters with control valves. Each of the control valves has a nozzle plate having a plurality of small nozzles therein. The nozzle plate includes a pair of portions, one of which is rotatable relative to the other. Control of flow through the nozzle plate may be effected by relative positioning of the portions of the nozzle plate. An upstream convergent portion of the nozzle plate may be fixed relative to the missile, with a downstream throat and/or divergent portion of the nozzle plate moveable. Movement of the movable portion of the nozzle plate may be accomplished by use of an actuator that is external to the missile body. The control valve provides a simple, lightweight and compact way of controlling flow from a divert thruster.

대표청구항 ▼

What is claimed is: 1. A rocket engine control valve in combination with a pressurized gas source, the combination comprising: the rocket control valve, including: a fixed portion integrated to a pressure chamber and having fixed portion openings therein; and a movable portion having movable portio

What is claimed is: 1. A rocket engine control valve in combination with a pressurized gas source, the combination comprising: the rocket control valve, including: a fixed portion integrated to a pressure chamber and having fixed portion openings therein; and a movable portion having movable portion openings therein; and the pressurized gas source; wherein the movable portion overlies the fixed portion; wherein the movable portion is rotatably mounted to the fixed portion; wherein the fixed portion openings and the movable portion openings combine to produce plural nozzles each having a convergent section, a divergent section, and a throat; wherein the fixed portion openings and the movable portion openings line up, allowing flow therethrough, when the movable portion is in an open position relative to the fixed portion; wherein the fixed portion openings and the movable portion openings are offset from one another, preventing flow therethrough, when the movable portion is in a closed position relative to the fixed portion; and wherein the pressurized gas source is upstream of the control valve. 2. The combination of claim 1, wherein the fixed portion openings include the convergent sections; and wherein the movable portion openings include at least one of the divergent sections and the throats. 3. The combination of claim 1, wherein the fixed portion is a fixed substantially circular plate; wherein the movable portion is a movable substantially circular plate; and wherein the portions are coupled together at a central axis of the circular plates. 4. The combination of claim 3, further comprising an actuator mechanically coupled to the movable portion, for rotating the movable portion relative to the fixed portion. 5. The combination of claim 4, wherein the actuator includes: a motor, a threaded shaft; and a nut on the threaded shaft; and wherein the nut is fixedly coupled to the movable plate, such that rotation of the shaft causes movement of the movable plate. 6. A rocket engine control valve comprising: a fixed portion integrated to a pressure chamber and having fixed portion openings therein; a movable portion having movable portion openings therein; and an actuator mechanically coupled to the movable portion, for rotating the movable portion relative to the fixed portion; wherein the movable portion overlies the fixed portion; wherein the movable portion is rotatably mounted to the fixed portion; wherein the fixed portion openings and the movable portion openings combine to produce plural nozzles each having a convergent section, a divergent section, and a throat; wherein the fixed portion openings and the movable portion openings line up, allowing flow therethrough, when the movable portion is in an open position relative to the fixed portion; wherein the fixed portion openings and the movable portion openings are offset from one another, preventing flow therethrough, when the movable portion is in a closed position relative to the fixed portion; wherein the fixed portion is a fixed substantially circular plate; wherein the movable portion is a movable substantially circular plate; wherein the portions are coupled together at a central axis of the circular plates; wherein the actuator includes: a motor; a threaded shaft; and a nut on the threaded shaft; wherein the nut is fixedly coupled to the movable plate, such that rotation of the shaft causes movement of the movable plate; and wherein the nut has trunnions that engage holes in a yoke that is attached to the movable plate. 7. The combination of claim 4, wherein the actuator is external to a body that encloses a pressurized gas source in communication with the control valve. 8. The combination of claim 1, further comprising a needle bearing between the fixed portion and the movable portion. 9. The combination of claim 1, wherein the plural nozzles include at least ten nozzles. 10. The combination of claim 1, wherein the fixed plate is on an upstream side of the control valve, such that flow through the valve passes through the fixed portion openings before passing through the movable portion openings. 11. The combination of claim 10, wherein the pressurized gas source includes a solid propellant. 12. The combination of claim 10, as part of a missile. 13. The combination of claim 10, as part of a system of divert thrusters that also includes additional of the control valves, controlling thrust in different directions. 14. The combination of claim 13, as part of a control system that also includes attitude control thrusters. 15. A method of controlling thrust from a rocket engine, the method comprising: providing pressurized gas upstream of a control valve; and relatively configuring portions of the control valve, thereby selectively aligning or not aligning plural holes in each of the portions, to thereby allow or shut off flow through the control valve; wherein the holes, when aligned, form plural convergent-divergent nozzles. 16. The method of claim 15, wherein the portions include an upstream fixed portion that includes convergent holes. 17. The method of claim 15, wherein the portions include an upstream fixed portion, and a downstream movable portion. 18. The method of claim 17, wherein the relatively configuring includes rotating the movable portion relative to the fixed portion. 19. A rocket engine control valve comprising: a fixed portion integrated to a pressure chamber and having fixed portion openings therein; and a movable portion having movable portion openings therein; wherein the movable portion overlies the fixed portion; wherein the movable portion is rotatably mounted to the fixed portion; wherein the fixed portion openings and the movable portion openings combine to produce plural nozzles each having a convergent section, a divergent section, and a throat; wherein the fixed portion openings and the movable portion openings line up, allowing flow therethrough, when the movable portion is in an open position relative to the fixed portion; wherein the fixed portion openings and the movable portion openings are offset from one another, preventing flow therethrough, when the movable portion is in a closed position relative to the fixed portion; and wherein the control valve also includes one or more fixed nozzles that are maintained open. 20. A rocket engine control system comprising: a pressurized gas source; and thrusters downstream from the pressurized gas source and receiving flow from the gas source, for controlling thrust in different directions; wherein each of the thrusters includes a control valve and an actuator coupled to the control valve for separately actuating the control valve; wherein each of the control valves includes: a fixed portion integrated to a pressure chamber and having fixed portion openings therein; and a movable portion having movable portion openings therein; wherein the movable portion overlies the fixed portion; wherein the movable portion is rotatably mounted to the fixed portion; wherein the fixed portion openings and the movable portion openings combine to produce plural nozzles each having a convergent section, a divergent section, and a throat; wherein the fixed portion openings and the movable portion openings line up, allowing flow through both the fixed portion openings and the movable portion openings, when the movable portion is in an open position relative to the fixed portion; and wherein the fixed portion openings and the movable portion openings are offset from one another, preventing flow through the fixed portion openings and preventing flow through the movable portion openings, when the movable portion is in a closed position relative to the fixed portion. 21. The control system of claim 20, wherein the fixed portion is a fixed substantially circular plate; wherein the movable portion is a movable substantially circular plate; and wherein the portions are coupled together at a central axis of the circular plates. 22. The control system of claim 21, wherein the actuator includes: a motor; a threaded shaft; and a nut on the threaded shaft; and wherein the nut is fixedly coupled to the movable plate, such that rotation of the shaft causes movement of the movable plate. 23. The control system of claim 20, wherein the fixed plate is on an upstream side of the control valve, such that flow through the valve passes through the fixed portion openings before passing through the movable portion openings. 24. The control system of claim 23, wherein the pressurized gas source includes a solid propellant. 25. The control system of claim 20, as part of a system of divert thrusters that also includes additional of the control valves, controlling thrust in different directions. 26. The control system of claim 20, wherein at least some of the control valves also include one or more fixed nozzles that are maintained open. 27. The method of claim 18, wherein the rotating includes, when shutting off flow through the control valve, shutting off flow first through nozzles that are farther from a central axis of the control valve. 28. A rocket engine control valve comprising: a fixed portion in communication with a pressure chamber and having fixed portion openings therein; and a movable portion having movable portion openings therein; and wherein the movable portion overlies the fixed portion; wherein the movable portion is rotatably mounted to the fixed portion at an axis of the portions; wherein the fixed portion openings and the movable portion openings line up, allowing flow therethrough, when the movable portion is in an open position relative to the fixed portion; wherein the fixed portion openings and the movable portion openings are offset from one another, preventing flow therethrough, when the movable portion is in a closed position relative to the fixed portion; and wherein in moving from the open position to the closed position the fixed portion openings and the movable portion openings offset from one another to prevent flow therethrough first for openings farther from the axis, and later for openings closer to the axis. 29. The control valve of claim 28, wherein the fixed portion openings and the movable portion openings combine to produce plural nozzles each having a convergent section, a divergent section, and a throat.