초록 ▼

A missile includes a tail section having a multi-nozzle grid with both fixed nozzlettes, and movable, thrust vector nozzlettes. The movable nozzlettes may be configured in a number of discrete array bars, each containing multiple of the movable nozzlettes. Movement of one or more array bars may be

A missile includes a tail section having a multi-nozzle grid with both fixed nozzlettes, and movable, thrust vector nozzlettes. The movable nozzlettes may be configured in a number of discrete array bars, each containing multiple of the movable nozzlettes. Movement of one or more array bars may be used to vector the thrust of the missile, providing roll, yaw, or spinning of the missile, for example.

대표청구항 ▼

What is claimed is: 1. A missile comprising: a nozzle grid including: a plurality of fixed nozzles; and a plurality of movable nozzles; and a pressurized gas source operatively coupled to the nozzle grid; wherein the movable nozzles are divided up into plural separately-actuatable arrays; and

What is claimed is: 1. A missile comprising: a nozzle grid including: a plurality of fixed nozzles; and a plurality of movable nozzles; and a pressurized gas source operatively coupled to the nozzle grid; wherein the movable nozzles are divided up into plural separately-actuatable arrays; and wherein the movable nozzles of each of the arrays are in a separate array bar. 2. The missile of claim 1, wherein the missile includes four array bars. 3. The missile of claim 1, wherein the array bars are axisymmetrically spaced about an axis of the missile. 4. The missile of claim 1, wherein the array bars are configured to be tilted along respective array bar axes, to thereby change orientation of the movable nozzles of the corresponding array bar. 5. The missile of claim 4, further comprising motors operatively coupled to respective of the array bars; wherein the motors are configured to individually tilt the array bars. 6. The missile of claim 1, wherein the fixed nozzles are parts of a nozzle plate; and wherein the array bars are movable within openings in the nozzle plate. 7. The missile of claim 1, wherein the array bars have deformable extensions located within cavities in the nozzle plate; and wherein the deformable extensions are configured to press against walls of the cavities when under pressure, thereby forming a seal between the array bar and the nozzle plate. 8. A missile comprising: a nozzle grid including: a plurality of fixed nozzles; and a plurality of movable nozzles; and a pressurized gas source operatively coupled to the nozzle grid; wherein the fixed nozzles and the movable nozzles are all in communication via a high pressure chamber upstream of the fixed nozzles and the movable nozzles. 9. The missile of claim 8, wherein the fixed nozzles are parts of a nozzle plate. 10. The missile of claim 9, wherein the movable nozzles are movable within openings in the nozzle plate. 11. The missile of claim 9, wherein the fixed nozzles are arranged in a substantially cruciform configuration. 12. The missile of claim 11, wherein the movable nozzles are located at least in part between arms of the cruciform configuration. 13. The missile of claim 12, wherein the movable nozzles are divided up into plural separately-actuatable arrays. 14. The missile of claim 13, wherein the movable nozzles of each of the arrays are substantially in a straight line. 15. A missile comprising: a nozzle grid including: a plurality of fixed nozzles; and a plurality of movable nozzles; a pressurized gas source operatively coupled to the nozzle grid; and movable fins mechanically coupled to the movable nozzles. 16. The missile of claim 15, wherein the movable nozzles are divided up into plural separately-actuatable arrays; wherein the movable nozzles of each of the arrays are in a separate array bar; and further comprising motors, wherein the motors are each operatively coupled to a respective array bar and a respective fin. 17. A missile comprising: a thrust vector control system; and an aerodynamic control system mechanically coupled to the thrust vector control system; wherein the thrust vector control system includes a plurality of movable nozzles; and wherein the aerodynamic control system includes movable fins. 18. The missile of claim 17, wherein the movable nozzles are in multiple array bars; and wherein each of the fins is mechanically coupled to a respective of the array bars. 19. The missile of claim 18, further comprising motors mechanically coupled to the array bars and configured to selectively tilt the array bars; wherein the array bars and the fins are coupled such that tilting of the array bars results in tilting of the corresponding fins. 20. The missile of claim 18, further comprising a plurality of fixed nozzles in a nozzle plate; wherein the array bars are located in openings in the nozzle plate. 21. The missile of claim 20, wherein the fixed nozzles are arranged in a substantially cruciform configuration; and wherein the array bars are located at least in part between arms of the cruciform configuration. 22. A method of propelling a missile, comprising: moving high pressure gas through a plurality of fixed nozzles, to thereby provide thrust to propel the missile; and simultaneously moving the high pressure gas through a plurality of movable nozzles, to thereby provide additional thrust to propel the missile; wherein the moving the gas through the movable nozzles controls at least one of the following: course of the missile, orientation of the missile, and spin rate of the missile. 23. The method of claim 22, further comprising controlling the missile; wherein the controlling includes changing orientation of at least some of the movable nozzles. 24. The method of claim 23, wherein the changing orientation includes tilting one or more array bars; and wherein each of the array bars contains multiple of the movable nozzles. 25. The method of claim 24, wherein the controlling also missile. 26. The method of claim 25, wherein the fins are each mechanically coupled to respective of the array bars.