IPC분류정보
국가/구분 |
United States(US) Patent
등록
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국제특허분류(IPC7판) |
|
출원번호 |
US-0413182
(2003-04-10)
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발명자
/ 주소 |
- Kim, Steven S.
- Krzewinski, Brian E.
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출원인 / 주소 |
- The United States of America as represented by the Secretary of the Navy
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대리인 / 주소 |
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인용정보 |
피인용 횟수 :
3 인용 특허 :
18 |
초록
▼
A high torque nozzle system for a tube launched rocket has a fixed position nozzle on the rocket and a set of internally positioned erodible vanes inside of the nozzle. The vanes erode as the rocket exits the launcher. The high torque nozzle system has a first section of a rocket nozzle body, a seco
A high torque nozzle system for a tube launched rocket has a fixed position nozzle on the rocket and a set of internally positioned erodible vanes inside of the nozzle. The vanes erode as the rocket exits the launcher. The high torque nozzle system has a first section of a rocket nozzle body, a second section of the rocket nozzle body and a torque ring that contains erodible vanes. The torque ring is fitted into a groove formed by the first and second sections of the rocket nozzle body, which are threaded together.
대표청구항
▼
1. A high torque nozzle system for a tube launched rocket, comprising: a first section of a rocket nozzle body; a second section of the rocket nozzle body; and, a torque ring having a plurality of erodible vanes thereon, wherein the first and second sections of the rocket nozzle body are capab
1. A high torque nozzle system for a tube launched rocket, comprising: a first section of a rocket nozzle body; a second section of the rocket nozzle body; and, a torque ring having a plurality of erodible vanes thereon, wherein the first and second sections of the rocket nozzle body are capable of being interconnected fixing the torque ring within a groove therebetween. 2. The high torque nozzle system of claim 1, further comprising an adhesive to fix the torque ring between the first and second sections of the rocket nozzle. 3. The high torque nozzle system of claim 2, wherein the adhesive comprises a heat resistant epoxy adhesive. 4. The high torque nozzle system of claim 1, wherein the first and second sections of the rocket nozzle are interconnectable by a threaded mating connection. 5. The high torque nozzle system of claim 1, wherein the torque ring comprises a ring structure connected to the plurality of erodible vanes as a single molded piece. 6. The high torque nozzle system of claim 1, wherein the plurality of erodible vanes comprise a composition selected from the group consisting of plastic, thermoplastic, silica-phenolic, glass-phenolic, refractory metal, carbon-carbon, carbon-phenolic, graphite-phenolic and ceramic. 7. The high torque nozzle system of claim 1, wherein the plurality of erodible vanes comprise a thermoplastic composition. 8. The high torque nozzle system of claim 1, wherein the plurality of erodible vanes comprise a phenolic composition. 9. The high torque nozzle system of claim 1, wherein the torque ring comprises a external spin neutral fin assembly. 10. The high torque nozzle system of claim 1, wherein the plurality of erodible vanes are internally positioned inside of the nozzle of the rocket. 11. A rocket comprising the high torque nozzle system of claim 1. 12. The rocket of claim 11, wherein the rocket comprises a 2.75 inch rocket. 13. A method for imparting a spin on a rocket, comprising the steps of: providing a high torque nozzle system for a tube launched rocket comprising a first section of a rocket nozzle body, a second section of the rocket nozzle body and a torque ring having a plurality of erodible vanes thereon, wherein the first and second sections of the rocket nozzle body are interconnected fixing the torque ring within a groove therebetween; and, launching the rocket from the launch tube, wherein the plurality of erodible vanes erode. 14. The method of claim 13, wherein the plurality of erodible vanes erode between about just prior to and just after rocket exit from the launch tube or before. 15. The method of claim 13, wherein the plurality of erodible vanes erode in from about 0.05 seconds to about 0.10 seconds after rocket launch. 16. The method of claim 13, wherein the torque vanes impart from about 10 ft-lb or greater pounds of torque to the launched rocket. 17. The method of claim 16, wherein the torque ring imparts from about 10 ft-lb to about 15 ft-lb of torque to the launched rocket. 18. A rapid spin rocket product produced by the method comprising the steps of: providing a high torque nozzle system for a tube launched rocket comprising a first section of a rocket nozzle body, a second section of the rocket nozzle body and a torque ring having a plurality of erodible vanes thereon, wherein the first and second sections of the rocket nozzle body are interconnected fixing the torque ring within a groove therebetween; and, launching the rocket from the launch tube, wherein the plurality of erodible vanes erode. 19. The product of claim 18, wherein the rocket comprises a 2.75 inch rocket. 20. The product of claim 18, wherein the launched rocket has a Circular Error Probable of from about 5 milliradians or less.
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