[특허]Steerable, intermittently operable rocket propulsion system

Alliant Techsystems Inc.

검색어에 아래의 연산자를 사용하시면 더 정확한 검색결과를 얻을 수 있습니다.
검색연산자

검색연산자	기능	검색시 예
()	우선순위가 가장 높은 연산자	예1) (나노 (기계 \| machine))
공백	두 개의 검색어(식)을 모두 포함하고 있는 문서 검색	예1) (나노 기계) 예2) 나노 장영실
\|	두 개의 검색어(식) 중 하나 이상 포함하고 있는 문서 검색	예1) (줄기세포 \| 면역) 예2) 줄기세포 \| 장영실
!	NOT 이후에 있는 검색어가 포함된 문서는 제외	예1) (황금 !백금) 예2) !image
*	검색어의 *란에 0개 이상의 임의의 문자가 포함된 문서 검색	예) semi*
""	따옴표 내의 구문과 완전히 일치하는 문서만 검색	예) "Transform and Quantization"

과학기술 지식인프라 ScienceON

안녕하세요!
ScienceON 챗봇입니다.
궁금한 것은 저에게 물어봐주세요.

특허 상세정보

MyON담기

내보내기

Steerable, intermittently operable rocket propulsion system

국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F02K-009/00
미국특허분류(USC)	060/253; 060/204
출원번호	US-0728733 (2003-12-05)
등록번호	US-7281367 (2007-10-16)
발명자 / 주소	Rohrbaugh,Eric M. White,Jeffrey M.
출원인 / 주소	Alliant Techsystems Inc.
대리인 / 주소	TraskBritt
인용정보	피인용 횟수 : 12 인용 특허 : 18

초록
▼

A propulsion system including an extinguishable rocket motor and an incorporated maneuver control system. The rocket motor may be of the solid fuel type. One or more proportional axial thrust valves in communication with a pressure vessel or motor case containing a solid fuel propellant may be used to release combustion products for creating axial thrust. A plurality of proportional maneuver control valves in communication with the pressure vessel and having associated maneuver control thrusters may be selectively actuated in different modes of operation to provide control of pitch, yaw and roll. Fully opening all valves in communication with the pressure vessel may be used to cause rapid depressurization to extinguish the propellant. Reignition of the rocket motor may be effected upon repressurization of the pressure vessel through closing at least some of the valves. Ignition grains may be employed to shorten reignition time, and multiple propellant grains may be provided for multiple pulses.

대표
청구항
▼

What is claimed is: 1. A propulsion system, comprising: a pressure vessel containing a propellant, wherein the propellant comprises at least one solid propellant grain; at least one axial thrust valve in communication with the pressure vessel and configured for selectively releasing gases generated by combustion of the propellant within the pressure vessel to directly provide axial thrust; and at least one maneuver control valve in communication with the pressure vessel and configured for selectively releasing gases generated by combustion of the propellant within the pressure vessel to provide thrust for maneuvering, wherein the at least one axial thrust valve and the at least one maneuver control valve are operable in combination for simultaneous opening to rapidly reduce pressure within the pressure vessel to a degree sufficient to substantially extinguish combustion of the at least one solid propellant grain. 2. The propulsion system of claim 1, wherein the at least one axial thrust valve is configured as a proportional valve. 3. The propulsion system of claim 1, wherein the at least one maneuver control valve is configured as a proportional valve. 4. The propulsion system of claim 1, wherein the at least one axial thrust valve is in communication with a thruster located and oriented to provide axial thrust along a longitudinal axis. 5. The propulsion system of claim 4, wherein the at least one maneuver control valve comprises two maneuver control valves, each of the two maneuver control valves in communication with at least one thruster located and oriented to provide maneuver control. 6. The propulsion system of claim 5, wherein the two maneuver control valves each comprise a valve in communication with a mutually opposing thruster located on opposing sides of the longitudinal axis and oriented to effect a change in pitch responsive to selective operation of one of the two maneuver control valves. 7. The propulsion system of claim 6, wherein the mutually opposing thrusters are located in a common plane transverse to the longitudinal axis. 8. The propulsion system of claim 4, wherein the at least one maneuver control valve comprises four maneuver control valves, each maneuver control valve in communication with at least one thruster, the at least one thruster located offset from the longitudinal axis and oriented to effect a change in yaw or roll responsive to selective operation of at least one of the four maneuver control valves. 9. The propulsion system of claim 8, wherein the at least one thruster is disposed as two mutually opposing pairs of thrusters, each thruster pair including mutually parallel thrusters. 10. The propulsion system of claim 9, wherein the mutually opposing pairs of thrusters are located in a common plane transverse to the longitudinal axis. 11. The propulsion system of claim 4, wherein the at least one maneuver control valve comprises four maneuver control valves, each of the four maneuver control valves in communication with at least one thruster located and oriented to provide maneuver control. 12. The propulsion system of claim 11, wherein the four maneuver control valves each comprise a valve in communication with a thruster located offset from the longitudinal axis and oriented to effect a change in at least one of pitch, yaw and roll responsive to selective operation of one or more of the four maneuver control valves. 13. The propulsion system of claim 12, wherein the four thrusters in communication with the four maneuver control valves are located in a common plane transverse to the longitudinal axis. 14. The propulsion system of claim 12, wherein two of the four thrusters are oriented to provide opposing, parallel thrust offset to opposite sides of the longitudinal axis and the other two of the four thrusters are oriented to provide opposing, parallel thrust offset to opposite sides of the longitudinal axis and perpendicular to the two thrusters. 15. The propulsion system of claim 4, wherein the at least one maneuver control valve comprises eight maneuver control valves, each maneuver control valve in communication with a thruster located and oriented to provide maneuver control. 16. The propulsion system of claim 15, wherein the thrusters are disposed as four pairs of thrusters offset from the longitudinal axis, each thruster pair including mutually parallel thrusters opposing another thruster pair and located 90째 circumferentially from two other thruster pairs. 17. The propulsion system of claim 16, wherein the pairs of thrusters are located in a common plane transverse to the longitudinal axis. 18. The propulsion system of claim 1, wherein the at least one solid propellant grain comprises a plurality of solid propellant grains mutually separated by a flame-inhibiting barrier. 19. The propulsion system of claim 18, further comprising at least one igniter separately associated with each solid propellant grain of the plurality. 20. The propulsion system of claim 1, further comprising at least one igniter grain associated with the at least one solid propellant grain. 21. The propulsion system of claim 20, wherein the at least one igniter grain comprises a plurality of separately actuable igniter grains. 22. The propulsion system of claim 1, wherein the pressure vessel, the at least one axial thrust valve, and the at least one maneuver control valve are disposed within a common housing. 23. The propulsion system of claim 1, wherein the at least one axial thrust valve and the at least one maneuver control valve are operable in combination for simultaneous opening to rapidly reduce pressure within the pressure vessel to a degree sufficient to substantially extinguish combustion of the at least one solid propellant grain, with at least a portion of the at least one solid propellant grain remaining. 24. A method for extinguishing a solid propellant undergoing combustion within a pressure vessel of a propulsion system, comprising: providing a plurality of valves in communication with the pressure vessel, wherein the plurality of valves comprises at least one valve in communication with a thruster for providing axial thrust and at least two valves in respective communication with thrusters for providing thrust for maneuvering; and opening the plurality of valves to rapidly reduce pressure within the pressure vessel to a degree sufficient to substantially extinguish combustion of the solid propellant. 25. The method of claim 24, wherein providing at least two valves in respective communication with thrusters for providing thrust for maneuvering comprises providing two valves in respective communication with thrusters for providing thrust for pitch control and four thrusters in respective communication with thrusters for providing yaw and roll control. 26. The method of claim 24, wherein providing a plurality of valves comprises providing a plurality of proportional valves. 27. The method of claim 24, wherein opening the plurality of valves comprises opening the plurality of valves to rapidly reduce pressure within the pressure vessel to a degree sufficient to substantially extinguish combustion of the solid propellant, with at least a portion of the solid propellant remaining. 28. A propulsion system for propelling and maneuvering a vehicle, the system comprising: a pressure vessel containing at least one solid propellant charge for generating gases through combustion thereof; at least one valve in communication with the pressure vessel and with a thruster for providing axial thrust for the vehicle by release of combustion gases from the pressure vessel; a plurality of valves in communication with the pressure vessel and respectively in communication with thrusters located and oriented for providing maneuver control for the vehicle, wherein each valve of the plurality is selectively operable to effect at least one of pitch, yaw and roll control of the vehicle through release of combustion gases though a thruster; and wherein the at least one valve and the valves of the plurality are operable to open fully in combination to cause rapid depressurization of the interior of the pressure vessel to substantially extinguish combustion of the at least one solid propellant charge. 29. The propulsion system of claim 28, wherein the at least one valve is controllable to adjust and maintain substantially constant pressure within the pressure vessel during combustion of the at least one solid propellant charge responsive to temperature fluctuations. 30. The propulsion system of claim 28, wherein the at least one valve and the valves of the plurality are each proportional valves. 31. The propulsion system of claim 28, wherein the at least one solid propellant charge comprises a plurality of solid propellant charges mutually separated by a flame-inhibiting barrier. 32. The propulsion system of claim 31, further comprising at least one igniter separately associated with each solid propellant charge of the plurality. 33. The propulsion system of claim 28, further comprising at least one igniter grain associated with the at least one solid propellant charge. 34. The propulsion system of claim 33, wherein the at least one igniter grain comprises a plurality of separately actuable igniter grains. 35. The propulsion system of claim 28, wherein the at least one valve and the valves of the plurality are operable to open frilly in combination to cause rapid depressurization of the interior of the pressure vessel to substantially extinguish combustion of the at least one solid propellant charge, with at least a portion of the at least one solid propellant charge remaining. 36. A solid propellant dual phase rocket motor comprising: a pressure vessel; a first solid pulse grain disposed within the pressure vessel and having at least one pulse igniter associated therewith; at least another solid pulse grain disposed within the pressure vessel, separated from the first pulse grain by a flame-inhibiting barrier and having at least one pulse igniter associated therewith; and a plurality of selectively operable proportional valves in communication with the pressure vessel, configured for selectively releasing gases generated by combustion of a solid propellant of either the first solid pulse grain or the at least another solid pulse grain within the pressure vessel, and having thrusters associated therewith. 37. A rocket motor, comprising: a pressure vessel; a solid propellant charge disposed within the pressure vessel for generating combustion gases; a selectively operable axial thrust valve for release of the combustion gases from the pressure vessel to directly provide axial thrust; and a plurality of selectively operable maneuver control valves for release of the combustion gases from the pressure vessel, wherein the axial thrust valve and the plurality of maneuver control valves are configured to effect a rapid depressurization of the pressure vessel during combustion of the solid propellant charge to substantially extinguish combustion thereof when the axial thrust valve and the plurality of maneuver control valves are fully open. 38. The rocket motor of claim 37, wherein the solid propellant charge exhibits the lowest possible steady state burn rate when the axial thrust valve is fully open and the plurality of maneuver control valves are fully closed. 39. The rocket motor of claim 37, wherein the axial thrust valve and the plurality of maneuver control valves comprise proportional valves. 40. The rocket motor of claim 37, wherein the axial thrust valve is configured for modulation of a flow area therethrough to compensate for temperature effects to provide substantially constant axial thrust. 41. The rocket motor of claim 37, further including: at least one additional solid propellant charge disposed within the pressure vessel and separated from the solid propellant charge by a flame-inhibiting barrier; and at least one pulse igniter associated with the at least one additional solid propellant charge. 42. The rocket motor of claim 37, further including: a source of flowable oxidizer; and a control valve for selectively controlling flow of the flowable oxidizer to the pressure vessel. 43. The rocket motor of claim 42, further including: a source of ignition fluid; and a control valve for selectively controlling flow of the ignition fluid to the pressure vessel. 44. The rocket motor of claim 37, wherein the axial thrust valve and the plurality of maneuver control valves are configured to effect a rapid depressurization of the pressure vessel during combustion of the solid propellant charge to substantially extinguish combustion thereof, with at least a portion of the solid propellant charge remaining, when the axial thrust valve and the plurality of maneuver control valves are fully open. 45. A propulsion system, comprising: a pressure vessel containing a propellant; at least one axial thrust valve in communication with the pressure vessel and configured for selectively releasing gases generated by combustion of the propellant within the pressure vessel to directly provide axial thrust; and at least one maneuver control valve in communication with the pressure vessel and configured for selectively releasing gases generated by combustion of the propellant within the pressure vessel to provide thrust for maneuvering, wherein the pressure vessel, the at least one axial thrust valve, and the at least one maneuver control valve are disposed within a common housing. 46. A rocket motor, comprising: a pressure vessel; a solid propellant charge disposed within the pressure vessel for generating combustion gases; a selectively operable axial thrust valve for release of the combustion gases from the pressure vessel to directly provide axial thrust; and a plurality of selectively operable maneuver control valves for release of the combustion gases from the pressure vessel, wherein the axial thrust valve is configured for modulation of a flow area therethrough to compensate for temperature effects to provide substantially constant axial thrust.

이 특허에 인용된 특허 (18)

이 특허를 인용한 특허 피인용횟수: 12

이 특허와 함께 이용한 콘텐츠

IPC 상위 출원인

내보내기

상세정보
내보내기 구분	파일저장 인쇄 메일전송
구성항목	관리번호, 국가코드, 자료구분, 상태, 출원번호, 출원일자, 공개번호, 공개일자, 등록번호, 등록일자, 발명명칭(한글), 발명명칭(영문), 출원인(한글), 출원인(영문), 출원인코드, 대표IPC 관리번호, 국가코드, 자료구분, 상태, 출원번호, 출원일자, 공개번호, 공개일자, 공고번호, 공고일자, 등록번호, 등록일자, 발명명칭(한글), 발명명칭(영문), 출원인(한글), 출원인(영문), 출원인코드, 대표출원인, 출원인국적, 출원인주소, 발명자, 발명자E, 발명자코드, 발명자주소, 발명자 우편번호, 발명자국적, 대표IPC, IPC코드, 요약, 미국특허분류, 대리인주소, 대리인코드, 대리인(한글), 대리인(영문), 국제공개일자, 국제공개번호, 국제출원일자, 국제출원번호, 우선권, 우선권주장일, 우선권국가, 우선권출원번호, 원출원일자, 원출원번호, 지정국, Citing Patents, Cited Patents
저장형식	Text(ASCII format) Excel format PIAS분석(.xls)
메일정보	받는사람 (필수) @ 보내는사람 (선택) @ 제목 내용 KISTI 검색결과 이메일 서비스
안내	> 총 건의 자료가 검색되었습니다. > 다운받으실 자료의 인덱스를 입력하세요. (1-10,000) > 검색결과의 순서대로 최대 10,000건 까지 다운로드가 가능합니다. > 데이타가 많을 경우 속도가 느려질 수 있습니다.(최대 2~3분 소요) > 다운로드 파일은 UTF-8 형태로 저장됩니다. 파일의 내용이 제대로 보이지 않을실 때는 웹브라우저 상단의 보기 -> 인코딩 -> 자동선택 여부를 확인하십시오 > ~ > Text(ASCII format) Excel format

과학기술 지식인프라 ScienceON

ScienceON Chatbot

특허 상세정보

Steerable, intermittently operable rocket propulsion system

초록
▼

대표
청구항
▼

이 특허에 인용된 특허 (18)

이 특허를 인용한 특허 피인용횟수: 12

이 특허와 함께 이용한 콘텐츠

IPC 상위 출원인

상세정보조회

원문조회

IPC 상세정보(version : 201201)

연구과제 성과물(0)

참여연구원의 다른 문헌(0)

처리중입니다.

잠시만 기다려주세요.

ScienceON Chatbot

특허 상세정보

Steerable, intermittently operable rocket propulsion system

초록 ▼

대표청구항 ▼

이 특허에 인용된 특허 (18)

이 특허를 인용한 특허 피인용횟수: 12

이 특허와 함께 이용한 콘텐츠

IPC 상위 출원인

상세정보조회

원문조회

IPC 상세정보(version : 201201)

연구과제 성과물(0)

참여연구원의 다른 문헌(0)

처리중입니다.

잠시만 기다려주세요.

초록
▼

대표
청구항
▼