[특허]Hybrid-LO2-LH2 low cost launch vehicle

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Hybrid-LO2-LH2 low cost launch vehicle

국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F02K-009/28
미국특허분류(USC)	60/204 ; 60/251 ; 60/219 ; 60/256 ; 60/257
출원번호	US-0701938 (1996-08-23)
발명자 / 주소	Jones Herbert Stephen Williams Harry Phillip
대리인 / 주소	Meise
인용정보	피인용 횟수 : 24 인용 특허 : 0

초록
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A low-cost rocket or thruster has a low-cost propellant injector, in which fluid fuel and oxidizer are injected into a combustion chamber. The walls of the combustion chamber are protected from the high temperatures of the combustion by a grain of solid propellant, the surface of which tends to melt andor vaporize in the presence of combustion temperatures, and thereby protects the walls of the chamber. The low-cost propellant injector may not mix the fluid fuel and oxidizer effectively, so that pockets of noncombusted gas may occur within the chamber. The ratio of fluid fuel and oxidizer is selected to be slightly oxidizer-rich, so that any pockets of unburned gas tend to be oxygen-rich. When the pockets come into contact with the solid fuel, the excess oxygen combusts with the gaseous solid fuel, and when the mixture is near stoichiometric, the fluid fuel combusts. Thus, an inexpensive bipropellant injector together with a solid fuel grain simultaneously allows use of solid fuel instead of insulation to protect the combustion chamber walls, and the combustion is stabilized by the presence of the solid fuel. Ideally, the amount of excess oxidizer should be sufficient to completely combust the solid fuel. The preferred propellants are LO2 and LH2, and the preferred solid fuel is HTPB.

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[ What is claimed is:] [1.] A rocket engine, comprising:a source of liquid oxidizer;a source of combustible fluid propellant;a chamber with walls, said chamber being coupled to a combustion product ejection port;a propellant injector coupled to said source of combustible fluid propellant, for injecting said propellant into said chamber at a rate;an oxidizer injector coupled to said source of liquid oxidizer and to said chamber, for injecting oxidizer into said chamber at a rate no less than a rate sufficient for complete combustion of said combustible fluid propellant, as a result of which said propellant combusts within said chamber to produce reaction products which leave said chamber through said ejection port, for thereby creating thrust; anda solid propellant liner within said chamber, said solid propellant liner becoming gaseous in response to combustion of propellant in said chamber, thereby combusting with any excess oxidizer to enhance said thrust;said combustion of said fluid propellant with said oxidizer providing a greater proportion of said thrust than said combustion of said solid propellant with said excess oxidizer. [13.] A method for operating a rocket engine which includes a combustible fluid propellant injector, a fluid oxidizer injector, and a combustion chamber lined with solid propellant, comprising the steps of:injecting said fluid propellant into said chamber at a selected rate; andinjecting said oxidizer into said chamber at a rate selected so that more oxidizer than is required to completely react with said fluid propellant enters said chamber, whereby said fluid propellant reacts with said oxidizer to produce thrust, and said solid propellant reacts with excess oxidizer to create additional thrust, and so that said combustion of said fluid propellant with said oxidizer provides a greater proportion of the thrust than said combustion of said solid propellant with said excess oxidizer. A method according to claim 13, wherein said step of injecting said fluid oxidizer includes the step of injecting oxygen. A method according to claim 13, wherein said step of injecting said fluid propellant includes the step of injecting hydrogen. A multistage rocket, at least one stage of which comprises:(a) a source of liquid oxidizer;(b) a source of combustible fluid propellant;(c) a chamber with walls, said chamber being coupled to a combustion product ejection port;(d) a propellant injector coupled to said source of combustible fluid propellant, for injecting said propellant into said chamber at a rate;(e) an oxidizer injector coupled to said source of liquid oxidizer and to said chamber, for injecting oxidizer into said chamber at a rate no less than a rate sufficient for complete combustion of said propellant, as a result of which said propellant combusts within said chamber and leaves said chamber through said ejection port, for thereby creating thrust, whereby said combustion occurs at a temperature sufficiently high to damage a wall of said chamber during operation of said rocket engine; and(f) a solid propellant liner within said chamber, said solid propellant liner becoming gaseous in response to combustion of propellant in said chamber, thereby absorbing heat and protecting said wall from said temperature, and in the process of becoming gaseous, combusting with any excess oxidizer to enhance said thrust in a lesser proportion of the total thrust than said thrust generated by combustion of said fluid propellant.

이 특허를 인용한 특허 피인용횟수: 24

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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)
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특허 상세정보

Hybrid-LO2-LH2 low cost launch vehicle

초록
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대표
청구항
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이 특허를 인용한 특허 피인용횟수: 24

IPC 상위 출원인

상세정보조회

원문조회

IPC 상세정보(version : 201201)

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Hybrid-LO2-LH2 low cost launch vehicle

초록 ▼

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이 특허를 인용한 특허 피인용횟수: 24

IPC 상위 출원인

상세정보조회

원문조회

IPC 상세정보(version : 201201)

연구과제 성과물(0)

참여연구원의 다른 문헌(0)

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