[특허]Propulsion unit for reusable launch vehicle

AIRBUS DEFENCE & SPACE SAS

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특허 상세정보

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Propulsion unit for reusable launch vehicle

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64G-001/00 B64G-001/40 B64G-001/14 B64G-005/00 F02K-009/97 B64F-005/50 B64G-001/64
출원번호	US-0901328 (2014-07-04)
등록번호	US-9981757 (2018-05-29)
우선권정보	FR-13 56695 (2013-07-08)
국제출원번호	PCT/EP2014/064282 (2014-07-04)
국제공개번호	WO2015/004010 (2015-01-15)
발명자 / 주소	Coraboeuf, Yohann Dutheil, Jean-Philippe
출원인 / 주소	AIRBUS DEFENCE & SPACE SAS
대리인 / 주소	Perman & Green LLP
인용정보	피인용 횟수 : 0 인용 특허 : 39

초록
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The invention relates to a propulsion unit for a reusable launch vehicle including a rocket engine supported by a cradle. According to the invention, the cradle includes at least three attachment elements for assembling the unit on the structure of the vehicle to which the unit is to be connected, the at least three attachment elements defining a plane for removing the unit, and in which the unit includes one or more fluid and/or electric links of the engine, each one of the links including a free end to be assembled with a corresponding circuit for supp...

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청구항
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1. A thrust unit for a reusable launch vehicle comprising a rocket engine supported by a cradle, wherein: said cradle comprises at least three fixing members for the assembly of said thrust unit on a structure of said reusable launch vehicle;said at least three fixing members defining a plane for dismantling said thrust unit; andsaid thrust unit further comprises one or more links, the one or more links comprising one or more of fluid links and electrical links, of said rocket engine, each of the one or more links comprising a free end configured for coupling with a corresponding circuit for supplying the reusable launch vehicle, a tip of at least some of said free ends is contained in said dismantling plane. 2. The thrust unit as claimed in claim 1, wherein the tip of the free end of each of said links is contained in said dismantling plane. 3. The thrust unit as claimed in claim 1, wherein said thrust unit further comprises at least one anchoring member for blocking the rotation of the rocket engine in respect of said cradle, said at least one anchoring member being connected firstly to said rocket engine and secondly to a corresponding anchoring point on said cradle. 4. The thrust unit as claimed in claim 1, wherein said cradle is extended, exhibiting in a transverse dimension of said cradle a front face and a rear face, said front face being configured for assembly with said rocket engine, said front face defining a front plane of said cradle containing at least one section of said front face, said at least one section exhibiting dimensions allowing the fixing of anchoring members of said rocket engine. 5. The thrust unit as claimed in claim 4, wherein said cradle exhibits a shape chosen from the group comprising a disc shape, a cross shape, an A shape, an H shape, a Y shape, a T shape. 6. The thrust unit as claimed in claim 4, wherein said rear face defines a rear plane of said cradle, so that said front and rear planes are parallel or substantially parallel. 7. The thrust unit as claimed in claim 3, wherein said cradle comprising at least two different limbs and at least two anchoring members, each of said anchoring members is connected to a different limb of said cradle. 8. A launch vehicle equipped with the thrust unit according to claim 1. 9. A handling assembly for the assembly and dismantling of the thrust unit according to claim 1 and the transportation of the thrust unit, wherein the handling assembly comprises; two longitudinal rails, each comprising a first portion of guide rails to be assembled on the inside to the structure of the reusable launch vehicle and a second guide rail portion integral with a chassis;said chassis being mobile, at least so as to be vertically displaced, such that said guide rail portions of the same longitudinal rail are configured to be placed end to end to form two side longitudinal guide rails, anda carriage movable in a straight line along said longitudinal rails, said carriage comprising two pairs of detachable support arms, each of said arms being for assembly to a different limb of said cradle to support said thrust unit after said thrust unit has been dismantled from the structure of said reusable launch vehicle. 10. The handling assembly as claimed in claim 9, wherein said carriage further comprises two longitudinal structural parts equipped with running gear suitable for ensuring the movement of said carriage along said guide rails, said longitudinal parts being spaced laterally relative to one another, being connected to one another by a mechanical reinforcement part, preventing any gap between said parts when said carriage supports said thrust unit, said carriage thereby defining a fork capable of receiving between said longitudinal parts the rocket engine of the thrust unit when said carriage is introduced into said reusable launch vehicle. 11. The handling assembly as claimed in claim 9, wherein said chassis is mobile so as to be vertically displaced to ensure that said guide rail portions are in view. 12. The handling assembly as claimed in claim 11, wherein said chassis is mounted on an articulated structure so as to be displaced between a low rest position and a high service position, said articulated structure being mobile. 13. The handling assembly as claimed in claim 9, wherein said chassis has a transverse cross section in the shape of a U, to receive said carriage without any risk of damaging said thrust unit. 14. The handling assembly as claimed in claim 9, wherein said cradle being in the shape of a cross or also an X, said mobile carriage comprises two pairs of detachable support arms, each arm being for assembly on a different limb of this cradle, to support said thrust unit after said thrust unit has been dismantled from the structure of the reusable launch vehicle. 15. The handling assembly as claimed in claim 14, further comprising fixing parts for the end of said support arms on said cradle limbs. 16. The handling assembly as claimed in claim 14, wherein at least one support arm of said pairs comprises a main connecting rod for connecting a limb of said cradle to said carriage and a secondary connecting rod, referred to as the transverse connecting rod, connecting said main connecting rod to said carriage in a slanting manner, so as to block the rotation of said cradle in respect of said carriage.

이 특허에 인용된 특허 (39)

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특허 상세정보

Propulsion unit for reusable launch vehicle

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이 특허에 인용된 특허 (39)

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Propulsion unit for reusable launch vehicle

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이 특허에 인용된 특허 (39)

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IPC 상세정보(version : 201201)

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