[특허]Reusable module for launcher

ASTRIUM SAS

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특허 상세정보

MyON담기

내보내기 페이스북 공유 트위터 공유 카카오톡 공유

Reusable module for launcher

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64G-001/00 B64G-001/40
출원번호	US-0141162 (2009-12-18)
등록번호	US-9174749 (2015-11-03)
우선권정보	FR-08 58940 (2008-12-22)
국제출원번호	PCT/EP2009/067549 (2009-12-18)
§371/§102 date	20110824 (20110824)
국제공개번호	WO2010/072681 (2010-07-01)
발명자 / 주소	Prampolini, Marco Gogdet, Olivier
출원인 / 주소	ASTRIUM SAS
대리인 / 주소	Oblon, McClelland, Maier & Neustadt, L.L.P.
인용정보	피인용 횟수 : 3 인용 특허 : 9

초록
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A propulsion module configured to launch a craft into space including a recoverable module and a non-recovered part, which is secured to the recoverable module at launch. The recoverable module includes a propulsive system to launch the craft, systems for command and control of the propulsive system, a subsonic flight propulsion motor, airfoils for the subsonic flight, a landing gear, and a braking parachute. The recoverable module is installed in a lower position of the craft when the craft is in the launch position. The non-recovered part includes at least one tank to feed the propulsive system. The recoverable module and the non-recovered part are configured to be separated when the propulsion module reaches a given altitude, and the recoverable module is capable of landing in a controlled fashion after a coasting flight, for example for a return to the launch site.

대표
청구항
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1. A recoverable module for a propulsion module configured to launch a craft into space, said craft comprising at least one stage, the recoverable module being securable to a non-recovered part that is not recovered at launch, and the recoverable module being configured to be installed in a lower position of the at least one stage, the recoverable module comprising: a propulsive system configured for launch of the craft;systems for command and control of the propulsive system;a subsonic flight propulsion motor;airfoils for the subsonic flight;a landing gear; anda braking parachute, whereinthe propulsive system is fed by at least one tank comprised in the non-recovered part, and the subsonic flight propulsion motor is distinct from the propulsive system,the recoverable module and the non-recovered part being configured to be separated when the propulsion module reaches a given altitude, andthe recoverable module being configured to land in a controlled fashion after a coasting flight, or to return to the launch site. 2. A recoverable module according to claim 1, in which the airfoils are formed by at least a part of a tail unit of the craft. 3. A recoverable module according to claim 2, in which the tail unit comprises at least two fins. 4. A recoverable module according to claim 3, comprising at least three fins of which at least two fins have a modifiable shape to form the airfoils. 5. A recoverable module according to claim 4, in which each of the at least two modifiable fins includes a first part attached to a case of the module and a second part installed so as to be movable on the first part, and in which displacement of the second part relative to the first part is obtained by at least one electric or hydraulic motor. 6. A recoverable module according to claim 3, in which each of two modifiable fins includes a first part attached to a case of the module and a second part installed so as to be movable on the first part, and in which displacement of the second part relative to the first part is obtained by at least one electric or hydraulic motor. 7. A recoverable module according to claim 1, comprising a central channel having an axis that is shared with an axis of the recoverable module, the subsonic flight propulsion motor being installed in the central channel, together with the braking parachute enclosed in a canister, and the canister being installed in an exhaust duct at a rear of the subsonic flight propulsion motor. 8. A recoverable module according to claim 1, in which the subsonic flight propulsion motor is an air-breathing motor fed with fuel by tanks installed in fins of a tail unit. 9. A recoverable module according to claim 1, in which the recoverable module has a blunt nose, to increase a supersonic wave drag during an initial phase of atmospheric re-entry, and to contribute to deceleration of the recoverable module. 10. A propulsion module configured to launch a craft into space, the propulsion module comprising at least one stage of the craft, and the propulsion module comprising a recoverable module according to claim 1 and a part configured to not be recovered comprising at least one tank to feed the propulsive system. 11. A craft of launcher type fitted with a propulsion module according to claim 10, comprising at least two stages, one stage formed by the propulsion module and a stage supporting a payload, the at least two stages being separable. 12. A craft of launcher type according to claim 11, in which the craft of launcher type ranges from a nanolauncher to a super heavy launcher type. 13. A craft of launcher type according to claim 12, in which the propulsion module forms a lower stage of the craft of launcher type or one of upper stages of the craft of launcher type. 14. A method of recovery of the recoverable module according to claim 1, comprising: a) separation of the recoverable module and the non-recovered part;b) freefall of the recoverable module;c) deployment of the braking parachute when a speed of the recoverable module becomes subsonic;d) start-up of the subsonic flight propulsion motor, and positioning of the airfoils during the deployment of the braking parachute;e) jettisoning of the braking parachute;f) starting a flare;g) return coasting; andh) landing. 15. A method according to claim 14, in which, during the separation a), separation of the recoverable module and of the non-recovered part takes place in a direction that is roughly orthogonal to the trajectory plane. 16. A method according to claim 14, in which the start-up d) takes place at low dynamic pressure, of order of 400 Pa, to facilitate variation of shape of the airfoil, and to have a time required to start the propulsion motor. 17. A method according to claim 14, wherein the starting the flare includes starting the flare to horizontally orientate the recoverable module. 18. A recoverable module for a propulsion module configured to launch a craft into space, said craft comprising at least one stage, the recoverable module being securable to a non-recovered part that is not recovered at launch, and the recoverable module being configured to be installed in a lower position of the at least one stage, the recoverable module comprising: a propulsive system configured for launch of the craft;systems for command and control of the propulsive system;a subsonic flight propulsion motor;airfoils for the subsonic flight;a landing gear;a braking parachute; anda central channel having an axis that is shared with an axis of the recoverable module, the subsonic flight propulsion motor being installed in the central channel, together with the braking parachute enclosed in a canister, and the canister being installed in an exhaust duct at a rear of the subsonic flight propulsion motor, whereinthe non-recovered part comprising at least one tank to feed the propulsive system,the recoverable module and the non-recovered part being configured to be separated when the propulsion module reaches a given altitude, andthe recoverable module being configured to land in a controlled fashion after a coasting flight, or to return to the launch site. 19. A recoverable module for a propulsion module configured to launch a craft into space, said craft comprising at least one stage, the recoverable module being securable to a non-recovered part that is not recovered at launch, and the recoverable module being configured to be installed in a lower position of the at least one stage, the recoverable module comprising: a propulsive system configured for launch of the craft;systems for command and control of the propulsive system;a subsonic flight propulsion motor;airfoils for the subsonic flight;a landing gear; anda braking parachute, whereinthe subsonic flight propulsion motor is an air-breathing motor fed with fuel by tanks installed in fins of a tail unit,the non-recovered part comprising at least one tank to feed the propulsive system,the recoverable module and the non-recovered part being configured to be separated when the propulsion module reaches a given altitude, andthe recoverable module being configured to land in a controlled fashion after a coasting flight, or to return to the launch site.

이 특허에 인용된 특허 (9)

이 특허를 인용한 특허 피인용횟수: 3

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특허 상세정보

Reusable module for launcher

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이 특허에 인용된 특허 (9)

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Reusable module for launcher

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이 특허에 인용된 특허 (9)

이 특허를 인용한 특허 피인용횟수: 3

IPC 상위 출원인

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IPC 상세정보(version : 201201)

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