[특허]Multi-stage space launch systems with reusable thrust augmentation and associated methods

The Boeing Company

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특허 상세정보

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Multi-stage space launch systems with reusable thrust augmentation and associated methods

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64G-001/00 B64G-005/00 B64G-001/58 B64G-001/62 B64G-001/64 B64G-001/40 B64G-001/36
출원번호	US-0219818 (2014-03-19)
등록번호	US-9457918 (2016-10-04)
발명자 / 주소	Hand, Michael Leslie
출원인 / 주소	The Boeing Company
대리인 / 주소	DASCENZO Intellectual Property Law, P.C.
인용정보	피인용 횟수 : 2 인용 특허 : 16

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Systems and methods for launching space vehicles into outer space are disclosed. Systems include a launch vehicle with at least two stages. A thrust augmentation stage provides thrust during an initial portion of a launch trajectory. A first stage provides thrust during the initial portion and during a second portion of the launch trajectory. In some systems, the thrust augmentation stage is reusable with a distinct first stage. In some systems, the thrust augmentation stage defines a central bore, through which the first stage extends for initial launch...

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1. A multi-stage space launch system for launching a space vehicle into outer space, the multi-stage space launch system comprising: a launch vehicle configured to operatively support a space vehicle for placement in outer space, wherein the launch vehicle includes at least two stages including: a thrust augmentation stage configured to provide thrust for an initial portion of a launch trajectory, wherein the thrust augmentation stage includes a plurality of shear cones positioned at an aft portion of the thrust augmentation stage; anda first stage configured to be selectively coupled to and decoupled from the thrust augmentation stage and further configured to provide thrust during the initial portion and during a second portion of the launch trajectory following the initial portion of the launch trajectory; anda land-based landing structure configured to selectively mate with the thrust augmentation stage following a launch when the thrust augmentation stage returns to Earth, wherein the land-based landing structure includes a plurality of pins configured to mate with the plurality of shear cones;wherein the thrust augmentation stage is configured to be selectively decoupled from the first stage during the launch trajectory and further configured for controlled landing following separation from the first stage; andwherein the thrust augmentation stage is configured to mate with the land-based landing structure following the launch when the thrust augmentation stage returns to Earth. 2. The multi-stage space launch system of claim 1, wherein the launch vehicle is configured to launch vertically, and wherein the thrust augmentation stage is configured to land vertically on Earth following separation from the first stage. 3. The multi-stage space launch system of claim 1, wherein the thrust augmentation stage is configured to utilize the same source of thrust that is used during the initial portion of the launch trajectory to return to and land on Earth. 4. The multi-stage space launch system of claim 1, wherein the thrust augmentation stage includes a body that defines a central bore, and wherein the first stage extends through the central bore for launch of the launch vehicle. 5. The multi-stage space launch system of claim 4, wherein the launch vehicle has a longitudinal axis, and wherein the central bore is coaxial with the longitudinal axis. 6. The multi-stage space launch system of claim 4, wherein the central bore extends completely through the thrust augmentation stage. 7. The multi-stage space launch system of claim 4, wherein the thrust augmentation stage and the first stage collectively define a guide track at an interface between the thrust augmentation stage and the first stage when the thrust augmentation stage and the first stage are operatively coupled together, wherein the guide track is configured to operatively constrain longitudinal translation of the first stage relative to the thrust augmentation stage when the first stage is being decoupled from the thrust augmentation stage during launch. 8. The multi-stage space launch system of claim 7, wherein the guide track includes at least one channel and at least one rail configured to longitudinally translate within the at least one channel. 9. The multi-stage space launch system of claim 8, wherein the at least one rail includes rollers configured to longitudinally roll within the at least one channel, and wherein the rollers are spring biased toward the at least one channel. 10. The multi-stage space launch system of claim 4, wherein the thrust augmentation stage includes interface heat shielding structure at an interface between the thrust augmentation stage and the first stage, wherein the interface heat shielding structure is configured to protect the thrust augmentation stage from heat associated with the first stage during separation of the thrust augmentation stage and the first stage during launch of the launch vehicle;wherein the thrust augmentation stage further includes aft heat shielding structure at the aft portion of the thrust augmentation stage, wherein the aft heat shielding structure is configured to protect the thrust augmentation stage at least from heat generated by the thrust augmentation stage during launch of the launch vehicle; andwherein the aft heat shielding structure is configured to withstand elevated temperatures for a longer period of time than the interface heat shielding structure. 11. The multi-stage space launch system of claim 1, wherein the launch vehicle includes a coupling mechanism configured to selectively and operatively couple together the thrust augmentation stage and the first stage for launch of the launch vehicle, wherein the coupling mechanism is further configured to selectively and operatively decouple the thrust augmentation stage from the first stage during the launch trajectory, and wherein the coupling mechanism includes at least one of explosive bolts and separation nuts. 12. The multi-stage space launch system of claim 1, wherein the thrust augmentation stage is configured to be powered by a liquid fuel. 13. The multi-stage space launch system of claim 1, further comprising: a control system configured to actively control a controlled descent of the thrust augmentation stage to land vertically on Earth following the initial portion of the launch trajectory. 14. The multi-stage space launch system of claim 13, further comprising: a launch facility, from which the launch vehicle is configured to launch;wherein the control system is configured to control the controlled descent of the thrust augmentation stage to the launch facility following the initial portion of the launch trajectory. 15. The multi-stage space launch system of claim 13, wherein the control system is configured to control the controlled descent of the thrust augmentation stage to Earth following the initial portion of the launch trajectory to within 1000 meters from a position from which the launch vehicle was launched. 16. The multi-stage space launch system of claim 1, further comprising: a control system configured to automatically control a controlled descent of the thrust augmentation stage to land vertically on Earth following the initial portion of the launch trajectory. 17. A method of launching a space vehicle into outer space, the method comprising: providing the multi-stage space launch system of claim 1;powering the thrust augmentation stage of the launch vehicle during the initial portion of the launch trajectory to provide thrust to the launch vehicle;following the initial portion of the launch trajectory, separating the first stage of the launch vehicle from the thrust augmentation stage;powering the first stage of the launch vehicle during the initial portion and the second portion of the launch trajectory following the initial portion of the launch trajectory to provide thrust to the launch vehicle; andcontrolling a controlled descent of the thrust augmentation stage to Earth following separation of the thrust augmentation stage from the first stage. 18. The method of claim 17, further comprising: retrieving and reusing the thrust augmentation stage with a distinct first stage to define a distinct launch vehicle for a subsequent launch of a distinct space vehicle into outer space. 19. A multi-stage space launch system for launching a space vehicle into outer space, the multi-stage space launch system comprising: a launch vehicle configured to operatively support a space vehicle for placement in outer space, wherein the launch vehicle includes at least two stages including: a thrust augmentation stage configured to provide thrust for an initial portion of a launch trajectory, wherein the thrust augmentation stage includes a body that defines a central bore; anda first stage configured to be selectively coupled to and decoupled from the thrust augmentation stage and further configured to provide thrust during the initial portion and during a second portion of the launch trajectory following the initial portion of the launch trajectory, wherein the first stage extends through the central bore for launch of the launch vehicle;wherein the thrust augmentation stage is configured to be selectively decoupled from the first stage during the launch trajectory and further configured for controlled landing following separation from the first stage; andwherein the thrust augmentation stage and the first stage collectively define a guide track at an interface between the thrust augmentation stage and the first stage when the thrust augmentation stage and the first stage are operatively coupled together, wherein the guide track is configured to operatively constrain longitudinal translation of the first stage relative to the thrust augmentation stage when the first stage is being decoupled from the thrust augmentation stage during launch. 20. The multi-stage space launch system of claim 19, wherein the launch vehicle is configured to launch vertically, and wherein the thrust augmentation stage is configured to land vertically on Earth following separation from the first stage. 21. The multi-stage space launch system of claim 19, wherein the thrust augmentation stage is configured to utilize the same source of thrust that is used during the initial portion of the launch trajectory to return to and land on Earth. 22. The multi-stage space launch system of claim 19, further comprising: a land-based landing structure configured to selectively mate with the thrust augmentation stage following the launch when the thrust augmentation stage returns to Earth;wherein the thrust augmentation stage is configured to mate with the land-based landing structure following the launch when the thrust augmentation stage returns to Earth. 23. The multi-stage space launch system of claim 22, wherein the thrust augmentation stage includes a plurality of shear cones positioned at an aft portion of the thrust augmentation stage; andwherein the land-based landing structure includes a plurality of pins configured to mate with the plurality of shear cones. 24. The multi-stage space launch system of claim 19, wherein the launch vehicle has a longitudinal axis, and wherein the central bore is coaxial with the longitudinal axis. 25. The multi-stage space launch system of claim 19, wherein the central bore extends completely through the thrust augmentation stage. 26. The multi-stage space launch system of claim 19, wherein the guide track includes at least one channel and at least one rail configured to longitudinally translate within the at least one channel. 27. The multi-stage space launch system of claim 26, wherein the at least one rail includes rollers configured to longitudinally roll within the at least one channel, and wherein the rollers are spring biased toward the at least one channel. 28. The multi-stage space launch system of claim 19, wherein the thrust augmentation stage includes interface heat shielding structure at an interface between the thrust augmentation stage and the first stage, wherein the interface heat shielding structure is configured to protect the thrust augmentation stage from heat associated with the first stage during separation of the thrust augmentation stage and the first stage during launch of the launch vehicle;wherein the thrust augmentation stage further includes aft heat shielding structure at the aft portion of the thrust augmentation stage, wherein the aft heat shielding structure is configured to protect the thrust augmentation stage at least from heat generated by the thrust augmentation stage during launch of the launch vehicle; andwherein the aft heat shielding structure is configured to withstand elevated temperatures for a longer period of time than the interface heat shielding structure. 29. The multi-stage space launch system of claim 19, wherein the launch vehicle includes a coupling mechanism configured to selectively and operatively couple together the thrust augmentation stage and the first stage for launch of the launch vehicle, wherein the coupling mechanism is further configured to selectively and operatively decouple the thrust augmentation stage from the first stage during the launch trajectory, and wherein the coupling mechanism includes at least one of explosive bolts and separation nuts. 30. The multi-stage space launch system of claim 19, wherein the thrust augmentation stage is configured to be powered by a liquid fuel. 31. The multi-stage space launch system of claim 19, further comprising: a control system configured to actively control a controlled descent of the thrust augmentation stage to land vertically on Earth following the initial portion of the launch trajectory. 32. The multi-stage space launch system of claim 31, further comprising: a launch facility, from which the launch vehicle is configured to launch;wherein the control system is configured to control the controlled descent of the thrust augmentation stage to the launch facility following the initial portion of the launch trajectory. 33. The multi-stage space launch system of claim 31, wherein the control system is configured to control the controlled descent of the thrust augmentation stage to Earth following the initial portion of the launch trajectory to within 1000 meters from a position from which the launch vehicle was launched. 34. The multi-stage space launch system of claim 19, further comprising: a control system configured to automatically control a controlled descent of the thrust augmentation stage to land vertically on Earth following the initial portion of the launch trajectory. 35. A method of launching a space vehicle into outer space, the method comprising: providing the multi-stage space launch system of claim 19;powering the thrust augmentation stage of the launch vehicle during the initial portion of the launch trajectory to provide thrust to the launch vehicle;following the initial portion of the launch trajectory, separating the first stage of the launch vehicle from the thrust augmentation stage;powering the first stage of the launch vehicle during the initial portion and the second portion of the launch trajectory following the initial portion of the launch trajectory to provide thrust to the launch vehicle; andcontrolling a controlled descent of the thrust augmentation stage to Earth following separation of the thrust augmentation stage from the first stage. 36. The method of claim 35, further comprising: retrieving and reusing the thrust augmentation stage with a distinct first stage to define a distinct launch vehicle for a subsequent launch of a distinct space vehicle into outer space.

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Multi-stage space launch systems with reusable thrust augmentation and associated methods

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