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1. 发明申请

US20120325957A1 ULTRA-RAPID AIR VEHICLE AND RELATED METHOD FOR AERIAL LOCOMOTION 有权
标题翻译：超快速空气车辆及其相关方法
公开(公告)号：US20120325957A1
公开(公告)日：2012-12-27
申请号：US13516878
申请日：2010-12-20
申请人： Marco Prampolini , Yohann Coraboeuf
发明人： Marco Prampolini , Yohann Coraboeuf
IPC分类号： B64C30/00
CPC分类号： B64C30/00 , B64C3/10 , B64C5/08 , B64C5/10 , B64C23/076 , B64D27/023 , B64D27/20 , B64D27/26 , B64D2027/026 , B64G1/14 , Y02T50/12 , Y02T50/164 , Y02T50/44 , Y02T90/44
摘要： The invention concerns an ultra-rapid air vehicle together with a method of aerial locomotion by means of an ultra-rapid air vehicle, where the air vehicle is propelled by a system of motors formed of turbojets (TB1, TB2), ramjets (ST1, ST2) and a rocket motor which can be made streamlined to reduce the drag of the base during the cruise phase, and where the vehicle has a gothic delta wing (A) fitted with moving fins (a1, a2) at both outer ends of the trailing edge of the delta wing (A).
摘要翻译：本发明涉及一种超快速空中飞行器以及超快速空中飞行器的空中移动方法，其中，空中交通工具由涡轮喷气发动机（TB1，TB2），冲击器（ST1， ST2）和火箭发动机，其可以被制成流线型以减少在巡航阶段期间底座的阻力，并且其中车辆具有装配有活动翅片（a1，a2）的哥特式三角翼（A），其在两个外端处三角翼的后缘（A）。

2. 发明授权

US09079661B2 Ultra-rapid air vehicle and related method for aerial locomotion 有权
标题翻译：超快速飞行器及相关方法进行航空运动
公开(公告)号：US09079661B2
公开(公告)日：2015-07-14
申请号：US13516878
申请日：2010-12-20
申请人： Marco Prampolini , Yohann Coraboeuf
发明人： Marco Prampolini , Yohann Coraboeuf
IPC分类号： B64C30/00 , B64D27/20 , B64C3/10 , B64C5/08 , B64C5/10 , B64C23/06 , B64G1/14 , B64D27/02
CPC分类号： B64C30/00 , B64C3/10 , B64C5/08 , B64C5/10 , B64C23/076 , B64D27/023 , B64D27/20 , B64D27/26 , B64D2027/026 , B64G1/14 , Y02T50/12 , Y02T50/164 , Y02T50/44 , Y02T90/44
摘要： The invention concerns an ultra-rapid air vehicle together with a method of aerial locomotion by means of an ultra-rapid air vehicle, where the air vehicle is propelled by a system of motors formed of turbojets (TB1, TB2), ramjets (ST1, ST2) and a rocket motor which can be made streamlined to reduce the drag of the base during the cruise phase, and where the vehicle has a gothic delta wing (A) fitted with moving fins (a1, a2) at both outer ends of the trailing edge of the delta wing (A).
摘要翻译：本发明涉及一种超快速空中飞行器以及超快速空中飞行器的空中移动方法，其中，空中交通工具由涡轮喷气发动机（TB1，TB2），冲击器（ST1， ST2）和火箭发动机，其可以被制成流线型以减少在巡航阶段期间底座的阻力，并且其中车辆具有装配有活动翅片（a1，a2）的哥特式三角翼（A），其在两个外端处三角翼的后缘（A）。

3. 发明申请

US20100327108A1 SPACECRAFT AFTERBODY DEVICE 有权
标题翻译：后备装置
公开(公告)号：US20100327108A1
公开(公告)日：2010-12-30
申请号：US12745177
申请日：2008-11-21
申请人： Marco Prampolini
发明人： Marco Prampolini
IPC分类号： B64G1/24 , B64G1/22 , F42B10/00 , B64G1/40 , B64G1/50
CPC分类号： B64G1/14 , F02K9/90 , F42B10/66
摘要： An afterbody device for a spacecraft fitted with at least one rocket engine at the rear of the craft includes at least one movable cover element designed to take a first position, masking and reducing the vehicle's rear drag, where it prolongs the vehicle's fuselage around at least one part of a rocket engine nozzle of the vehicle and extends beyond the rear of the vehicle's fuselage, and to take a second position fully deployed, increasing the vehicle's aerodynamic drag.
摘要翻译：用于在飞行器后部配备有至少一个火箭发动机的航天器的后体装置包括设计成采取第一位置的至少一个可移动盖元件，掩蔽并减少车辆的后阻力，其中至少延长了车辆的机身车辆的火箭发动机喷嘴的一部分并且延伸超出车辆机身的后部，并且进行完全展开的第二位置，增加车辆的空气动力学阻力。

4. 发明授权

US08844876B2 Simplified reusable module for launcher 有权
标题翻译：发射器简易可重用模块
公开(公告)号：US08844876B2
公开(公告)日：2014-09-30
申请号：US13704136
申请日：2011-06-10
申请人： Marco Prampolini
发明人： Marco Prampolini
IPC分类号： B64G1/00 , B64G1/62 , B64G1/40
CPC分类号： B64G1/401 , B64G1/002 , B64G1/40 , B64G1/62
摘要： A recoverable module for a propulsion module configured to launch a craft into space, the recoverable module including a central body, a propulsion system configured to launch the craft, systems for commanding and controlling the propulsion system, at least one propulsion engine in subsonic flight, lift surfaces for the subsonic flight and landing gear, the lift surface including two substantially flat wings fixed with respect to the central body, arranged on either side of the central body of the module, and a stabilizer mounted articulated for rotation on a downstream end of each wing, each stabilizer including at least one pair of lower wing surface and upper wing surface flaps mounted articulated on the stabilizer or any other flap fulfilling a dynamic function.
摘要翻译：一种用于推进模块的可恢复模块，其构造成将飞行器发射到太空中，所述可恢复模块包括中心体，构造成发射飞行器的推进系统，用于命令和控制推进系统的系统，亚音速飞行中的至少一个推进发动机，用于亚音速飞行和起落架的提升表面，提升表面包括布置在模块的中心主体的任一侧上的相对于中心体固定的两个基本平坦的翼，以及安装件，其被铰接以在下游端每个翼，每个稳定器包括至少一对下翼表面和上翼表面翼片，其铰接在稳定器或满足动态功能的任何其它翼片上。

5. 发明申请

US20130087659A1 SIMPLIFIED REUSABLE MODULE FOR LAUNCHER 有权
标题翻译：简化的可重新启动模块
公开(公告)号：US20130087659A1
公开(公告)日：2013-04-11
申请号：US13704136
申请日：2011-06-10
申请人： Marco Prampolini
发明人： Marco Prampolini
IPC分类号： B64G1/40
CPC分类号： B64G1/401 , B64G1/002 , B64G1/40 , B64G1/62
摘要： A recoverable module for a propulsion module configured to launch a craft into space, the recoverable module including a central body, a propulsion system configured to launch the craft, systems for commanding and controlling the propulsion system, at least one propulsion engine in subsonic flight, lift surfaces for the subsonic flight and landing gear, the lift surface including two substantially flat wings fixed with respect to the central body, arranged on either side of the central body of the module, and a stabilizer mounted articulated for rotation on a downstream end of each wing, each stabilizer including at least one pair of lower wing surface and upper wing surface flaps mounted articulated on the stabilizer or any other flap fulfilling a dynamic function.
摘要翻译：一种用于推进模块的可恢复模块，其构造成将飞行器发射到太空中，所述可恢复模块包括中心体，构造成发射飞行器的推进系统，用于命令和控制推进系统的系统，亚音速飞行中的至少一个推进发动机，用于亚音速飞行和起落架的提升表面，提升表面包括布置在模块的中心主体的任一侧上的相对于中心体固定的两个基本平坦的翼，以及安装件，其被铰接以在下游端每个翼，每个稳定器包括至少一对下翼表面和上翼表面翼片，其铰接在稳定器或满足动态功能的任何其它翼片上。

6. 外观设计

USD589867S1 Airplane 有权
公开(公告)号：USD589867S1
公开(公告)日：2009-04-07
申请号：US29297601
申请日：2007-11-14
申请人： Christian Chesne , Robert Abadie-Lahaille , Valéry Auger , Marco Prampolini , Jean Claude Paulat , Jérôme Bertrand
设计人： Christian Chesne , Robert Abadie-Lahaille , Valéry Auger , Marco Prampolini , Jean Claude Paulat , Jérôme Bertrand

7. 发明授权

US09174749B2 Reusable module for launcher 有权
标题翻译：发射器可重复使用的模块
公开(公告)号：US09174749B2
公开(公告)日：2015-11-03
申请号：US13141162
申请日：2009-12-18
申请人： Marco Prampolini , Olivier Gogdet
发明人： Marco Prampolini , Olivier Gogdet
IPC分类号： B64G1/00 , B64G1/40
CPC分类号： B64G1/002 , B64G1/401 , B64G1/402
摘要： 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.
摘要翻译：推进模块，被配置为将飞行器发射到空间中，包括可恢复模块和未恢复部分，其在发射时固定到可恢复模块。可回收模块包括推进系统，用于指挥和控制推进系统的推进系统，亚音速飞行推进电机，亚音速飞行器的翼型，起落架和制动降落伞。当工艺处于发射位置时，可恢复模块安装在工艺的较低位置。未回收部分包括至少一个供给推进系统的罐。当可推动模块达到给定高度时，可恢复模块和未恢复部分被配置为分离，并且可恢复模块能够在惯性飞行之后以受控的方式登陆，例如返回到发射场地。

8. 发明授权

US08604402B2 Spacecraft afterbody device 有权
标题翻译：航天器后身装置
公开(公告)号：US08604402B2
公开(公告)日：2013-12-10
申请号：US12745177
申请日：2008-11-21
申请人： Marco Prampolini
发明人： Marco Prampolini
IPC分类号： F42B10/00
CPC分类号： B64G1/14 , F02K9/90 , F42B10/66
摘要： An afterbody device for a spacecraft fitted with at least one rocket engine at the rear of the craft includes at least one movable cover element designed to take a first position, masking and reducing the vehicle's rear drag, where it prolongs the vehicle's fuselage around at least one part of a rocket engine nozzle of the vehicle and extends beyond the rear of the vehicle's fuselage, and to take a second position fully deployed, increasing the vehicle's aerodynamic drag.
摘要翻译：用于在飞行器后部配备有至少一个火箭发动机的航天器的后体装置包括设计成采取第一位置的至少一个可移动盖元件，掩蔽并减少车辆的后阻力，其中至少延长了车辆的机身车辆的火箭发动机喷嘴的一部分并且延伸超出车辆机身的后部，并且进行完全展开的第二位置，增加车辆的空气动力学阻力。

9. 发明申请

US20110297793A1 REUSABLE MODULE FOR LAUNCHER 有权
标题翻译：可重新启动的模块
公开(公告)号：US20110297793A1
公开(公告)日：2011-12-08
申请号：US13141162
申请日：2009-12-18
申请人： Marco Prampolini , Olivier Gogdet
发明人： Marco Prampolini , Olivier Gogdet
IPC分类号： B64G1/14 , B64G1/62 , B64D37/04 , B64D17/80 , B64D37/02 , B64G1/40 , B64C25/00
CPC分类号： B64G1/002 , B64G1/401 , B64G1/402
摘要： 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.
摘要翻译：推进模块，被配置为将飞行器发射到空间中，包括可恢复模块和未恢复部分，其在发射时固定到可恢复模块。可恢复模块包括推进系统，用于指挥和控制推进系统的推进系统，亚音速飞行推进电机，亚音速飞行器的翼型，起落架和制动降落伞。当工艺处于发射位置时，可恢复模块安装在工艺的较低位置。未回收部分包括至少一个供给推进系统的罐。当可推动模块达到给定高度时，可恢复模块和未恢复部分被配置为分离，并且可恢复模块能够在惯性飞行之后以受控的方式登陆，例如返回到发射场地。

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