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91. 发明申请

US20190168887A1 IN-FLIGHT TRANSFER OF REACTANT FROM A TOWING OR CARRYING AIRPLANE TO AN ATTACHED ROCKET OR ROCKETPLANE 审中-公开
公开(公告)号：US20190168887A1
公开(公告)日：2019-06-06
申请号：US16135998
申请日：2018-09-19
申请人： John A. Burgener , Mitchell Burnside Clapp , Daniel Lee DeLong
发明人： John A. Burgener , Mitchell Burnside Clapp , Daniel Lee DeLong
IPC分类号： B64D39/00 , B64C39/02 , B64G1/00 , B64G1/14 , B64D5/00
CPC分类号： B64D39/00 , B64D5/00 , B64D27/023 , B64G1/005 , B64G1/14
摘要： A high altitude vehicle is brought to a desired altitude above sea-level prior to the transfer of fuel and/or oxidant from an airplane to the high altitude vehicle. The high altitude vehicle may be towed to the desired altitude by a tow airplane or may reach the desired altitude under its own power. At the desired altitude, the high altitude vehicle is connected to the tow airplane via a tow cable. Alternatively, the high altitude vehicle may be mechanically carried by the tow airplane. Fuel and/or oxidant is transferred to the high altitude vehicle from the tow airplane via respective fuel and/or oxidant lines. The high altitude vehicle then separates from the tow airplane and proceeds to high altitude under its own power. The high altitude vehicle weighs less and may have smaller wings than a comparable vehicle configured for self-powered, fully fueled flight from takeoff.

92. 发明申请

US20180222603A1 AIR AND SPACE CRAFT WITH INDEPENDENTLY ORIENTED THRUST GENERATORS 审中-公开
公开(公告)号：US20180222603A1
公开(公告)日：2018-08-09
申请号：US15637922
申请日：2017-06-29
申请人： Charles Grigg
发明人： Charles Grigg
IPC分类号： B64G1/14 , B64G1/40 , B64C39/00 , B64D27/20 , B64D27/02
CPC分类号： B64G1/14 , B64C15/02 , B64C39/001 , B64D27/023 , B64D27/20 , B64D2027/026 , B64G1/40 , B64G1/403
摘要： An aircraft includes a fuselage having an upper surface and a lower surface and a plurality of planetary modules housed in the fuselage, an individual planetary module having a first jet engine directed outward of the upper surface of the fuselage and a second jet engine directed outward of the lower surface of the fuselage, the individual planetary module rotatable within the fuselage about a vertical axis.

93. 发明授权

US09193457B2 Superconductive hypersonic liquefaction nosecone 有权
标题翻译：超导超声液化诺西酮
公开(公告)号：US09193457B2
公开(公告)日：2015-11-24
申请号：US13969467
申请日：2013-08-16
申请人： Charl Emelio Janeke
发明人： Charl Emelio Janeke
IPC分类号： B64C30/00 , B64C1/00 , B64C1/38
CPC分类号： B64C1/38 , B64C1/0009 , B64C23/04 , B64C30/00 , B64C2001/0045 , B64D27/023
摘要： An apparatus and method for mitigating the shock front of an aerospace plane flying at hypersonic speeds. The invention employs supercooling driven by the cryogenic power of liquid hydrogen, regenerative evaporation of liquid hydrogen or liquid nitrogen and consequential isothermal compression, to usurp the shock front in totality at Mach 1.
摘要翻译：一种减轻超音速飞行的航空航天飞机的冲击前沿的装置和方法。本发明采用由液氢的低温动力驱动的过冷，液态氢或液氮的再生蒸发和随后的等温压缩，以Mach 1全面篡夺冲击前沿。

94. 发明授权

US08702041B2 Aerodynamic and spatial composite flight aircraft, and related piloting method 有权
标题翻译：空气动力学和空间复合飞行器及相关试点方法
公开(公告)号：US08702041B2
公开(公告)日：2014-04-22
申请号：US12443359
申请日：2007-10-17
申请人： Christophe Chavagnac , Jérôme Bertrand , Hugues Laporte-Weywada , Olivier Poulain , Philippe Matharan , Robert Laine
发明人： Christophe Chavagnac , Jérôme Bertrand , Hugues Laporte-Weywada , Olivier Poulain , Philippe Matharan , Robert Laine
IPC分类号： B64G1/14 , B64G1/26 , B64G1/40 , B64D27/02 , B64C39/12
CPC分类号： B64G1/005 , B64D27/023 , B64D2027/026 , B64G1/002 , B64G1/14 , B64G1/401 , Y02T50/44
摘要： An aircraft having propulsion units for both conventional aircraft flight in the atmosphere and for high-altitude operation as a rocket. The aircraft is divided into a payload compartment and a compartment containing rocket propulsion unit propellant or fuel, and includes a long transverse wing with a small back-sweep to favor lift in the dense layers of the atmosphere and to thus make it possible to climb to high altitudes at a subsonic speed before using the rocket propulsion units. The return flight portion is performed by gliding or controlled as for a conventional aircraft.
摘要翻译：一架飞机具有用于常规飞机在大气中飞行和作为火箭进行高空作战的推进装置。飞机分为有效载荷舱和包含火箭推进装置推进剂或燃料的舱室，并且包括具有小的反向扫掠的长横翼，以有利于在大气层的致密层中的升力，从而使其可以爬上在使用火箭推进装置之前，亚音速的高海拔高度。返回飞行部分通过滑翔或受控于常规飞机执行。

95. 发明申请

US20100276545A1 Aerodynamic and Spatial Composite Flight Aircraft, and related Piloting Method 有权
标题翻译：空气动力学和空间复合飞行器及相关试飞方法
公开(公告)号：US20100276545A1
公开(公告)日：2010-11-04
申请号：US12443359
申请日：2007-10-17
申请人： Christophe Chavagnac , Jérôme Bertrand , Hugues Laporte-Weywada , Olivier Poulain , Philippe Matharan , Robert Laine
发明人： Christophe Chavagnac , Jérôme Bertrand , Hugues Laporte-Weywada , Olivier Poulain , Philippe Matharan , Robert Laine
IPC分类号： B64G1/14 , B64C1/00
CPC分类号： B64G1/005 , B64D27/023 , B64D2027/026 , B64G1/002 , B64G1/14 , B64G1/401 , Y02T50/44
摘要： This aircraft comprises both propulsion units (7, 16, 17) for conventional aircraft flight in the atmosphere and for high-altitude operation as a rocket. It is divided into a payload compartment (8) and a compartment (13) essentially containing rocket propulsion unit ergols. It comprises a long transverse wing (3) with a small back-sweep to favour the lift in the dense layers of the atmosphere and make it possible to climb to high altitudes at a subsonic speed before using the rocket propulsion units. The return is performed by gliding or controlled as for a conventional aircraft.
摘要翻译：这架飞机包括用于常规飞机在大气中飞行并作为火箭进行高空作战的推进装置（7,16,17）。它分为有效载荷隔室（8）和基本上包含火箭推进单元麦角的舱室（13）。它包括长横翼（3），具有小的反向扫掠，有利于大气层中的升力，并且可以在使用火箭推进装置之前以亚音速爬升到高海拔地区。返回通过滑翔或控制来执行，如同常规飞机。

96. 发明申请

US20080221745A1 COLLECTION AND DISTRIBUTION SYSTEM 审中-公开
标题翻译：收集和分配系统
公开(公告)号：US20080221745A1
公开(公告)日：2008-09-11
申请号：US11932698
申请日：2007-10-31
申请人： Peter H. Diamandis , Granger Whitelaw , Michael R. D'Angelo
发明人： Peter H. Diamandis , Granger Whitelaw , Michael R. D'Angelo
IPC分类号： G05D1/00
CPC分类号： B64D27/023 , A63K3/00 , B64G3/00
摘要： A collection and distribution system wherein information is collected from one or more aerial vehicles and from one or more ground-based sources before being processed and provided to an end-user.
摘要翻译：一种收集和分配系统，其中在处理之前将信息从一个或多个空中交通工具和一个或多个地面来源收集并提供给最终用户。

97. 发明申请

US20080217472A1 ROCKET-POWERED VEHICLE RACING REALITY SYSTEM 审中-公开
标题翻译： ROCKET-POWERED车辆现场系统
公开(公告)号：US20080217472A1
公开(公告)日：2008-09-11
申请号：US11875745
申请日：2007-10-19
申请人： Peter H. Diamandis , Granger Whitelaw , Michael R. D'Angelo
发明人： Peter H. Diamandis , Granger Whitelaw , Michael R. D'Angelo
IPC分类号： B64D45/00
CPC分类号： B64D27/023 , A63K3/00 , B64G3/00
摘要： An aerial vehicle race and reality system for entertaining spectators wherein computer-generated images are optionally provided to at-least partially define a race-course.
摘要翻译：一种用于娱乐观众的空中车辆种族和现实系统，其中可选地提供计算机生成的图像以至少部分地限定赛跑。

98. 发明授权

US06340133B1 System to transform a horizontal take-off and self-sustained horizontal flight airplane into self-sustained horizontal flight, vertical landing and take-off, hybrid integrated airplane 失效
标题翻译：将水平起飞和自立水平飞行飞机转变为自主持续的水平飞行，垂直着陆和起飞的系统，混合动力综合飞机
公开(公告)号：US06340133B1
公开(公告)日：2002-01-22
申请号：US09581312
申请日：2000-06-12
申请人： Franco Capanna
发明人： Franco Capanna
IPC分类号： B64C2722
CPC分类号： B64D27/023 , B64C29/0083
摘要： The present invention relates to a system for the transformation of a traditional self-sustained horizontal take-off and landing aircraft into hybrid, integrated, self-sustained vertical take-off and landing and horizontal flight comprising, besides the propulsion system already provided in the aircraft, a hydraulic propulsion system, activating at least a blade rotor (1), to be used during the vertical take-off and landing and transition phases, said hydraulic system being powered by the engines of the aircraft, and at least an auxiliary engine (2), provided in a rear position and/or under the aircraft, said at least an auxiliary engine being progressively tiltable and swingable between two limit positions, respectively vertical position and horizontal position, said standard propulsion means of the aircraft being deactivated during the vertical take-off and landing and the transition and activated during the self-sustained horizontal flight, and said at least an auxiliary engine and said at least one auxiliary engine being operating during the vertical take-off and landing and the transition and deactivated during the self-sustained horizontal flight.
摘要翻译：本发明涉及一种用于将传统的自维持水平起飞和着陆飞机转变成混合动力，综合的，自持的垂直起飞和降落和水平飞行的系统，除了已经提供的推进系统之外，飞机，液压推进系统，启动至少一个叶片转子（1），以在垂直起飞和着陆和过渡阶段期间使用，所述液压系统由飞行器的发动机驱动，并且至少辅助发动机（2），设置在后部位置和/或在飞行器下方，所述至少一个辅助发动机可以在两个极限位置（分别垂直位置和水平位置）之间逐渐倾斜和摆动，所述飞行器的标准推进装置在垂直起飞和着陆，并且在自维持水平飞行期间过渡并被激活，并且至少表示辅助发动机和所述至少一个辅助发动机在垂直起飞和着陆期间运行，并且在自持水平飞行过程中停止运转。

99. 发明授权

US6119985A Reusable rocket-propelled high altitude airplane and method and apparatus for mid-air oxidizer transfer to said airplane 失效
标题翻译：可重复使用的火箭推进高空飞机和中空氧化剂转移到飞机的方法和装置
公开(公告)号：US6119985A
公开(公告)日：2000-09-19
申请号：US813476
申请日：1997-03-07
申请人： Mitchell B. Clapp , Robert M. Zubrin
发明人： Mitchell B. Clapp , Robert M. Zubrin
IPC分类号： B64C39/02 , B64D27/02 , B64D39/00 , B64G1/00 , B64G1/14 , B64G1/40 , B64G1/58 , B64G1/62
CPC分类号： B64G1/005 , B64C39/02 , B64D27/023 , B64D39/00 , B64G1/14 , B64G1/401 , B64G1/402 , B64G1/58 , B64G1/62 , F05B2220/50 , Y02T50/44
摘要： A reusable rocket airplane which may be utilized to launch satellites and other payloads into space. The airplane may also be used for rapid surface to surface flight. The reusable rocket airplane may be safely supplied with oxidizer in mid-air, achieve an altitude outside the Earth's atmosphere, and return safely to be used again. The rocket airplane utilizes unique concepts to secure its gas turbine engines for high speed flight, minimize fluid spillage during mid-air oxidizer transfer, as well as employs design features advantageous to the economical building and reuse of the rocket airplane.
摘要翻译：一种可重复使用的火箭飞机，可用于将卫星和其他有效载荷发射到太空。飞机也可用于快速的表面飞行。可重复使用的火箭飞机可以在半空中安全地供应氧化剂，实现地球大气层外的高度，并安全返回再次使用。火箭飞机利用独特的概念来确保其燃气涡轮发动机的高速飞行，使中空氧化器传输期间的流体溢出最小化，并且采用有利于经济建筑和火箭飞机重用的设计特征。

100. 发明授权

US5855340A 3X multi-engine jet configuration and method of operation 失效
标题翻译： 3X多引擎喷气机配置及操作方法
公开(公告)号：US5855340A
公开(公告)日：1999-01-05
申请号：US493738
申请日：1995-06-22
申请人： Richard J. Bacon
发明人： Richard J. Bacon
IPC分类号： B64D27/02 , B64D27/20 , B64D27/16
CPC分类号： B64D27/023 , B64D27/20
摘要： A centerline mounted overbalanced multiple main jet engine configuration. The multiple jet engines are centerline mounted rather than parallel offset. While each jet engine is a "main" engine, capable of safely operating the aircraft in the event of a failure of the other engines, the engines are overbalanced in the sense that at least one of the main engines has substantially greater thrust than the other main engines. All of the main engines operate at critical periods of flight, but only one or the other of the main engines operates at other periods. The configuration of this invention combines the efficiency and performance of a single engined aircraft with enhanced safety advantages.
摘要翻译：中心线安装超平衡多主喷气发动机配置。多台喷气发动机是中心线安装的，而不是平行偏移。虽然每个喷气发动机是“主要”发动机，能够在其他发动机发生故障的情况下安全地操作飞行器，但是发动机是过平衡的，因为主发动机中的至少一个具有比其他发动机大得多的推力主机所有主要发动机都在关键的飞行时段运行，但只有一个或另一个主发动机在其他时期运行。本发明的结构将单个发动机的效率和性能与增强的安全性优点相结合。

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