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61. 发明申请

US20180208295A1 THRUST PRODUCING UNIT WITH AT LEAST TWO ROTOR ASSEMBLIES AND A SHROUDING 审中-公开
公开(公告)号：US20180208295A1
公开(公告)日：2018-07-26
申请号：US15878831
申请日：2018-01-24
申请人： AIRBUS HELICOPTERS DEUTSCHLAND GMBH
发明人： Sebastian MORES , Alessandro D'ALASCIO , Thomas KNEISCH , Klaus KICKER , Stefanie LINK , Uwe KIESEWETTER , Marius BEBESEL
IPC分类号： B64C11/00 , B64C27/08 , B64C11/48
CPC分类号： B64C11/001 , B64C11/48 , B64C27/08 , B64C27/20 , B64C2201/027 , B64C2201/162 , B64D25/00
摘要： A thrust producing unit for producing thrust in a predetermined direction, comprising at least two rotor assemblies and a shrouding, each one of the at least two rotor assemblies, defining an associated rotor plane, wherein a first rotor assembly of the at least two rotor assemblies is provided for operating in a failure-free operating mode of the thrust producing unit and a second rotor assembly of the at least two rotor assemblies is provided for operating at least in case of a failure of the first rotor assembly, and wherein the shrouding accommodates at most one of the at least two rotor assemblies.

62. 发明申请

US20180178899A1 AIRCRAFT CAPABLE OF VERTICAL TAKE-OFF AND LANDING, VERTICAL AND HORIZONTAL FLIGHT AND ON-AIR ENERGY GENERATION 审中-公开
公开(公告)号：US20180178899A1
公开(公告)日：2018-06-28
申请号：US15391700
申请日：2016-12-27
申请人： Korea Advanced Institute of Science and Technology
发明人： Dongsoo HAR , Celso MORAES , Dongsuk KUM
IPC分类号： B64C3/38 , B64C29/02 , B64C9/20 , B64C13/50 , B64C39/02 , B64D27/24
CPC分类号： B64D27/24 , B64C3/385 , B64C5/02 , B64C11/001 , B64C13/50 , B64C29/02 , B64C39/024 , B64C2201/021 , B64C2201/042 , B64C2201/066 , B64C2201/088 , B64C2201/104 , B64C2201/108 , B64C2201/141 , B64C2201/146 , B64C2201/162 , B64C2201/165 , Y02T50/62
摘要： An aircraft includes: a fuselage having opposing leading and trailing extremities along a vertical axis; a fixed wing airframe having opposed at least two main wings connected to the fuselage and extending on a horizontal axis; at least two electric coplanar main wing motors respectively attached to the main wings; a duct frame attach to the trailing extremity of the fuselage; at least two horizontal stabilizers connected to the duct frame and extending on the horizontal axis; an electric tail motor fitted an inner side of the duct frame; multiple battery packs installed inside the fuselage and suitable for supply power to the main wing motors and the tail motor; and support beams suitable for connecting the duct frame to the fuselage.

63. 发明授权

US09950800B2 Integrated pusher turbofan for aircraft 有权
公开(公告)号：US09950800B2
公开(公告)日：2018-04-24
申请号：US14555340
申请日：2014-11-26
申请人： The Boeing Company
发明人： Sina Golshany , Todd W. Erickson , Christopher R. Holtorf , Derek R. Alderks
IPC分类号： B64D27/18 , B64D29/02 , B64C3/32 , B64C11/00
CPC分类号： B64D27/18 , B64C3/32 , B64C11/001 , B64D29/02 , Y02T50/66
摘要： A propulsion system for a transport aircraft employs a gas turbine core coupled to a wing. A ducted fan is coupled to the core gas turbine extending downstream from and integrated in a trailing edge of the airplane wing.

64. 发明授权

US09902501B2 Propeller for an aircraft turbomachine, including a blade retaining structure through which the aerodynamic part of each blade passes 有权
公开(公告)号：US09902501B2
公开(公告)日：2018-02-27
申请号：US14977049
申请日：2015-12-21
申请人： Airbus Operations (SAS)
发明人： Julien Guillemaut , Guillaume Gallant
IPC分类号： B64D27/00 , B64D27/14 , B64C11/00 , B64C11/06 , B64C11/20
CPC分类号： B64D27/14 , B64C11/001 , B64C11/06 , B64C11/20 , B64D2027/005 , Y02T50/66
摘要： A propeller for a turbomachine intended to be driven in rotation about a propeller rotation axis and including variable pitch blades. The propeller further includes a structure for radial retention of the blades in the event of them breaking. The retaining structure extends around the propeller rotation axis and has the aerodynamic part of each blade of the propeller pass through it. Moreover, each aerodynamic part is equipped with an abutment configured to be retained radially by the retaining structure in the event of a blade fracture causing a fracture in the aerodynamic part radially inside the abutment.

65. 发明授权

US09902494B2 Vertical take off aircraft 有权
公开(公告)号：US09902494B2
公开(公告)日：2018-02-27
申请号：US15402784
申请日：2017-01-10
申请人： MARTIN UAV, LLC
发明人： Stephen Morris
IPC分类号： B64C29/00 , B64C29/02 , G05D1/10 , G05D1/08 , B64C11/00 , B64C9/00
CPC分类号： B64C29/02 , B64C11/001 , B64C39/024 , B64C2009/005 , B64C2201/021 , B64C2201/088 , B64C2201/162 , G05D1/0858 , G05D1/102
摘要： An aircraft includes a fuselage, a wing, a ducted fan and a controller. The wing and the ducted fan are coupled to the fuselage. The controller is operable to control the aircraft in a vertical flight mode, a horizontal flight mode, and transition the aircraft from the vertical flight mode to the horizontal flight mode.

66. 发明授权

US09776714B2 Engine system for vertical and short take off and landing (V/STOL) aircraft 有权
公开(公告)号：US09776714B2
公开(公告)日：2017-10-03
申请号：US14514219
申请日：2014-10-14
申请人： Sandor Wayne Shapery
发明人： Sandor Wayne Shapery
IPC分类号： B64D27/00 , B64C29/00 , B64C11/00 , B64D27/02
CPC分类号： B64C29/0075 , B64C11/001 , B64D2027/026 , Y02T50/64
摘要： An engine system with a multi-gas-generator, tip-turbine driven lift fan with pressurized air circulation control for use on vertical and short-take-off and landing (V/STOL) aircraft is disclosed. Gas generators located around the periphery of the fan drive the fan through action on a fan blade-tip turbine or provide compressed gas (hot or cold) to circulation control devices. Variable pitch fan blades improve part-power cruise performance. Enclosed in a nacelle, the engine employs circulation control to enhance V/STOL performance. In some embodiments, a core cruise turbine gas generator mounted in the center of the fan duct powers the fan during cruise mode. In some hybrid gas and electric power embodiments, the core cruise gas generator is replaced by an electric motor that draws power from a battery in the fuselage. The battery may be charged by an electric generator driven by a gas generator around the periphery of the fan.

67. 发明申请

US20170096221A1 Modular and Morphable Air Vehicle 审中-公开
公开(公告)号：US20170096221A1
公开(公告)日：2017-04-06
申请号：US15205162
申请日：2016-07-08
申请人： Piasecki Aircraft Corporation
发明人： John W. Piasecki , Frederick W. Piasecki , Brian Geiger , Douglas Johnson , David Pitcairn
IPC分类号： B64C37/00 , B64D17/80 , B64C29/00 , B64C25/58 , B64C3/56 , B64C27/22 , B60F5/02 , B64D25/00
CPC分类号： B64C37/00 , B60F5/02 , B64C3/385 , B64C3/56 , B64C11/001 , B64C25/58 , B64C27/08 , B64C27/20 , B64C27/22 , B64C27/32 , B64C27/52 , B64C27/57 , B64C29/00 , B64C29/0033 , B64C39/00 , B64C39/02 , B64D17/80 , B64D25/00 , B64D2201/00 , G05D1/102
摘要： An unmanned air module includes one or more rotors, engines, a transmission and avionics. Any of several different ground modules may be attached to the air module. The air module may fly with and without the ground module attached. The ground module may be manned. The air module may have two rotors, which may be ducted fans. The air module may include a parachute, an airbag and landing gear.

68. 发明申请

US20160376001A1 VEHICLE INCLUDING A TETRAHEDRAL BODY OR CHASSIS 审中-公开
标题翻译：车辆包括四面体或底盘
公开(公告)号：US20160376001A1
公开(公告)日：2016-12-29
申请号：US14631156
申请日：2015-02-25
申请人： Robin Felix
发明人： Robin Felix
IPC分类号： B64C39/00 , B64G1/42 , B63G8/08 , B64C11/46 , B63G8/04 , B64G1/40 , B64C1/06
CPC分类号： B64C39/00 , B63B2241/16 , B63G8/001 , B64C1/06 , B64C11/001 , B64C11/46 , B64C39/024 , B64C2001/0045 , B64G1/10 , B64G1/283 , B64G1/32 , B64G1/40 , B64G1/425 , B64G1/426 , B64G1/446
摘要： A vehicle constructed in the shape of tetrahedral. The vehicle may be an aircraft, a space-craft, a sub-surface vehicle, or an unmanned drone. A tetrahedral body component is one of: a regular tetrahedron, an extended tetrahedron, a foreshortened tetrahedron, a tapered tetrahedron, and a truncated tetrahedron. A means for propulsion is mounted to at least one of the faces of the tetrahedral body component. The means for propulsion may include a turbine engine, a water jet, a gas jet, or electromagnetic propulsion. In another embodiment, the means for propulsion include an engine and a propeller. The engine block is mounted internal to the tetrahedral body component, and is located at the intersection of a tetrahedral shape with a cube shape. The engine block is mounted to the tetrahedral body component by struts perpendicular to the faces of the engine block.
摘要翻译：一种四面体形状的车辆。车辆可以是飞机，太空飞船，地面车辆或无人驾驶飞机。四面体组分是以下之一：正四面体，延伸四面体，缩短四面体，锥形四面体和截顶四面体。用于推进的装置安装在四面体部件的至少一个面上。用于推进的装置可以包括涡轮发动机，水射流，气体射流或电磁推进。在另一个实施例中，用于推进的装置包括发动机和螺旋桨。发动机缸体安装在四面体组件内部，位于四面体形状与立方体形状的交点处。发动机缸体通过垂直于发动机缸体表面的支柱安装在四面体部件上。

69. 发明授权

US09481471B2 Autonomous propulsion apparatus and methods 有权
标题翻译：自主推进装置及方法
公开(公告)号：US09481471B2
公开(公告)日：2016-11-01
申请号：US14076797
申请日：2013-11-11
申请人： The Boeing Company
发明人： Daniel Newman
IPC分类号： F02K3/00 , B64D31/06 , B64D31/00 , B64C11/00
CPC分类号： B64D31/06 , B64C11/001 , B64D31/00 , F02K3/00
摘要： Autonomous propulsion apparatus and methods are disclosed. An example autonomous propulsion unit includes a flight controller capable of executing flight control instructions stored in a memory of the autonomous propulsion unit; and a propulsor to generate propulsion in accordance with the instructions for a payload carrier to which the autonomous propulsion unit is coupled, wherein the flight controller is to provide flight control for the propulsor in an absence of flight control instructions from the payload carrier.
摘要翻译：公开了自主推进装置和方法。示例性自主推进单元包括能够执行存储在自主推进单元的存储器中的飞行控制指令的飞行控制器; 以及推进器，以根据与自主推进单元耦合的有效载荷载体的指令产生推进，其中飞行控制器将在没有来自有效载荷的飞行控制指令的情况下为推进器提供飞行控制。

70. 发明申请

US20160207368A1 Vertical Take-Off and Landing Roadable Aircraft 审中-公开
标题翻译：垂直起降和着陆可行的飞机
公开(公告)号：US20160207368A1
公开(公告)日：2016-07-21
申请号：US14544553
申请日：2015-01-21
申请人： Rajesh Gaonjur
发明人： Rajesh Gaonjur
IPC分类号： B60F5/02 , B64C11/00 , B64C37/00 , B64C27/08
CPC分类号： B60F5/02 , B64C11/001 , B64C27/08 , B64C37/00
摘要： A vertical take-off and landing (VTOL) roadable aircraft which has the features and dimensions of a typical road vehicle is disclosed. When operated on the road the wheels are powered by the engine. When the vehicle is configured for flight, a plurality of propellers is deployed from the storage compartment located on the roof and is powered by the same engine. The conversion process transforms the vehicle into a highly manoeuvrable quadcopter or a multi-rotor aircraft. The design concept enables propellers of relative large diameter to be conveniently secure to the vehicle, while allowing reliable deployment, retrieval and storage of the propellers as required. The total combined area of the propellers enables a low disk loading in the range of some helicopters with equivalent flight efficiency. The propellers are shrouded for safe operation. The conversion is automated, fast, and can be carried out while the vehicle is still moving.
摘要翻译：公开了具有典型道路车辆的特征和尺寸的垂直起降（VTOL）可行驶飞机。当在道路上操作时，车轮由发动机供电。当车辆被配置为飞行时，多个螺旋桨从位于屋顶上的储藏室部署并由相同的发动机供电。转换过程将车辆转换成高度可操纵的四足直升机或多转子飞机。设计理念使得相对较大直径的螺旋桨能够方便地安全到车辆，同时允许螺旋桨可靠地部署，检索和存储。螺旋桨的总组合面积使得在一些具有相当飞行效率的直升机的范围内的低盘载荷。螺旋桨被安全操作。该转换是自动化，快速的，并且可以在车辆仍在移动时进行。

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