公开(公告)号：US12110105B2

公开(公告)日：2024-10-08

申请号：US18107880

申请日：2023-02-09

申请人： Textron Innovations Inc.

发明人： John Richard McCullough ,  Paul K. Oldroyd

IPC分类号： B64C29/02 ,  B64C11/28 ,  B64C27/50 ,  B64C29/00 ,  B64C39/02 ,  B64C39/06 ,  B64D1/08 ,  B64D35/00 ,  B64D25/12

CPC分类号： B64C29/0033 ,  B64C11/28 ,  B64C27/50 ,  B64C29/02 ,  B64C39/02 ,  B64C39/06 ,  B64D1/08 ,  B64D35/00 ,  B64C2211/00 ,  B64D25/12

摘要： An aircraft includes an airframe having at least one wing. A distributed propulsion system is attached to the airframe and includes first and second pluralities of propulsion assemblies. In a vertical takeoff and landing flight mode, each of the propulsion assemblies generates vertical thrust with rotor assemblies of the first plurality of propulsion assemblies rotating in a horizontal plane and rotor assemblies of the second plurality of propulsion assemblies rotating in a parallel horizontal plane. In a forward flight mode, each of the propulsion assemblies generates forward thrust with the rotor assemblies of the first plurality of propulsion assemblies rotating in a vertical plane and the rotor assemblies of the second plurality of propulsion assemblies rotating in a parallel vertical plane. In both the vertical takeoff and landing flight mode and the forward flight mode, a pod assembly coupled to the airframe remains in a generally horizontal attitude.

公开(公告)号：US20240228047A1

公开(公告)日：2024-07-11

申请号：US18430336

申请日：2024-02-01

申请人： Vivek Sandrapaty

发明人： Vivek Sandrapaty

IPC分类号： B64D17/34 ,  B64D25/12

CPC分类号： B64D17/343 ,  B64D25/12

摘要： A separable aircraft cabin module is provided with parachutes that are dynamically and independently reefed in order to safely deliver the cabin module, and its occupants from a separation from a main aircraft body at altitude and speed to a landing. The arrangement includes a rear parachute and two front parachutes which particularly handle the cylindrical shape of the cabin module through the various stages after separation from the main aircraft body.

公开(公告)号：US11492116B2

公开(公告)日：2022-11-08

申请号：US17545158

申请日：2021-12-08

申请人： Textron Innovations Inc.

发明人： Kip Gregory Campbell

IPC分类号： B64C29/00 ,  B64D1/02 ,  B64D37/12 ,  B64D25/12

摘要： A tiltrotor aircraft has a vertical takeoff and landing flight mode and a forward flight mode. The aircraft includes an airframe having at least one wing. First and second oppositely disposed booms extend longitudinally from the at least one wing. Forward rotors are coupled to the forward ends of the booms and aft rotors are coupled to the aft ends of the booms. The forward rotors are reversibly tiltable between a vertical lift orientation, wherein the forward rotors are above the booms, and a forward thrust orientation, wherein the forward rotors are forward of the booms. The aft rotors are reversibly tiltable between a vertical lift orientation, wherein the aft rotors are below the booms, and a forward thrust orientation, wherein the aft rotors are aft of the booms.

公开(公告)号：US20200255136A1

公开(公告)日：2020-08-13

申请号：US16677453

申请日：2019-11-07

申请人： Karem Aircraft, Inc.

发明人： Abe Karem

IPC分类号： B64C29/00 ,  B64D7/00 ,  B64D1/06 ,  B64D1/10 ,  B64C39/02 ,  B64D25/12

摘要： Devices and systems of the inventive concept provide a durable, all-weather manned or unmanned aircraft that is capable of vertical flight and provides improved stability upon payload launch or delivery. The payload bay is positioned along the central axis of the aircraft and proximal to the aircraft's center of gravity. Control and fuel systems are positioned fore and aft of the payload bay, respectively. The payload bay is configured to store and deliver a wide variety of payload types. The aircraft also includes features that reduce vibration, prolong the interval between necessary maintenance, and permit all-weather operation.

公开(公告)号：US10730632B2

公开(公告)日：2020-08-04

申请号：US15837139

申请日：2017-12-11

申请人： Goodrich Corporation

发明人： Dariusz Sapija ,  Sebastian Szymański

IPC分类号： B64D25/12 ,  B64C1/32 ,  B64D25/08 ,  B64D45/00

摘要： The present disclosure relates to an aircraft comprising a passenger module, and also a method of protecting a passenger on an aircraft. The passenger module is configured to be ejected through a skin of the aircraft in response to an ejection command. The ejection command may be given in response to a fatal condition to the aircraft being detected or manually indicated.

公开(公告)号：US10343773B1

公开(公告)日：2019-07-09

申请号：US16246474

申请日：2019-01-12

申请人： Bell Helicopter Textron Inc.

发明人： John Richard McCullough ,  Paul K. Oldroyd

IPC分类号： B64C29/02 ,  B29C39/02 ,  B64C39/02 ,  B64D1/08 ,  B64C39/06 ,  G05D1/00 ,  B64D25/12

摘要： An aircraft includes a flying frame and a pod assembly that is selectively attached to the flying frame. The pod assembly has an aerodynamic outer shape. The flying frame includes an airframe having first and second wings, a propulsion system attached to the airframe and a flight control system operably associated with the propulsion system. The flying frame has a vertical takeoff and landing mode in which the first wing is forward of the pod assembly and the second wing is aft of the pod assembly. The flying frame has a forward flight mode in which the first wing is below the pod assembly and the second wing is above the pod assembly. The flying frame is operable for flight both with the pod assembly and without the pod assembly attached thereto. The flying frame is operable to jettison the pod assembly during flight.

公开(公告)号：US09963228B2

公开(公告)日：2018-05-08

申请号：US15200163

申请日：2016-07-01

申请人： Bell Helicopter Textron Inc.

发明人： John Richard McCullough ,  Paul K. Oldroyd

IPC分类号： B64C29/00 ,  B64C39/08 ,  B64C39/02 ,  B64D27/12 ,  B64C11/28 ,  B64D17/80 ,  B64C1/28 ,  B64C1/32 ,  B64C17/02 ,  B64C27/26 ,  B64C27/28 ,  B64C29/02 ,  B64D25/12 ,  B64C27/30

CPC分类号： B64C29/0033 ,  B64C1/28 ,  B64C1/32 ,  B64C11/28 ,  B64C17/02 ,  B64C27/26 ,  B64C27/28 ,  B64C27/30 ,  B64C29/02 ,  B64C39/024 ,  B64C39/08 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/185 ,  B64C2211/00 ,  B64D17/80 ,  B64D25/12 ,  B64D27/12

摘要： In some embodiments, an aircraft includes a flying frame having an airframe, a propulsion system attached to the airframe and a flight control system operably associated with the propulsion system wherein, the flying frame has a vertical takeoff and landing mode and a forward flight mode. A pod assembly is selectively attachable to the flying frame such that the flying frame is rotatable about the pod assembly wherein, the pod assembly remains in a generally horizontal attitude during vertical takeoff and landing, forward flight and transitions therebetween.

公开(公告)号：US08100362B2

公开(公告)日：2012-01-24

申请号：US12162379

申请日：2007-01-29

申请人： Bernard Guering

发明人： Bernard Guering

IPC分类号： B64C1/00 ,  B64C13/00 ,  B64C13/04 ,  B64C39/02 ,  B64D25/12

CPC分类号： B64C1/068 ,  B64C1/22

摘要： A cockpit and an aircraft including such cockpit. The cockpit includes a front section of an aircraft. Such cockpit includes a pressure bulkhead sealing the section and a pressurization system for pressurizing such section.

摘要翻译： 驾驶舱和包括这种驾驶舱的飞机。 驾驶舱包括飞机的前部。 这种驾驶舱包括密封该部分的压力隔板和用于对该区段加压的加压系统。

公开(公告)号：US20100006695A1

公开(公告)日：2010-01-14

申请号：US12442778

申请日：2007-09-10

申请人： Michel Aguilar

发明人： Michel Aguilar

IPC分类号： B64C29/00 ,  B64D25/12

CPC分类号： B64C29/0008 ,  B64C29/0091 ,  B64C39/10 ,  B64D27/02 ,  Y02T50/12

摘要： A vertical take-off vehicle includes two thermoreactors/turbine engines having a rectangular air inlet opening into a positive-displacement rotary compressor supplying compressed air to a tank connected to (i) a combustion chamber whose exhaust gases actuate a compressor-driving turbine and discharge onto the fixed rear wing upper surface, and (ii) the combustion chamber of the main engine whose exhaust gases discharge directly onto the wing upper surface, the variable incidence of which, in take-off mode, generates a lift force adding to the forces that develop on the front wings. In take-off mode, the variable-geometry upper surfaces of the front wings have a maximum camber onto which the exhaust gases produced in an internal combustion chamber flow at great speed. In cruise mode, the combustion chamber is off and the upper surface returns to a reduced camber position as the rear wing returns to an incidence optimizing total drag and lift forces.

摘要翻译： 垂直起飞车包括两个热反应器/涡轮发动机，其具有通向正位移旋转压缩机的矩形空气入口，该容积旋转压缩机将压缩空气供应到连接到（i）燃烧室的罐，该燃烧室的排气致动压缩机驱动涡轮并排出 （ii）主发动机的燃烧室，其排气直接排放到机翼上表面上，其起飞模式中的变化发生产生增加力的升力 在前翼发展。 在起飞模式中，前翼的可变几何上表面具有在内燃室中产生的排气以高速度流动的最大弧度。 在巡航模式中，当后翼返回到最佳总牵引力和提升力的入射点时，燃烧室关闭并且上表面返回到减小的外倾位置。

公开(公告)号：US5899414A

公开(公告)日：1999-05-04

申请号：US906116

申请日：1997-07-25

申请人： Jose G. Duffoo

发明人： Jose G. Duffoo

IPC分类号： B64D17/80 ,  B64D25/12

CPC分类号： B64D25/12 ,  B64D17/80 ,  B64D2201/00

摘要： An aircraft rescue system is provided including a plurality of parachutes coupled to a tail of the aircraft, a midsection of the aircraft, and a nose of the aircraft. The parachutes are adapted to deploy upon the actuation thereof. A control mechanism is included for allowing a pilot to manually actuate the parachutes.

摘要翻译： 提供了一种飞机救援系统，包括耦合到飞行器尾部的多个降落伞，飞机的中部和飞机的鼻子。 降落伞适于在其致动时展开。 包括用于允许飞行员手动致动降落伞的控制机构。