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公开(公告)号：US12110112B2
公开(公告)日：2024-10-08
申请号：US17828092
申请日：2022-05-31
申请人： THE BOEING COMPANY
CPC分类号： B64D11/04 , B64D11/0007
摘要： A galley cart stowage system for stowing galley carts in a galley of an aircraft includes a lower cart compartment and an upper cart compartment located above the lower cart compartment both configured to receive at least one galley cart. At least one vertical conveyance device extends between the cart compartments to move the galley carts between the cart compartments. A galley workspace having a workspace volume is located between the cart compartments. The galley workspace has a countertop movable between a deployed position and a clearance position to form an opening between the lower cart compartment and the upper cart compartment to allow movement of the galley carts between the lower cart compartment and the upper cart compartment.
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公开(公告)号：US11820487B2
公开(公告)日：2023-11-21
申请号：US17540504
申请日：2021-12-02
申请人： The Boeing Company
摘要： An aircraft has an aft main cargo cabin with a low deck floor, and a rear access configured to provide access to the aft main cargo cabin from behind the fuselage. The deck floor of the aft main cargo cabin is lower than a first deck floor of a forward main cabin of a forward section of the fuselage. The aft main cargo cabin has a second height that is greater than the first height of the forward main cabin, allowing the aft main cargo cabin to accommodate oversize cargo with larger dimension(s). The aircraft may be built with such an aft main cargo cabin and rear access, or may be a modified aircraft that includes such an aft main cargo cabin and rear access. Related methods of reconfiguring a base aircraft into a modified aircraft having such an aft main cargo cabin and rear access are also disclosed.
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公开(公告)号：US11549383B2
公开(公告)日：2023-01-10
申请号：US16669766
申请日：2019-10-31
申请人： The Boeing Company
摘要： A variable geometry aerodynamic blade system employs a blade having a leading edge and a trailing edge. At least one shape memory alloy component is integrated in the blade for aerodynamic repositioning of one or both of the leading and trailing edges. At least one heating element interacts with the at least one shape memory alloy component to provide heating for transition between an austenitic and a martensitic phase. The at least one shape memory alloy component is responsive to the at least one heating element to alter one of a camber and twist of the blade responsive to a control signal. A control system is operatively engaged to the at least one heating element, the control system receiving a command signal and outputting the control signal responsive to the command signal.
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公开(公告)号：US10800525B2
公开(公告)日：2020-10-13
申请号：US13897452
申请日：2013-05-20
申请人： The Boeing Company
发明人： Mithra M. K. V. Sankrithi , Arvin Shajanian , Sergey D. Barmichev , Victor Ken Stuhr , Joshua M. Kusnitz , Ismail Robbana
摘要： A hybrid fuel airplane and methods are presented. A cryogenic fuel is transferred to an airplane propulsor from an airplane fuel system comprising a cryogenic fuel tank and a jet fuel tank. The cryogenic fuel tank conforms to an outer mold line and carries a cryogenic fuel, and is located in a portion of the airplane body while not extending beyond the outer mold line. The jet fuel tank carries a jet fuel and is located in an airplane wing, or an airplane body, or both. A dynamic aircraft load is born on the cryogenic fuel tank, and the airplane propulsor is operated using the cryogenic fuel to generate thrust for the hybrid fuel airplane. An aerodynamic lift is generated using the airplane wing coupled to the airplane body.
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公开(公告)号：US20160297528A1
公开(公告)日：2016-10-13
申请号：US14680978
申请日：2015-04-07
申请人： The Boeing Company
CPC分类号： B64D11/0601 , B64C1/00 , B64C1/061 , B64C1/064 , B64C1/12 , B64C2001/0027 , B64C2001/0045 , Y02T50/12 , Y02T50/46
摘要： An aircraft configuration having a crown cabin above a main cabin, with the crown cabin having a hanging floor structure. This enables a fuselage design that substantially increases passenger seating capacity relative to traditional single-passenger-deck configurations, while minimizing fuselage perimeter and fuselage wetted area relative to double-passenger-deck configurations.
摘要翻译： 具有在主舱上方的冠舱的飞行器构造，其中舱室具有悬挂的地板结构。 这使得机身设计相对于传统的单乘客甲板配置大大增加乘客座椅容量，同时相对于双乘客甲板配置使机身周边和机身湿润面积最小化。
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公开(公告)号：US20160046381A1
公开(公告)日：2016-02-18
申请号：US14457287
申请日：2014-08-12
申请人： The Boeing Company
CPC分类号： B64D27/26 , B64C3/32 , B64C25/04 , B64C25/34 , B64D27/02 , B64D29/02 , B64D29/04 , B64D2027/005 , B64D2027/262 , B64D2027/264 , Y02T50/66
摘要： An aircraft includes an engine mounted to a wing by a first support, such as a strut, configured to secure the engine to the wing in a position above the wing. A second support, secured to a fuselage portion of the aircraft, is defined by a bridge structure configured to separately and independently secure the engine to the fuselage. The engine is thus secured by the first support directly to the aircraft wing, and via the second support, in concert with the first, to a portion of an aircraft fuselage spaced laterally of the engine-to-wing attachment. In one embodiment the bridge structure, which extends between the engine and fuselage, may be bowed upwardly so as to define a convex curvature when viewed along the longitudinal axis of the aircraft. Such a curvature may, inter alia, optimize aerodynamic spacing of the bridge from the wing to minimize undesirable shock waves.
摘要翻译： 飞机包括通过诸如支柱的第一支撑件安装到机翼的发动机，其构造成将发动机固定在机翼上方的机翼上。 固定在飞行器的机身部分上的第二支撑件由桥结构限定，桥结构构造成将发动机单独地并独立地固定在机身上。 因此，发动机通过第一支撑件直接固定到飞行器机翼，并且经由第二支撑件与第一支撑件一体地固定到发动机到翼的附件侧向间隔的飞行器机身的一部分。 在一个实施例中，在发动机和机身之间延伸的桥结构可以向上弯曲，以便当沿着飞行器的纵向轴线观察时限定凸曲率。 这样的曲率可以特别地优化桥梁与机翼的空气动力学间隔，以最小化不期望的冲击波。
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公开(公告)号：US11926431B2
公开(公告)日：2024-03-12
申请号：US17570293
申请日：2022-01-06
申请人： The Boeing Company
摘要： Coupler assemblies are described that removably couple sides of an auxiliary fuel tank in a cargo area of an aircraft. In one embodiment, a first coupler of the coupler assemblies includes a first attachment member that supports a body with a hollow channel having a centerline disposed longitudinally in the fuselage between a first end and a second end, and a slot between an outer surface of the body and the hollow channel. A second coupler of the coupler assemblies includes an engagement member, a second attachment member, and an arm extending between the engagement member and the second attachment member. The engagement member is slidably received within the hollow channel from the first end, and fits slidably within the hollow channel to engage with the body of the first coupler, with the arm extending through the slot.
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公开(公告)号：US20230234708A1
公开(公告)日：2023-07-27
申请号：US17584583
申请日：2022-01-26
申请人： The Boeing Company
CPC分类号： B64D11/0007 , B64D11/04
摘要： A lift system for an aircraft includes a first galley cart, a second galley cart, a floor deck, and a frame. The frame defines a first storage zone, a second storage zone, and a third storage zone that are stacked. A bottom end of the first storage zone is aligned with the floor deck, a top end of the second storage zone is aligned with the floor deck, and a bottom end of the third storage zone is aligned with a top end of the first storage zone. The lift system also includes a first lift configured to move the first galley cart from the first storage zone to the second storage zone and a second lift configured to move the second galley cart from the first storage zone to the third storage zone.
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公开(公告)号：US11208213B2
公开(公告)日：2021-12-28
申请号：US15473758
申请日：2017-03-30
申请人： The Boeing Company
发明人： Mithra M. K. V. Sankrithi , Max Urban Kismarton , James A. Fullerton , Gary Lee Senechal , Sergey D. Barmichev
摘要： A fuselage is described that includes a plurality of frames and a plurality of seat rows spaced apart according to a seat pitch. Each frame includes a lateral floor beam, and each seat row of the plurality of seat rows includes a load-bearing structural base with a plurality of legs attached to a proximal lateral floor beam and a distal lateral floor beam. Each seat row also includes a seat or bank of seats attached to the load-bearing structural base, where the seat or bank of seats includes at least one seat bottom and at least one seat back. Further, each seat row includes an interface between (i) the load-bearing structural base and (ii) the seat or bank of seats to allow for attachment and detachment of the seat or bank of seats relative to the load-bearing structural base.
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公开(公告)号：US20190264617A1
公开(公告)日：2019-08-29
申请号：US15904838
申请日：2018-02-26
申请人： The Boeing Company
摘要： Hybrid turbine engines and methods of operating the same are disclosed herein. The hybrid turbine engines include a first thrust-generating device that includes a turbine with a turbine rotary shaft and a clutch, which includes a clutch input, which is operatively coupled to the turbine rotary shaft, and a clutch output. The clutch defines an engaged state and a disengaged state. The hybrid turbine engines also include a rotary electric machine including a machine rotary shaft that is operatively coupled to the clutch output, a second thrust-generating device that is operatively coupled to the machine rotary shaft, and an electric power system. The rotary electric machine is configured to selectively receive an electric power output from the electric power system, such as to selectively produce additional thrust, and to selectively receive in an input torque from the machine rotary shaft, such as to selectively produce additional electric power.
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