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公开(公告)号：US11655017B2
公开(公告)日：2023-05-23
申请号：US17350438
申请日：2021-06-17
发明人： Aurelien Vayssiere , Nicolas Montil , Mathieu Gester , Hubert Neukirch , Pascal Jervaise , Markus Kammerer , Pierre Arnould
摘要： A stiffener skeleton that is configured to be mounted to an upper deck of a rotary wing aircraft in a maintenance phase, comprising an upper stiffening structure with a plurality of supporting arms for providing upside stiffening support, and a lateral stiffening structure with a plurality of supporting legs for providing lateral stiffening support, wherein the plurality of supporting arms and the plurality of supporting legs form a self-supporting frame structure.
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公开(公告)号：US11603180B2
公开(公告)日：2023-03-14
申请号：US17109355
申请日：2020-12-02
摘要： An aircraft with a fuselage and at least one emergency exit system, the at least one emergency exit system including a jettisonable component that is accommodated and locked in an associated frame structure of the aircraft in normal operation mode to form a portion of the fuselage and that is releasable from the associated frame structure for being jettisoned from the aircraft in an emergency mode; and further including an emergency evacuation assistance device that is adapted to assist in an emergency evacuation of the aircraft via the associated frame structure in the emergency mode; wherein the emergency evacuation assistance device is attached to the jettisonable component such that the emergency evacuation assistance device is deployed by means of the jettisonable component when the jettisonable component is jettisoned from the aircraft in the emergency mode.
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公开(公告)号：US11912402B2
公开(公告)日：2024-02-27
申请号：US17666317
申请日：2022-02-07
CPC分类号： B64C27/006 , B64C1/12 , B64C27/00 , B64D27/26 , B64D45/00 , B64C27/06 , B64D2045/009
摘要： A rotary wing aircraft with a fuselage that forms an aircraft interior region, the fuselage comprising an upper primary skin that separates the aircraft interior region from an aircraft upper deck arranged above the fuselage, wherein the aircraft upper deck comprises an engine accommodating region with a firewall arrangement, the engine accommodating region accommodating at least one aircraft engine within the firewall arrangement, wherein the firewall arrangement comprises at least one gasket for tightening pass-through of a torque tube that connects the at least one aircraft engine to a main gear box of the rotary wing aircraft, and wherein the at least one gasket comprises at least two fire proof shells and a ring-shaped flexible fire proof bellows.
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