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公开(公告)号：US11999469B2
公开(公告)日：2024-06-04
申请号：US17350609
申请日：2021-06-17
发明人： Axel Fink , Pierre Pardoux , Dominique Mailliu
CPC分类号： B64C27/26 , B64C39/068 , B64D25/18
摘要： A compound helicopter with braced wings in joined-wing configuration, a fuselage that extends from a front fuselage section to a rear fuselage section, and an emergency floatation system with main floatation balloons and lateral floatation wherein balloons, the main floatation balloons comprise at least one front floatation balloon that is arranged in the front fuselage section and at least one rear floatation balloon that is arranged in the rear fuselage section, and wherein the lateral floatation balloons comprise at least one first lateral floatation balloon that is arranged close to an interconnection region of the first braced wing and at least one second lateral floatation balloon that is arranged close to an interconnection region of the second braced wing.
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公开(公告)号：US20240003171A1
公开(公告)日：2024-01-04
申请号：US18121050
申请日：2023-03-14
CPC分类号： E05C3/045 , E05C3/004 , B64C1/1438
摘要： The disclosure relates to a door locking assembly for locking a door of an aircraft, comprising a locking hook adapted for blocking in a locking position a lockable arm of a door of an aircraft; a release lever connected to the locking hook for moving the locking hook from a releasing position into the locking position in response to being actuated by a lockable arm of a door of an aircraft; an operating handle connected at least to the release lever and rotatable for moving the locking hook from the locking position to the releasing position; and a locking indicator connected to the locking hook for indicating positioning of the locking hook in one of the locking position or the releasing position.
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公开(公告)号：US20230192279A1
公开(公告)日：2023-06-22
申请号：US17989077
申请日：2022-11-17
发明人： Jerome GENEIX , Mikolaj LUSZCZYNSKI
CPC分类号： B64C27/24 , B64D27/24 , B64D35/00 , B60L53/00 , G05D1/102 , H02K7/14 , H01M10/46 , B60L2200/10 , H01M2220/20
摘要： A rotary wing aircraft that extends along a roll axis between a nose region and an aft region, comprising: at least one first single-blade rotor and at least one second single-blade rotor which are spaced apart from each other along the roll axis; at least one first electric machine and at least one second electric machine which are at least configured to drive in motor mode the at least one first single-blade rotor and the at least one second single-blade rotor for generating lift in hover condition of the rotary wing aircraft; at least one propulsion device that is at least configured to generate forward thrust in forward flight condition of the rotary wing aircraft; and a fixed-wing arrangement that is at least configured to provide lift in the forward flight condition.
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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：US20220389943A1
公开(公告)日：2022-12-08
申请号：US17722470
申请日：2022-04-18
发明人： Gregor PAULMANN , Genevieve MKADARA
IPC分类号： F15B19/00
摘要： A failure detection apparatus for a hydraulic system, to a hydraulic, failure detection-capable system, and to a method of operating a failure detection apparatus. The failure detection apparatus comprises a monitoring and failure detection unit that receives first and second pressure values from first and second pressure sensors and comprises a failure detection unit that detects a failure of at least one hydraulically operated device when a 2-tuple of a plurality of 2-tuples is within a first and outside a second predetermined tolerance range of relative pressure values, and wherein the failure detection unit 260 detects a failure of the pump when a 2-tuple of the plurality of 2-tuples is outside the first predetermined tolerance range of relative pressure values.
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公开(公告)号：US20220161915A1
公开(公告)日：2022-05-26
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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7.发明申请公开(公告)号：US20210122393A1
公开(公告)日：2021-04-29
申请号：US16898685
申请日：2020-06-11
发明人： Boris GROHMANN , Thomas ROHR , Nicolas AVRIL , Axel GUSE
摘要： A vehicle control system for controlling a vehicle and to a method of operating such a vehicle control system. The vehicle control system may include an inceptor adapted for controlling a servo-assisted control unit via a mechanical linkage first and second force generating devices that are mechanically connected to the inceptor in parallel and provided for generating respective first and second forces that act in operation on the inceptor, a hands-on/off detection management unit, and a decoupling device that mechanically decouples the second force generating device from the inceptor based on a control signal from the hands-on/off detection management unit.
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公开(公告)号：US20240182160A1
公开(公告)日：2024-06-06
申请号：US18233637
申请日：2023-08-14
发明人： Axel FINK , Aurelien ACHARD , Didier BERTIN
CPC分类号： B64C25/36 , B64C25/58 , B64C2025/325
摘要： A rotorcraft with at least one non-retractable wheel-type landing gear and a fuselage comprising a lower shell, an inner floor, and at least one lower fuselage compartment arranged between the inner floor and the lower shell, wherein the at least one non-retractable wheel-type landing gear is rigidly attached in the at least one lower fuselage compartment and comprises: at least one wheel; a shock absorber connected to the at least one wheel and comprising a shock absorber tube and a shock absorber rod telescopically mounted to the shock absorber tube; at least two mounting arms extending laterally from the shock absorber tube; and a mounting pin extending from the shock absorber tube toward a floor fitting provided at the inner floor, wherein the mounting pin is connected to the floor fitting.
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公开(公告)号：US20240035314A1
公开(公告)日：2024-02-01
申请号：US18121119
申请日：2023-03-14
CPC分类号： E05B77/38 , B64C1/1407 , B64C27/04
摘要： An aircraft door with an inner door space; a door opening system arranged at least partly in the inner door space. The door opening system comprises: at least one locking device for locking the aircraft door in a locked state, actuation kinematics for actuating the at least one locking device, and at least one transmission rod coupling the actuation kinematics with the at least one locking device; wherein the at least one transmission rod is displaceable in the inner door space by means of the actuation kinematics for actuating the at least one locking device; and an anti-vibration device mounted in the inner door space to the at least one transmission rod for absorbing vibrations of the at least one transmission rod, wherein the anti-vibration device is displaceable in the inner door space together with the at least one transmission rod.
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公开(公告)号：US11739771B2
公开(公告)日：2023-08-29
申请号：US17722470
申请日：2022-04-18
发明人： Gregor Paulmann , Genevieve Mkadara
IPC分类号： F15B19/00
CPC分类号： F15B19/005 , F15B2211/6306 , F15B2211/857 , F15B2211/863
摘要： A failure detection apparatus for a hydraulic system, to a hydraulic, failure detection-capable system, and to a method of operating a failure detection apparatus. The failure detection apparatus comprises a monitoring and failure detection unit that receives first and second pressure values from first and second pressure sensors and comprises a failure detection unit that detects a failure of at least one hydraulically operated device when a 2-tuple of a plurality of 2-tuples is within a first and outside a second predetermined tolerance range of relative pressure values, and wherein the failure detection unit 260 detects a failure of the pump when a 2-tuple of the plurality of 2-tuples is outside the first predetermined tolerance range of relative pressure values.
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