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公开(公告)号：EP4382415A1
公开(公告)日：2024-06-12
申请号：EP22315307.3
申请日：2022-12-06
发明人： Fink, Axel , Achard, Aurélien , Bertin, Didier
摘要： A rotorcraft with at least one non-retractable wheel-type landing gear (8) and a fuselage comprising a lower shell, an inner floor (14), and at least one lower fuselage compartment arranged between the inner floor (14) and the lower shell, wherein the at least one non-retractable wheel-type landing gear (8) is rigidly attached in the at least one lower fuselage compartment and comprises: at least one wheel; a shock absorber (8b) connected to the at least one wheel and comprising a shock absorber tube (8c) and a shock absorber rod (8d) telescopically mounted to the shock absorber tube (8c); at least two mounting arms (8e) extending laterally from the shock absorber tube (8c); and a mounting pin device (12) extending laterally from the shock absorber tube (8c) and comprising a mounting pin (16) connected to a floor fitting provided at the inner floor (14).
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公开(公告)号：EP4378834A1
公开(公告)日：2024-06-05
申请号：EP23200826.8
申请日：2023-09-29
摘要： La présente invention concerne un procédé pour paramétrer dans un aéronef (1) une masse de calcul relative à une charge à transporter (15) par un système d'accrochage (5) de l'aéronef (1). Le procédé comporte : détection qu'un état courant de l'aéronef (1) est un état de vol avec la charge à transporter (15) attachée au système d'accrochage (5), dans l'affirmative, affichage sur un afficheur (25) d'une proposition de masse (27), validation de la proposition de masse (27) à l'aide d'une interface de validation (35) pour affecter la proposition de masse (27) à la masse de calcul, ou en l'absence d'une validation de la proposition de masse (27) à l'issue d'une condition prédéterminée, affection d'une masse prédéterminée à la masse de calcul.
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公开(公告)号：EP4311762A1
公开(公告)日：2024-01-31
申请号：EP22400007.5
申请日：2022-07-29
摘要： The invention relates to an aircraft door (7) with an inner door space (7d); a door opening system (8) arranged at least partly in the inner door space, comprising: at least one locking device (8c) for locking the aircraft door in a locked state, actuation kinematics (8b) for actuating the at least one locking device, and at least one transmission rod (8d) 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 (9) 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：EP4289731A2
公开(公告)日：2023-12-13
申请号：EP23206166.3
申请日：2020-12-02
发明人： FINK, Axel , PARDOUX, Pierre , MAILLIU, Dominique
IPC分类号： B64C39/06
摘要： The present invention relates to a compound helicopter 1 with braced wings 5a, 5b in joined-wing configuration, a fuselage 4 that extends from a front fuselage section 4a to a rear fuselage section 4b, and an emergency floatation system 3 with main floatation balloons 14a, 14b, 15a, 15b and lateral floatation balloons 16a, 16b, wherein the main floatation balloons comprise at least one front floatation balloon 14a, 14b that is arranged in the front fuselage section 4a and at least one rear floatation balloon 15a, 15b that is arranged in the rear fuselage section 4b, and wherein at least one first lateral floatation balloon 16a is mounted to the first lower wing 7a, or to the first upper wing 6a; and the at least one second lateral floatation balloon 16b mounted to the second lower wing 7b, or to the second upper wing 6b.
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公开(公告)号：EP4109400A1
公开(公告)日：2022-12-28
申请号：EP21400014.3
申请日：2021-06-22
摘要： The invention is related to a method 400, comprising: providing (S410) a light source, a high contrast providing object, and an image acquisition device; emitting (S420) a light beam from the light source through the high contrast providing object, a transparent object and a surface of the transparent object toward the image acquisition device; exposing (S430) the surface of the transparent object to icing conditions such that a layer of ice is formed by ice accretion on the surface, wherein the light beam traverses the layer of ice after having traversed the transparent object; acquiring (S440) a series of images over time of the high contrast providing object using the image acquisition device; determining (S450) blur occurring in the series of images over the time; and quantifying (S460) the loss of visibility over the time through the transparent object on the basis of the determined blur.
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公开(公告)号：EP4098889A1
公开(公告)日：2022-12-07
申请号：EP21400010.1
申请日：2021-06-02
IPC分类号： F15B19/00
摘要： The present embodiments relate to a failure detection apparatus 200 for a hydraulic system 100, to a hydraulic, failure detection-capable system 10, and to a method of operating a failure detection apparatus 200. The failure detection apparatus 200 comprises a monitoring and failure detection unit 240 that receives first and second pressure values from first and second pressure sensors 210, 220 and comprises a failure detection unit 260 that detects a failure of at least one hydraulically operated device 130 when a 2-tuple of a plurality of 2-tuples 341, 342, 343, 344, 345 is within a first and outside a second predetermined tolerance range of relative pressure values 310, 320, and wherein the failure detection unit 260 detects a failure of the pump 160 when a 2-tuple of the plurality of 2-tuples 341, 342, 343, 344, 345 is outside the first predetermined tolerance range of relative pressure values 310.
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公开(公告)号：EP3396196B1
公开(公告)日：2019-12-18
申请号：EP18164123.4
申请日：2018-03-27
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公开(公告)号：EP4431321A1
公开(公告)日：2024-09-18
申请号：EP23315051.5
申请日：2023-03-16
CPC分类号： B60J1/16 , B60J1/007 , B60J1/1853 , B64C1/1492 , B64D13/00 , B64C27/04
摘要： The invention relates to a window (6) for a vehicle (1) with a main window pane (6a) having a vent window opening (6b), and a vent window assembly (7) mounted to the main window pane. The vent window assembly comprises: a movable vent window pane (7a) adapted for closing the vent window opening in closed state of the vent window assembly; a first vent window frame assembly (8) comprising a first support frame (8a) arranged on a first surface (6c) of the main window pane; and a second vent window frame assembly (10) comprising a second support frame (10a) arranged on a second surface (6d) of the main window pane, wherein the second vent window frame assembly is rigidly attached to the first vent window frame assembly at the vent window opening such that the first and second vent window frame assemblies fasten each other at the main window pane.
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公开(公告)号：EP4345318A1
公开(公告)日：2024-04-03
申请号：EP22315219.0
申请日：2022-09-27
发明人： Le Cadet, Yann , Mora, Paul
摘要： The invention is related to an adjustable spacer (1) for adjusting a spacing between a first component and a second component to a predefined distance, comprising: a support component (2) configured to be rigidly mounted to the first component; a spacing component (3) movably mounted to the support component (2) for adjusting positioning of the support component (2) relative to the second component; and a fixing component (4) configured for locking the spacing component (3) on the support component (2) after the positioning of the support component (2) relative to the second component at the predefined distance.
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公开(公告)号：EP4197906A1
公开(公告)日：2023-06-21
申请号：EP21315280.4
申请日：2021-12-16
摘要： The present invention relates to a rotary wing aircraft 100 that extends along a roll axis R between a nose region 101 and an aft region 102, comprising: at least one first single-blade rotor 120 and at least one second single-blade rotor 130 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 120 and the at least one second single-blade rotor 130 for generating lift in hover condition of the rotary wing aircraft; at least one propulsion device 140 that is at least configured to generate forward thrust in forward flight condition of the rotary wing aircraft; and a fixed-wing arrangement 150 that is at least configured to provide lift in the forward flight condition.
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