公开(公告)号：US11603180B2

公开(公告)日：2023-03-14

申请号：US17109355

申请日：2020-12-02

Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH ,  AIRBUS HELICOPTERS

Inventor： Aurelien Vayssiere ,  Bernhard Rein ,  Sven Laessig ,  Hubert Neukirch ,  Pierre Fruitet

IPC: B64C1/32 ,  B64D25/08 ,  B64C27/04 ,  B64C1/14

Abstract: 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.

公开(公告)号：US10807706B2

公开(公告)日：2020-10-20

申请号：US15169906

申请日：2016-06-01

Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH ,  AIRBUS HELICOPTERS

Inventor： Fabrice Joussellin ,  Aurelien Vayssiere ,  Pierre Fruitet ,  Laure-Anne Mathieu ,  Hassene Heboub ,  Philippe Benentendi

IPC: B64C1/32 ,  B64C27/04 ,  B64C1/14

Abstract: A jettisonable emergency exit for a vehicle, comprising an outer peripheral edge that is adapted to be accommodated in an associated frame provided in a vehicle, wherein at least one emergency exit retention means and at least one emergency exit locking device are integrated into the outer peripheral edge, the at least one emergency exit retention means comprising at least one non-retractable pivot finger around which the jettisonable emergency exit is rotatable in an emergency mode, and the at least one emergency exit locking device comprising at least one locking hook that is adapted for locking the jettisonable emergency exit in an associated locking position in normal operation mode and for releasing the jettisonable emergency exit in an associated retracted position in the emergency mode.

公开(公告)号：US11655017B2

公开(公告)日：2023-05-23

申请号：US17350438

申请日：2021-06-17

Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH ,  AIRBUS HELICOPTERS

Inventor： Aurelien Vayssiere ,  Nicolas Montil ,  Mathieu Gester ,  Hubert Neukirch ,  Pascal Jervaise ,  Markus Kammerer ,  Pierre Arnould

IPC: B64C1/06 ,  B64C27/04

CPC classification number: B64C1/061 ,  B64C27/04

Abstract: 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.

公开(公告)号：US10717513B2

公开(公告)日：2020-07-21

申请号：US15814455

申请日：2017-11-16

Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH ,  AIRBUS HELICOPTERS

Inventor： Aurelien Vayssiere ,  Pierre Fruitet ,  Fabrice Joussellin ,  Robert Sienicki ,  Bartlomiej Tazbir ,  Michal Mroz ,  Bernhard Rein

IPC: B64C1/14 ,  E05D15/10 ,  B64C27/04 ,  E05F5/00

Abstract: A rotary wing aircraft with a fuselage that is equipped with at least one rail, comprising at least one sliding element, in particular a sliding door or a sliding window, that is slidably supported by the at least one rail, wherein the at least one sliding element is at least slidable along the at least one rail by means of an opening sliding movement into an opening movement direction from a fully closed position into a fully opened position, wherein a dampening unit is provided that dampens the opening sliding movement of the at least one sliding element upon reaching of the fully opened position.

公开(公告)号：US10066430B2

公开(公告)日：2018-09-04

申请号：US15050530

申请日：2016-02-23

Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH

Inventor： Fabrice Joussellin ,  Aurelien Vayssiere

IPC: E05F11/00 ,  E05D15/06 ,  B64C1/14 ,  E05D15/28 ,  E05D13/00 ,  E06B3/46

Abstract: A sliding closing element for a sliding closing element arrangement of a vehicle, the sliding closing element arrangement comprising at least one rail that is adapted for slidably supporting the sliding closing element, the sliding closing element comprising at least one fail safe sliding arm assembly with at least one bogie support arm and at least one safety arm, the at least one bogie support arm comprising at least one bogie assembly with at least one guide roller that is adapted for rolling along the at least one rail in operation, and the at least one safety arm being adapted for retaining the at least one fail safe sliding arm assembly on the at least one rail in case of a failure of the at least one bogie support arm.

公开(公告)号：US11912402B2

公开(公告)日：2024-02-27

申请号：US17666317

申请日：2022-02-07

Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH

Inventor： Aurelien Vayssiere ,  Hubert Neukirch ,  Markus Kammerer ,  Bernhard Rein

IPC: B64C27/00 ,  B64C1/12 ,  B64D27/26 ,  B64D45/00 ,  B64C27/06

CPC classification number: B64C27/006 ,  B64C1/12 ,  B64C27/00 ,  B64D27/26 ,  B64D45/00 ,  B64C27/06 ,  B64D2045/009

Abstract: 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.