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公开(公告)号：US20220405910A1
公开(公告)日：2022-12-22
申请号：US17667718
申请日：2022-02-09
摘要： A method, comprising: providing a light source, a high contrast providing object, and an image acquisition device; emitting 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 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 a series of images over time of the high contrast providing object using the image acquisition device; determining blur occurring in the series of images over the time; and quantifying 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：US11148826B2
公开(公告)日：2021-10-19
申请号：US16702781
申请日：2019-12-04
发明人： Valerie Juppet , Fanny Stutzmann , Marie Charbonneau , Jorrit Van Der Spek , Olga Gonzalez-Valbuena
摘要： Controlling and reconfiguring a display system that includes at least two screens that are installed in a cockpit of an aircraft in case of a failure of one of the screens. For example, a control unit of the display system may detect occurrence of a screen failure. In response to detecting the screen failure, the control unit may determine whether a critical flight relevant information has not been displayed on an operational screen during a predetermined period of time, and in response to determining that the critical flight relevant information has not been displayed on the operational screen during the predetermined period of time, command display of a message on the operational screen that suggests displaying the critical flight relevant information on the operational screen.
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公开(公告)号：US10787264B2
公开(公告)日：2020-09-29
申请号：US15964149
申请日：2018-04-27
摘要： A vibration filter mechanism between a fuselage and a piece of equipment of the aircraft. The filter mechanism comprises a pair of filter members, each secured with a first structure that is to be connected to the fuselage and with a second structure of the piece of equipment. Each filter member is secured with the first structure via a first pivot type connection having one degree of freedom to move in rotation and with the second structure via a second pivot type connection having one degree of freedom to move in rotation. The filter mechanism includes resilient return means for deforming during relative movement in rotation between at least one of the filter members and the first structure. The resilient return means presents a predetermined stiffness suitable for generating a return force opposing the relative movement in rotation between at least one of the filter members and the first structure.
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公开(公告)号：US20200277082A1
公开(公告)日：2020-09-03
申请号：US16802967
申请日：2020-02-27
摘要： A haptic alert mechanism. The mechanism includes an actuator. At least one arm of a movable stopping piece is connected to the actuator. A spring box is provided with an enclosure containing a pre-stressed torsion spring, said spring box being mounted to be movable in rotation about the axis of rotation. The enclosure includes at least one lug that is mounted to be movable in rotation about said axis of rotation. A finger of the torsion spring passes through an elongate orifice in a front flank of the enclosure to form a movable, resilient stop that is overridable.
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公开(公告)号：US20200239157A1
公开(公告)日：2020-07-30
申请号：US16702781
申请日：2019-12-04
发明人： Valerie JUPPET , Fanny STUTZMANN , Marie CHARBONNEAU , Jorrit VAN DER SPEK , Olga GONZALEZ-VALBUENA
摘要： Controlling and reconfiguring a display system that includes at least two screens that are installed in a cockpit of an aircraft in case of a failure of one of the screens. For example, a control unit of the display system may detect occurrence of a screen failure. In response to detecting the screen failure, the control unit may determine whether a critical flight relevant information has not been displayed on an operational screen during a predetermined period of time, and in response to determining that the critical flight relevant information has not been displayed on the operational screen during the predetermined period of time, command display of a message on the operational screen that suggests displaying the critical flight relevant information on the operational screen.
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公开(公告)号：US20180312259A1
公开(公告)日：2018-11-01
申请号：US15964149
申请日：2018-04-27
IPC分类号： B64D11/06
摘要： A vibration filter mechanism between a fuselage and a piece of equipment of the aircraft. The filter mechanism comprises a pair of filter members, each secured with a first structure that is to be connected to the fuselage and with a second structure of the piece of equipment. Each filter member is secured with the first structure via a first pivot type connection having one degree of freedom to move in rotation and with the second structure via a second pivot type connection having one degree of freedom to move in rotation. The filter mechanism includes resilient return means for deforming during relative movement in rotation between at least one of the filter members and the first structure. The resilient return means presents a predetermined stiffness suitable for generating a return force opposing the relative movement in rotation between at least one of the filter members and the first structure.
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公开(公告)号：US20160355249A1
公开(公告)日：2016-12-08
申请号：US15169906
申请日：2016-06-01
发明人： Fabrice JOUSSELLIN , Aurelien VAYSSIERE , Pierre FRUITET , Laure-Anne MATHIEU , Hassene HEBOUB , Philippe BENENTENDI
摘要： 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.
摘要翻译： 一种用于车辆的可抛弃的紧急出口，包括适于容纳在设置在车辆中的相关联的框架中的外周边缘，其中至少一个紧急出口保持装置和至少一个紧急出口锁定装置集成到外周边 所述至少一个紧急出口保持装置包括至少一个不可缩回的枢转指状物，所述可坠毁的紧急出口在紧急模式下围绕所述至少一个不可缩回的枢轴指，所述至少一个紧急出口锁定装置包括至少一个适于 用于在正常操作模式下将可坠毁的紧急出口锁定在相关联的锁定位置中，并且用于在紧急模式下将可坠毁的紧急出口释放在相关联的缩回位置。
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8.发明申请DEVICE FOR PROTECTING AN INDIVIDUAL SITTING ON A SEAT, A SEAT, AND A VEHICLE 有权用于保护座椅，座椅和车辆上的个人座椅的装置公开(公告)号：US20150259071A1
公开(公告)日：2015-09-17
申请号：US14641498
申请日：2015-03-09
发明人： Tomas SANTANA-GALLEGO , Ulf GRUENE
IPC分类号： B64D11/06 , B60R21/233 , B60R21/261 , B60R21/18
CPC分类号： B64D11/0621 , B60R21/18 , B60R21/233 , B60R21/261 , B60R2021/0093 , B60R2021/23308 , B60R2022/027 , B64D11/06 , B64D11/062 , B64D11/06205 , B64D25/06
摘要： A protection device having a set of inflatable protection members including a neck airbag, a left lower airbag, a left upper airbag, a right lower airbag, and a right upper airbag. The protection device has a lower pocket provided with a lower base forming the neck airbag and two lower lateral branches forming the left lower airbag and the right lower airbag. An upper pocket at least partially secured to the lower pocket is provided with an upper base forming a head airbag and two upper lateral branches forming the left upper airbag and the right upper airbag. At least one longitudinal internal wall provide at least two “tubes” in each upper airbag, the upper pocket being in fluid flow communication with the lower pocket.
摘要翻译： 一种保护装置，具有一组充气保护构件，包括颈部安全气囊，左下部安全气囊，左上部安全气囊，右侧气囊和右侧上部安全气囊。 保护装置具有下部凹口，其具有形成颈部安全气囊的下部底座和形成左下部安全气囊的右下部分支和右侧下部安全气囊。 至少部分地固定到下部口袋的上部口袋设置有形成头部安全气囊的上部基座和形成左上部安全气囊和右上部安全气囊的两个上部横向分支。 至少一个纵向内壁在每个上部安全气囊中提供至少两个“管”，上部袋与下部凹槽流体连通。
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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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