公开(公告)号：US09156558B2

公开(公告)日：2015-10-13

申请号：US13174659

申请日：2011-06-30

Applicant: Ronald A. Shields ,  Peter A. Settles ,  Willard F. Hagan ,  Giuseppe Gullotto

Inventor： Ronald A. Shields ,  Peter A. Settles ,  Willard F. Hagan ,  Giuseppe Gullotto

IPC: G05B23/02 ,  B64D25/02 ,  B64D25/00 ,  B64D11/06

CPC classification number: B64D11/0621 ,  B64D11/062 ,  B64D11/06205 ,  B64D25/00 ,  B64D25/02 ,  B64D2201/00 ,  G07C5/0808 ,  G07C5/0841

Abstract: An electronic module assembly (EMA) for use in controlling one or more personal restraint systems. A programmed processor within the EMA is configured to determine when a personal restraint system associated with each seat in a vehicle should be deployed. In addition, the programmed processor is configured to perform a diagnostic self-test to determine if the EMA and the personal restraint systems are operational. In one embodiment, results of the diagnostic self-test routine are displayed on a display included on the electronic module assembly. In an alternative embodiment, the results of the diagnostic self-test routine are transmitted via a wireless transceiver to a remote device. The remote device can include a wireless interrogator or can be a remote computer system such as a cabin management computer system.

Abstract translation: 一种用于控制一个或多个个人约束系统的电子模块组件（EMA）。 EMA内的编程处理器被配置为确定何时应该部署与车辆中的每个座椅相关联的个人约束系统。 此外，编程处理器被配置为执行诊断自检，以确定EMA和个人约束系统是否可操作。 在一个实施例中，诊断自检程序的结果被显示在包括在电子模块组件上的显示器上。 在替代实施例中，诊断自检程序的结果通过无线收发器传送到远程设备。 远程设备可以包括无线询问器，或者可以是诸如客舱管理计算机系统的远程计算机系统。

公开(公告)号：US09045222B2

公开(公告)日：2015-06-02

申请号：US13699758

申请日：2011-03-30

Applicant: Zi Lu ,  Cheng-Ho Tho ,  Michael R. Smith ,  Andrew T. Hill ,  Samgeeth Rajan

Inventor： Zi Lu ,  Cheng-Ho Tho ,  Michael R. Smith ,  Andrew T. Hill ,  Samgeeth Rajan

IPC: B64C25/56 ,  B64C27/00

CPC classification number: B64C27/006 ,  B64D25/00 ,  B64D2201/00

Abstract: The external crash attenuation airbag includes an inflatable bladder which is inflatable to an exterior of an aircraft, so that the inflatable bladder is generally located between the aircraft and a crash surface when inflated. The airbag includes a vent configured to burst at a predefined burst pressure, the vent being located along a side portion of the inflatable bladder. The airbag also includes a vent support located approximate the vent, the vent support being configured to prevent deformation and therefore maintain the effectiveness of a venting area of the vent, and the vent support being rigid and annular and includes an upper portion and a lower portion that are hinged together around the vent.

Abstract translation: 外部碰撞衰减安全气囊包括可膨胀到飞机外部的可膨胀气囊，使得充气气囊通常位于飞行器和膨胀时的碰撞表面之间。 安全气囊包括通气孔，其构造成以预定的突发压力爆裂，所述排气口沿着可充气气囊的侧部分定位。 安全气囊还包括靠近通气口的通气支架，排气口支架构造成防止变形并因此保持通气口通气区域的有效性，并且排气支架是刚性和环形的并且包括上部和下部 它们围绕通风口铰接在一起。

公开(公告)号：US20150102164A1

公开(公告)日：2015-04-16

申请号：US14513508

申请日：2014-10-14

Applicant: AIRBUS HELICOPTERS

Inventor： Louis DELORME ,  Nicolas LAMARCHE ,  David AYACHE ,  Bernard CERTAIN

IPC: B64C25/56

CPC classification number: B64C25/56 ,  B64C2025/325 ,  B64D25/00 ,  B64D2201/00

Abstract: A buoyancy system (10) for an aircraft (1), the buoyancy system (10) being provided with at least one inflatable float (15). The buoyancy system (10) has at least one inflator (25) and at least one actuator (30) interposed between said inflator (25) and a float (15), said actuator (30) having a cylinder (35) and a rod (40) partially received in said cylinder (35). Said rod (40) is secured to a piston (50) defining a first chamber (61) within said cylinder (35) and in fluid flow communication with the inflator (25), and a second chamber (62) within said rod (40) and in fluid flow communication with said float (15), and said piston (50) has a channel (63) to put the first chamber (61) into fluid flow communication with the second chamber (62), said deployment device (20) having a shutter (70) for shutting said channel (63).

Abstract translation: 一种用于飞机（1）的浮力系统（10），所述浮力系统（10）设置有至少一个可充气浮子（15）。 浮力系统（10）具有至少一个充气机（25）和置于所述充气机（25）和浮子（15）之间的至少一个致动器（30），所述致动器（30）具有气缸（35）和杆 （40）部分地容纳在所述气缸（35）中。 所述杆（40）固定到限定所述气缸（35）内的第一室（61）并与所述充气机（25）流体连通的活塞（50），并且所述杆（40）内的第二室（62） ）并且与所述浮子（15）流体连通，并且所述活塞（50）具有通道（63），以将所述第一腔室（61）与所述第二腔室（62）流体连通，所述展开装置（20） ）具有用于关闭所述通道（63）的快门（70）。

公开(公告)号：US08870115B2

公开(公告)日：2014-10-28

申请号：US13641426

申请日：2010-12-29

Applicant: Zi Lu ,  Cheng-Ho Tho ,  Michael R. Smith

Inventor： Zi Lu ,  Cheng-Ho Tho ,  Michael R. Smith

IPC: B64C25/56 ,  B64C25/32

CPC classification number: B64C25/56 ,  B64C25/52 ,  B64C2025/325 ,  B64D2201/00

Abstract: A crash attenuation system has an airbag inflatable generally adjacent to an exterior of the aircraft. The system includes a gas generator in fluid communication with an interior of the airbag. The system also includes a vent system having a vent passage supported by the aircraft, the vent passage being configured to allow gas to escape from within the airbag during an impact. The vent system also includes an actuator door for sealing the vent passage, thereby preventing gas from leaving the airbag. The actuator door is actuated by an actuator, the actuator being in fluid communication with the gas generator through an actuator duct. The system operates such that deployment of gas from the gas generator causes the actuator to inflate, thereby causing the actuator door to seal the vent passage. The gas generator is configured to re-inflate the airbag after the actuator door seals the vent passage.

Abstract translation: 碰撞衰减系统具有通常与飞机外部相邻的气囊充气。 该系统包括与气囊的内部流体连通的气体发生器。 该系统还包括具有由飞行器支撑的通气通道的排气系统，该排气通道构造成允许气体在冲击期间从气囊内逸出。 排气系统还包括用于密封通气通道的致动器门，从而防止气体离开气囊。 致动器门由致动器致动，致动器通过致动器导管与气体发生器流体连通。 系统操作使得来自气体发生器的气体展开使致动器膨胀，从而使致动器门密封通气通道。 气体发生器构造成在致动器门密封通气通道之后再次充气气囊。

公开(公告)号：US08588996B2

公开(公告)日：2013-11-19

申请号：US13380925

申请日：2009-07-27

Applicant: Andrew T. Hill ,  Michael R. Smith ,  Charles E. Covington ,  Nicholas Lappos ,  Walter Sonneborn

Inventor： Andrew T. Hill ,  Michael R. Smith ,  Charles E. Covington ,  Nicholas Lappos ,  Walter Sonneborn

IPC: G05D3/00

CPC classification number: B64D25/00 ,  B64D2201/00

Abstract: An occupant protection system for an aircraft comprising a sensor system for sensing flight condition information and a control system, which includes an impending crash detection system and an impact detection system. The impending crash detection system receives flight information from the sensors determines whether a crash is likely to occur. If an impending crash is detected, the impending crash detection system activates impact modes of a first group of aircraft systems. The impact detection system receives flight information from the sensor system and determines whether an impact has occurred or is occurring. If an impact is detected, the impact detection system activates impact modes of a second group of aircraft systems.

Abstract translation: 一种用于飞行器的乘员保护系统，包括用于感测飞行情况信息的传感器系统和包括即将发生的碰撞检测系统和冲击检测系统的控制系统。 即将发生的碰撞检测系统从传感器接收飞行信息，确定是否可能发生碰撞。 如果检测到即将发生的碰撞，即将发生的碰撞检测系统激活第一组飞行器系统的冲击模式。 冲击检测系统从传感器系统接收飞行信息，并确定影响是否发生或正在发生。 如果检测到冲击，冲击检测系统激活第二组飞行器系统的冲击模式。

公开(公告)号：US08523220B1

公开(公告)日：2013-09-03

申请号：US13424197

申请日：2012-03-19

Applicant: William J. Gehret ,  Joshua Vyrostek ,  Kevin J. Keeslar ,  Daniel Nick Foubert

Inventor： William J. Gehret ,  Joshua Vyrostek ,  Kevin J. Keeslar ,  Daniel Nick Foubert

IPC: B60R21/16 ,  B60R21/20 ,  B64D25/115

CPC classification number: B64D11/0621 ,  B60R21/20 ,  B60R21/231 ,  B60R21/26 ,  B60R2021/0093 ,  B64D11/06 ,  B64D11/0604 ,  B64D11/06205 ,  B64D2201/00

Abstract: Structure mounted airbag assemblies and associated systems and methods are described herein. An airbag system configured in accordance with an embodiment of the present disclosure can include, for example, a housing having a cavity and an opening in communication with the cavity, an airbag assembly within the cavity, and an inflator operably coupled to the airbag assembly. The airbag assembly can include an airbag configured to deploy through the opening of the housing during a crash event. The airbag system can further include a door removably positioned across the opening and configured to move away from the opening during airbag deployment. The housing can be affixed to an interior portion of an aircraft, forward of and offset from an aircraft seat.

Abstract translation: 结构安装的安全气囊组件和相关联的系统和方法在本文中描述。 根据本公开的实施例配置的气囊系统可以包括例如具有空腔和与空腔连通的开口的壳体，腔内的气囊组件以及可操作地联接到气囊组件的充气器。 安全气囊组件可以包括气囊，其构造成在碰撞事件期间部署穿过壳体的开口。 安全气囊系统还可以包括可拆卸地定位成横跨开口并且构造成在气囊展开期间远离开口移动的门。 外壳可以固定在飞行器的内部，在飞机座前方并偏离飞机座。

公开(公告)号：US20130187646A1

公开(公告)日：2013-07-25

申请号：US13608959

申请日：2012-09-10

Applicant: Andre Baca ,  Ronald A. Shields ,  Willard F. Hagan

Inventor： Andre Baca ,  Ronald A. Shields ,  Willard F. Hagan

IPC: G01R33/00

CPC classification number: G01R33/0047 ,  B64D11/062 ,  B64D11/06205 ,  B64D2201/00 ,  G05B9/02 ,  G05B23/0256 ,  Y02T50/46

Abstract: Electronics module assemblies (“EMAs”) for inflatable personal restraints and associated systems are described herein. An EMA configured in accordance with an embodiment of the present technology can include, for example, a housing having a body portion, cover portion that attaches to the body portion to form an enclosure, and protrusion extending outwardly from the cover portion. The protrusion can have an outer boundary at which the protrusion projects away from the cover portion. The EMA can further include a crash sensor within the enclosure in an area defined by the outer boundary of the protrusion. The protrusion can form an envelope of space around the crash sensor that defines a minimum distance an external object with a magnetic field can come to the crash sensor without activating it. The EMA can optionally include a magnetic field configured to disable the crash sensor upon the detection of an external magnetic field.

Abstract translation: 本文描述了用于充气个人约束和相关系统的电子模块组件（“EMA”）。 根据本技术的实施例构造的EMA可以包括例如具有主体部分的壳体，附接到主体部分以形成外壳的盖部分和从盖部分向外延伸的突出部。 突出部可以具有突出部远离盖部突出的外边界。 EMA还可以在外壳内的碰撞传感器包括在突起的外边界限定的区域内。 突起可以形成围绕碰撞传感器的空间的包络，其限定具有磁场的外部物体可以到达碰撞传感器而不激活它的最小距离。 EMA可以可选地包括被配置为在检测到外部磁场时禁用碰撞传感器的磁场。

公开(公告)号：US08480127B2

公开(公告)日：2013-07-09

申请号：US13032891

申请日：2011-02-23

Applicant: Thomas Rathmann-Ramlow ,  Ulf Grüne

Inventor： Thomas Rathmann-Ramlow ,  Ulf Grüne

IPC: B60R21/18

CPC classification number: B60R21/18 ,  B60R22/26 ,  B64D11/062 ,  B64D11/06205 ,  B64D2201/00

Abstract: A restraint system for occupants of a vehicle, comprising a belt; an airbag unit arranged on the belt, wherein the positions of the belt and the airbag unit can be shifted with respect to each other; an airbag in the airbag unit; and means for securing the position of the airbag on the belt, i.e., means by which the airbag and the belt can be fastened together upon deployment of the airbag without the possibility of a shift in their relative positions.

Abstract translation: 一种用于车辆乘员的约束系统，包括皮带; 布置在所述带上的气囊单元，其中所述带和所述气囊单元的位置可以相对于彼此移位; 气囊单元中的气囊; 以及用于将气囊的位置固定在皮带上的装置，即，在安全气囊展开时，气囊和皮带可以紧固在一起的装置，而不会有相对位置的变化的可能性。

公开(公告)号：US20130068883A1

公开(公告)日：2013-03-21

申请号：US13699758

申请日：2011-03-30

Applicant: Zi Lu ,  Cheng-Ho Tho ,  Michael R. Smith ,  Andrew T. Hill ,  Samgeeth Rajan

Inventor： Zi Lu ,  Cheng-Ho Tho ,  Michael R. Smith ,  Andrew T. Hill ,  Samgeeth Rajan

IPC: B60R21/239 ,  B64C25/56

CPC classification number: B64C27/006 ,  B64D25/00 ,  B64D2201/00

Abstract: The external crash attenuation airbag includes an inflatable bladder which is inflatable to an exterior of an aircraft, so that the inflatable bladder is generally located between the aircraft and a crash surface when inflated. The airbag includes a vent configured to burst at a predefined burst pressure, the vent being located a side portion of the inflatable bladder. The airbag also includes a vent support located approximate the vent, the vent support being configured to prevent deformation and therefore maintain the effectiveness of a venting area of the vent.

Abstract translation: 外部碰撞衰减安全气囊包括可膨胀到飞机外部的可膨胀气囊，使得充气气囊通常位于飞行器和膨胀时的碰撞表面之间。 安全气囊包括通气孔，其被构造成以预定的突发压力爆裂，通气口位于可膨胀气囊的侧部。 安全气囊还包括靠近通气口的排气口支架，排气口支撑件构造成防止变形并因此保持排气口通气区域的有效性。

公开(公告)号：US20120068015A1

公开(公告)日：2012-03-22

申请号：US13229909

申请日：2011-09-12

Applicant: Laurent Dock

Inventor： Laurent Dock

IPC: B64D25/00 ,  G06F19/00 ,  B64D11/00

CPC classification number: B64D25/00 ,  B64D2201/00

Abstract: A method of activating protection means (1) via activator means (3) in order to protect the physical integrity of an occupant of an aircraft (10) during an accident, the aircraft being associated with a rectangular coordinate system comprising a longitudinal axis (X), a transverse axis (Y), and an elevation axis (Z), in which method said protection means (1) are activated when, firstly the acceleration of said aircraft (10) along a particular axis (X, Y, Z) of the coordinate system of the aircraft (10) is greater than a first variable threshold, and secondly when the speed variation of the aircraft along said particular axis (X, Y, Z) is greater than a second variable threshold, the first variable threshold and the second variable threshold each varying as a function of the stage of flight of the aircraft (10) in such a manner as to be minimized during predetermined accident-prone stages of flight.

Abstract translation: 一种通过激活器装置（3）激活保护装置（1）的方法，以便在事故期间保护飞机（10）的乘客的身体完整性，飞机与包括纵向轴线（X）的直角坐标系相关联 ），横轴（Y）和仰角轴（Z），其中当所述飞机（10）沿着特定轴线（X，Y，Z）的加速度时，所述保护装置（1）被激活， （10）的坐标系大于第一可变阈值，其次当沿着所述特定轴（X，Y，Z）的飞行器的速度变化大于第二可变阈值时，第一可变阈值 并且所述第二可变阈值各自随着所述飞行器（10）的飞行阶段的函数而变化，以便在预定的事故容易发生的阶段期间被最小化。