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公开(公告)号：US10889382B2
公开(公告)日：2021-01-12
申请号：US15842023
申请日：2017-12-14
发明人： Valerie Briand
摘要： A pneumatic deicing device (1) is provided for breaking and removing an ice deposit accumulated on the outer surface (2) of an aircraft, in particular on an airplane wing. The device (1) includes an outer layer (15) intended to withstand the outside environment, an inner interface layer (50) intended to be connected to the outer surface (2) of the aircraft, and at least two outer (30) and inner (40) intermediate layers connected to one another by an array of stitches (36) so as to define deicing chambers (35) that can be inflated quickly to cause a mechanical action to break the ice. The outer intermediate layer (30) includes a knit textile layer (34). At least one interlayer (20; 32) made from polar elastomer material is arranged above the knit textile layer (34) and immediately in contact with the outer layer (15) and the knit textile layer (34).
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公开(公告)号：US10197753B2
公开(公告)日：2019-02-05
申请号：US15489991
申请日：2017-04-18
发明人： Yannick Pelletier
摘要： A connector joins the core of at least one optical fiber to the core of another fiber in a manner that is functional and leaktight against the external media, including: a cylindrical body, whose inner portion includes an insert provided with longitudinal through-holes or through-conduits; at least one optical linkage device including a cylindrical ferrule, generally made of ceramic, pierced for the passage of the core of the fiber, and a ferrule holder joined to the end of the associated fiber and providing the mechanical linkage between the ferrule and the insert; and an O-ring seal provided between the ferrule holder and the receiving conduit of the insert. The body of the connector and the insert form a monobloc assembly, either realized as a single piece or realized with the aid of two complementary pieces, fixed to each other in a totally leaktight or hermetic fashion.
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公开(公告)号：US09573666B2
公开(公告)日：2017-02-21
申请号：US14740351
申请日：2015-06-16
发明人： Jean-Yves Rivault
IPC分类号： B63B43/14 , B63B7/06 , B63B39/03 , B63B43/04 , B63B43/06 , B64C25/54 , B64C25/56 , B64D25/18 , B64C25/32
CPC分类号： B63B43/14 , B63B7/06 , B63B39/03 , B63B43/04 , B63B43/06 , B64C25/54 , B64C25/56 , B64C2025/325 , B64D25/18
摘要： The invention generally relates to devices for stabilizing floating structures and systems and methods utilizing such stabilization devices. Some embodiments of the stabilization device include a fabric material having a collapsed configuration and an expanded configuration. The expanded configuration of the fabric material may form a column of the fabric material. The column of fabric material may define an internal volume. The front end of the column of fabric material may be closed, and the back end of the column of fabric material may define an opening for receiving water for filling the internal volume. When filled with water, the stabilization device may improve roll stabilization of a floating structure. The floating structure may be a flotation device of an emergency flotation system, boat, or inflatable raft, for example. The emergency flotation system may be used with aircraft, (e.g., helicopters) to provide stabilization when the aircraft is ditched in water.
摘要翻译： 本发明一般涉及用于稳定浮动结构的装置和利用这种稳定装置的系统和方法。 稳定装置的一些实施例包括具有折叠构型和扩展构型的织物材料。 织物材料的膨胀构型可以形成织物材料的柱。 织物材料柱可以定义内部体积。 织物材料柱的前端可以是封闭的，并且织物材料柱的后端可以限定用于接收用于填充内部容积的水的开口。 当充满水时，稳定装置可以改善浮动结构的滚动稳定性。 浮动结构可以是例如紧急浮选系统，船或充气筏的浮选装置。 紧急浮选系统可以与飞机（例如直升机）一起使用，以便在飞机在水中飞溅时提供稳定性。
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公开(公告)号：US20160325842A1
公开(公告)日：2016-11-10
申请号：US15109336
申请日：2015-01-21
发明人： Loic Boissy
CPC分类号： B64D15/166
摘要： Embodiments of the present disclosure relate generally to systems and methods for de-icing an aircraft surface (14). The systems create a shock pulse to create a shock activation. The shock pressure is designed to deform the surface of an erosion shield (16) on the surface in order to expulse ice from the wing. The deformation may be between a negative to a positive shape. In one example, the de-icing occurs from a pulse delivered by pressurized fluid injected into and quickly removed from a recess (12) between the aircraft surface and an erosion shield. A pulse of pressurized air or fluid may be injected into one or more cells (32) formed in the recess, together or alternately, according to the desired effect on the erosion shield surface.
摘要翻译： 本公开的实施例总体上涉及用于使飞行器表面（14）除冰的系统和方法。 系统产生冲击脉冲以产生冲击激活。 冲击压力被设计成使表面上的侵蚀屏蔽（16）的表面变形，以便从机翼中消除冰。 变形可以在负形状到正形状之间。 在一个示例中，除冰从由喷射入飞行器表面和侵蚀屏蔽之间的凹部（12）中并被快速移除的加压流体输送的脉冲发生。 加压空气或流体的脉冲可以根据对侵蚀屏蔽表面的期望效果一起或交替地注入到形成在凹部中的一个或多个单元（32）中。
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公开(公告)号：US20150360758A1
公开(公告)日：2015-12-17
申请号：US14740351
申请日：2015-06-16
发明人： Jean-Yves Rivault
CPC分类号： B63B43/14 , B63B7/06 , B63B39/03 , B63B43/04 , B63B43/06 , B64C25/54 , B64C25/56 , B64C2025/325 , B64D25/18
摘要： The invention generally relates to devices for stabilizing floating structures and systems and methods utilizing such stabilization devices. Some embodiments of the stabilization device include a fabric material having a collapsed configuration and an expanded configuration. The expanded configuration of the fabric material may form a column of the fabric material. The column of fabric material may define an internal volume. The front end of the column of fabric material may be closed, and the back end of the column of fabric material may define an opening for receiving water for filling the internal volume. When filled with water, the stabilization device may improve roll stabilization of a floating structure. The floating structure may be a flotation device of an emergency flotation system, boat, or inflatable raft, for example. The emergency flotation system may be used with aircraft, (e.g., helicopters) to provide stabilization when the aircraft is ditched in water.
摘要翻译： 本发明一般涉及用于稳定浮动结构的装置和利用这种稳定装置的系统和方法。 稳定装置的一些实施例包括具有折叠构型和扩展构型的织物材料。 织物材料的膨胀构型可以形成织物材料的柱。 织物材料柱可以定义内部体积。 织物材料柱的前端可以是封闭的，并且织物材料柱的后端可以限定用于接收用于填充内部容积的水的开口。 当充满水时，稳定装置可以改善浮动结构的滚动稳定性。 浮动结构可以是例如紧急浮选系统，船或充气筏的浮选装置。 紧急浮选系统可以与飞机（例如直升机）一起使用，以便在飞机在水中飞溅时提供稳定性。
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公开(公告)号：US20150274311A1
公开(公告)日：2015-10-01
申请号：US14668701
申请日：2015-03-25
发明人： Valérie Briand
CPC分类号： B64D37/32 , B32B1/02 , B32B5/024 , B32B27/065 , B32B27/12 , B32B2250/40 , B32B2262/0269 , B32B2262/0276 , B32B2262/101 , B32B2262/106 , B32B2307/558 , B32B2307/702 , B32B2605/00 , B64D37/06 , D03D15/00 , Y02T50/44
摘要： Embodiments of the present invention relate generally to fuel tanks for aviation, and particularly to construction of rigid tank walls that have been found useful in absorbing energy of a magnitude expected during a crash. In some aspects, the rigid tank wall construction includes particular materials, such as a thermoplastic resin matrix. In some aspects, the rigid tank wall construction includes a particular arrangement of reinforcing fibers, such as a twill weave pattern.
摘要翻译： 本发明的实施例一般涉及用于航空的燃料箱，特别涉及用于吸收在碰撞期间预期的大小的能量的刚性罐壁的结构。 在一些方面，刚性罐壁结构包括特定材料，例如热塑性树脂基体。 在一些方面，刚性罐壁结构包括加强纤维的特定布置，例如斜纹组织图案。
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