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    APPARATUS FOR IMPROVING THE CRASHWORTHINESS OF AIRCRAFT FLUID SYSTEMS
    1.
    发明公开
    APPARATUS FOR IMPROVING THE CRASHWORTHINESS OF AIRCRAFT FLUID SYSTEMS 有权
    用于改善飞机流体系统的易碎性的装置

    公开(公告)号：EP3296214A1

    公开(公告)日：2018-03-21

    申请号：EP16196094.3

    申请日：2016-10-27

    Applicant: Bell Helicopter Textron Inc.

    Inventor： PLAGIANOS, Nicholas James ,  PERYEA, Martin ,  DICKISON, Steve ,  PUJOL, Michael ,  REYNOLDS, Robert

    IPC: B64D37/08 ,  B64D37/00

    CPC classification number: B64C1/10 ,  B64D37/005 ,  B64D37/06 ,  B64D37/08 ,  B64D37/32

    Abstract: A fluid connection system (320) for fluidly connecting a pair of fluid reservoirs, such as fuel cells (302, 304, 306, 308), includes a bellowed portion (322) surrounding a connection portion (330) through which fluid can flow between the two reservoirs. The bellowed portion (322) allows for relative movement between the two reservoirs without breaking the fluid-tight connection between the two reservoirs. Also, a guard member (340) surrounds at least some of the outer periphery of the bellowed portion (322). The guard member (340) serves as a shield around the fluid-tight connection and bellowed portion (322), and thereby helps prevent damage to the fluid-tight connection in the event of a crash or hard landing.

    Abstract translation: 用于流体地连接诸如燃料电池（302,304,306,308）之类的一对流体储存器的流体连接系统（320）包括围绕连接部分（330）的波纹状部分（322），流体可通过该连接部分 两个水库。 波纹部分（322）允许两个储存器之间的相对运动而不破坏两个储存器之间的流体密封连接。 而且，防护构件（340）围绕波纹状部分（322）的至少一些外周。 防护构件340用作围绕流体密封连接和波纹状部分322的防护罩，从而有助于在碰撞或硬着陆的情况下防止流体密封连接的损坏。

    ROTORCRAFT FUEL SYSTEM HAVING ENHANCED CRASH RESISTANCE
    2.
    发明公开
    ROTORCRAFT FUEL SYSTEM HAVING ENHANCED CRASH RESISTANCE 审中-公开
    具有增强的抗冲击性的旋翼燃料系统

    公开(公告)号：EP3241756A1

    公开(公告)日：2017-11-08

    申请号：EP16172307.7

    申请日：2016-05-31

    Applicant: Bell Helicopter Textron Inc.

    Inventor： PERYEA, Martin ,  SMITH, Michael Reaugh ,  HAMELWRIGHT Jr., Douglas ,  BRAND, Albert G. ,  PLAGIANOS, Nicholas J. ,  EMRICH, Joshua ,  CARR, Timothy

    IPC: B64D37/04

    CPC classification number: B64D37/06 ,  B64C27/00 ,  B64C27/04 ,  B64D37/04 ,  B64D37/32

    Abstract: A rotorcraft (10) includes a fuselage (16) having a fuel tank receiving assembly (24) with a fuel tank (28) positioned therein. The fuel tank (28) including a plurality of interconnected fuel bags operable to contain liquid fuel. A network of straps is disposed about the fuel tank (28) forming a restraint assembly (130; 172; 182; 202). The network of straps includes at least one perimeter strap (132, 134, 136, 138, 140) extending at least partially about at least two fuel bags and at least one surrounding strap (142, 144, 146) extending at least partially about the at least two fuel bags. The at least one perimeter strap (132, 134, 136, 138, 140) has at least two intersections (156, 158) with the at least one surrounding strap (142, 144, 146).

    Abstract translation: 一种旋翼飞行器（10）包括具有燃料箱接收组件（24）的机身（16），燃料箱（28）位于其中。 燃料箱（28）包括多个可操作以容纳液体燃料的互连燃料箱。 围绕形成约束组件（130; 172; 182; 202）的燃料箱（28）设置有网带。 所述带的网络包括至少一个周边带（132,134,136,138,140），所述至少一个周边带至少部分地围绕至少两个燃料袋延伸，所述至少一个周围带（142,144,146）至少部分地围绕 至少两个燃料袋。 所述至少一个周边带（132,134,136,138,140）具有与所述至少一个周围带（142,144,146）的至少两个交叉点（156,158）。

    DEPLOYABLE APPARATUS TO PREVENT HELICOPTER ROLLOVER
    4.
    发明公开
    DEPLOYABLE APPARATUS TO PREVENT HELICOPTER ROLLOVER 审中-公开

    公开(公告)号：EP3392142A1

    公开(公告)日：2018-10-24

    申请号：EP17182786.8

    申请日：2017-07-24

    Applicant: Bell Helicopter Textron Inc.

    Inventor： POSTER, Scott David ,  PERYEA, Martin

    IPC: B64C25/56

    CPC classification number: B64F1/221 ,  B64C25/56 ,  B64C27/06

    Abstract: The present invention includes an apparatus for preventing aircraft rollover upon a water landing comprising: a deployable first and/or second boom (116, 122) affixed by a first end (117) to the aircraft (100) and capable of deployment substantially perpendicular to a longitudinal axis of the aircraft (100); and a first and/or second air bladder (118, 124) attached to a second end of the first and/or second boom (116, 122), wherein the first and/or second air bladders (118, 124) are configured to inflate when an aircraft (100) lands in the water (112), wherein deployment of the first and second boom (116, 122) and air bladder (118, 124) prevents aircraft rollover upon water landing; or a deployable keel (130) affixed by a first end to the aircraft (100) and capable of deployment substantially perpendicular to a longitudinal axis and opposite a rotor of the aircraft (100) upon a water landing, wherein the keel is sized to prevent aircraft rollover upon deployment; or both.

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