公开(公告)号：US20150336654A1

公开(公告)日：2015-11-26

申请号：US14249576

申请日：2014-04-10

申请人： The Boeing Company

发明人： Justin D Cottet ,  Roger S Kepner ,  Michael L Drake

IPC分类号： B64C1/06

CPC分类号： B64C1/06 ,  B32B3/12 ,  B32B15/01 ,  B32B15/015 ,  B32B2307/558 ,  B32B2307/722 ,  B32B2311/18 ,  B32B2311/22 ,  B32B2311/24 ,  B32B2605/18 ,  B64C2025/005 ,  F16F7/12

摘要： An energy absorbing rub strip having a core material and a fairing positioned over the core material. The core material may be configured to buckle under the application of a predetermined amount of force and the fairing may be configured to be attached to a fuselage of an aircraft. The fairing may be made out of an abrasive-resistant material such as titanium or a nickel-based metal. The core material may be comprised of an aluminum honeycomb. The core material may be comprised of a dual density material. The length of the rub strip may extend beyond potential contact points on the fuselage during landing and takeoff. Upon a ground contact event, the thickness of deformed/buckled core material may be measured to determine if the ground contact event may have caused structural damage to the aircraft.

摘要翻译： 一种能量吸收擦拭条，其具有芯材料和位于芯材料上方的整流罩。 芯材可以被配置为在预定量的力的应用下弯曲，并且整流罩可以被配置为附接到飞行器的机身。 整流罩可以由诸如钛或镍基金属的耐磨材料制成。 芯材料可以由铝蜂窝体组成。 芯材料可以由双密度材料构成。 摩擦条的长度可能在着陆和起飞期间延伸超过机身上的潜在接触点。 在地面接触事件时，可以测量变形/弯曲的芯材料的厚度，以确定地面接触事件是否可能对飞机造成结构损坏。

公开(公告)号：US09637212B2

公开(公告)日：2017-05-02

申请号：US14249576

申请日：2014-04-10

申请人： The Boeing Company

发明人： Justin D Cottet ,  Roger S Kepner ,  Michael L Drake

IPC分类号： B64C25/00 ,  B64C25/58 ,  B64C1/06 ,  B32B15/01 ,  B32B3/12 ,  F16F7/12

CPC分类号： B64C1/06 ,  B32B3/12 ,  B32B15/01 ,  B32B15/015 ,  B32B2307/558 ,  B32B2307/722 ,  B32B2311/18 ,  B32B2311/22 ,  B32B2311/24 ,  B32B2605/18 ,  B64C2025/005 ,  F16F7/12

摘要： An energy absorbing rub strip having a core material and a fairing positioned over the core material. The core material may be configured to buckle under the application of a predetermined amount of force and the fairing may be configured to be attached to a fuselage of an aircraft. The fairing may be made out of an abrasive-resistant material such as titanium or a nickel-based metal. The core material may be comprised of an aluminum honeycomb. The core material may be comprised of a dual density material. The length of the rub strip may extend beyond potential contact points on the fuselage during landing and takeoff. Upon a ground contact event, the thickness of deformed/buckled core material may be measured to determine if the ground contact event may have caused structural damage to the aircraft.