Aircraft panel including ballistic stab-in armor

Abstract

A panel assembly that includes inside and outside core layers, an armor layer sandwiched between the inside and outside core layers, and an armor member that includes at least an outside portion and a transverse portion. The outside core layer includes a cut out portion defined therein. The armor layer has opposing first and second major surfaces. The outside portion of the armor member is positioned in the cut out portion of the outside core layer and the outer surface of the transverse portion is generally perpendicular to the first and second major surfaces of the armor layer.

Description

CROSS REFERENCE TO RELATED APPLICATIONS[0001]This application is a national stage application, filed under 35 U.S.C. § 371, of International Patent Application No. PCT / US19 / 15721, filed on Jan. 29, 2019, which claims the benefit of U.S. Provisional Application No. 62 / 760,156, filed Nov. 13, 2018, the entireties of which are incorporated herein by reference.FIELD OF THE INVENTION[0002]The present invention relates generally to aircraft panels, and more particularly to an aircraft panel that includes ballistic stab-in armor.BACKGROUND OF THE INVENTION[0003]The need has arisen to develop an improved ballistic edge protection for aircraft panels such as those used in flight deck doors or other aircraft interior structures. Such structures include, but are not necessarily limited to, galleys, lavatories and closets and are collectively known as monuments. Current panel edge protection is heavy, expensive and requires ballistic resistant mechanical fasteners that result in holes in the pa...

AI Technical Summary

Benefits of technology

[0008]The present invention protects the edge of an armored panel from ballistic threats striking in close proximity of the panel edge. Preferably, the present invention reduces cost and weight when compared to the prior art, and removes the requirement for special ballistic resistant mechanical fasteners. This is accomplished by inserting, or stabbing-in, the ballistic armored material into the edge of the panel directly as opposed to encompassing the outside of the panel. The armored stab-in is bonded within the panel, therefore removing the need for mechanical fasteners. Further, by bonding the stab-in armor internally the space requirements of the panel are preferably not increased. Steel or titanium metal armor, added as doublers, is not necessary. However, doublers can still be used if desired.

[0009]In a preferred embodiment, the stab-in armor is made from multiple layers of UHMWPE formed in a U, J or L shape made from being pressed in a heated tool. The honeycomb armor panel comprises composite or aluminum skins with a honeycomb composite or aluminum core. The lightweight UHMWPE or para-aramid armor is located in the center of the panel and adhered by adhesive to the core. The exposed core at the edge of the panel is routed out to accept the stab-in armor which lays flush beneath the panel face sheets. Structural adhesive is injected into the cavity before the stab-in armor is positioned permanently. The edge is then covered with edge trim to hide the stab-in armor from view. The curved geometry of the stab-in cradles the bullet at impact and creates a backstop effect that prevents the bullet from exiting as it is captured in stab-in armor insert. Such an in-situ edge armor stab-in provides an unseen, lightweight solution to ballistic edge protection that reduces the weight of the overall armor package compared to the prior art. The edge armor can be made in long sections and cut to required lengths thus minimizing production costs. It also provides a subtle ballistic solution to accommodate industrial design needs for a less obtrusive presence. It further removes the need for mechanical fasteners.

Problems solved by technology

Current panel edge protection is heavy, expensive and requires ballistic resistant mechanical fasteners that result in holes in the panel and the armor.

The current design adds weight, cost and introduces weaknesses at the fastener.

As the threat approaches the edge, there is less material to cradle the bullet sufficiently and the panel armor is compromised by either being destroyed or folding over from the bullet impact and allowing the ballistic threat to continue forward.

This, however, increases the thickness of the panel armor and / or completely changes the laminate armor to a heavier metal solution thus increasing cost and weight.

The current state of the art is further limited because aircraft interior flight deck doors and other monuments have strict design envelope requirements to limit interference with adjacent aircraft structure or other interior monuments or linings, therefore, increasing the thickness of the armor package may not be a feasible option.

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