Static structures (e.g. – buildings) – Facer held by stiffener-type frame – Facer back abuts and conceals frame
Patent
1980-06-24
1983-08-23
Friedman, Carl D.
Static structures (e.g., buildings)
Facer held by stiffener-type frame
Facer back abuts and conceals frame
52787, F04C 254
Patent
active
043996426
DESCRIPTION:
BRIEF SUMMARY
BACKGROUND OF THE INVENTION
This invention relates to aircraft floor panel installation components and system and in particular to fastener inserts for honeycomb panels.
Aircraft floor panels are generally a composition of two metal sheets separated by a honeycomb core structure. Recently, instead of metal sheets, composite materials, i.e., epoxy, graphite, etc., have been utilized which provide for an even lighter and stronger floor panel structure.
These honeycomb panel structures are fragile in the core area where fasteners are utilized to mount the panel. Accordingly, floor panel attachment methods used a separate insert and screw combination. The inserts were always bonded and potted to the floor panels during floor panel fabrication. The inserts used on honeycomb core floor panels were of two basic types, single piece and two piece.
The single piece has a body and a lower flange. The lower flange is bonded to the lower facesheet of the panel, the body goes thru the panel and is swaged over onto the upper facesheet.
The two piece inserts are two inter-locking pieces each with a flange. The pieces are inserted one from each side of the panel and the flanges are bonded onto the facesheets.
During panel installation, screws are installed through the inserts in order to secure the panels. The herein disclosed dimpled washer system is an improvement which will save time and money in the fabrication and installation phase. In addition, the new installation concept is specifically designed to provide for a more effective moisture sealing arrangement, and a method which would not dimple the facesheets and crush the core, as well as void conventional manufacturing steps.
SUMMARY OF THE INVENTION
The present invention is an improved installation system for floor panels and in particular to inserts for floor panels having a honeycomb type core matrix utilized in aircraft. The system involves using two alike dimpled washers and an optional rubber grommet under the screw head effectively sealing the installation from moisture. Further, electrolytic corrosion is inhibited by the application of an aluminum-pigmented coating to the washers and the screw before installation. The dimpled washers and screws are designed to secure aircraft floor panels to floor support members. These washers are easier, cheaper and lighter to install than conventional floor panel inserts.
The dimpled washer consists of a thin upper flange and a cylindrical body. Two washers are used per hole, one washer inserted in the upper panel surface and the other in the lower panel surface. The washers are either fitted or may be bonded in place using a simple cold bonding process. A rubber grommet is used under the fastener head to insulate the fastener from the dimpled metal washer. Washers and fasteners may be made from titanium, steel, or aluminum.
Upon installation of the washers on each side of the panel, no potting is used to the core structure and no squeezing action is needed for installing the washer inserts. These two manufacturing steps are completely deleted saving time and weight since potting compound is not used, which of course is more economical.
Furthermore, this new installation system of two opposed dimpled washers presents a novel, unique feature because the dimpled washers abut one another as soon as the screw or fastener is tightened and thus automatically provides for a "stop" to the installation. In addition, each washer is slightly deformed upon fastening of the screw which offers a double biased spring force against the annula under surface of the screw head. Thus a non-corecrushing feature, a non-face-dimpling feature and an improved sealing feature is accomplished by the present installation system. In general, an aircraft floor installation apparatus and system is disclosed for floor panels having an upper and a lower face sheet separated by a core and provided with fastening holes, for mounting to an airplane floor beam structure provided with mounting holes. The system uses two washers, the first dimpled washer
REFERENCES:
patent: 1031024 (1912-07-01), Rickles
patent: 2140709 (1938-12-01), Mauser
patent: 2713482 (1955-07-01), Stapleton
patent: 3110064 (1963-11-01), Koontz
patent: 3742673 (1973-07-01), Jennings et al.
Bard Ronald E.
Gorges Friedrich J.
Halsey Robert M.
DeVogel Nicolaas
Donahue Bernard A.
Friedman Carl D.
The Boeing Company
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