Abstract:
A unitary fastener insert (50) for structural sandwich panels (52) is comprised of a shaft (58) of a generally uniform circular cross section having a base (64) and a tip (62), a generally circular flange (68) extending radially outward from the base circumferentially peripheral the shaft, and a central stepped bore therethrough (72) including an enlarged fastener seat recess (78) disposed interiorly of the tip for receiving the head (90) of a fastener (54) merging to a reduced bore (82) for receiving the shank (94) of the fastener. The insert of the present invention is specifically configured for production by a forging technique, also described herein.
Abstract:
A floor panel installation system and apparatus using two dimpled washer inserts, each at opposite sides of a floor panel. The two inserts equal a thickness which is almost equal to the floor panel thickness, so that a slight gap exists between the two washers which will close at installation, when the fastener is tightened, thus providing a resilient tightening and sealing feature as well as a "controlled stop" to the fastener installation procedure, avoiding panel crushing, potting compounds, sealers, etc.
Abstract:
A composite, lightweight, fire-retardant laminar structural panel (10, 10', 10", 30) of the present invention comprising: (i) a sheet-like central honeycomb core (11) formed of aluminum, paper treated to improve its fire resistance characteristics, or the like; (ii) upper and lower imperforate face sheets (15, 16) formed of lightweight fibrous materials impregnated with a phenolic resin; (iii) a pair of upper and lower phenolic adhesive films (18, 19) interposed between the honeycomb core (11) and respective ones of the imperforate face sheets (15, 16) for adhesively bonding the face sheets (15, 16) to opposite sides of the core (11); and (iv), a fire-retardant coating (20) comprising a copolymer of vinylidene fluoride and hexafluoropropene applied to at least the exposed surface of the lower face sheet (16). In certain of the exemplary forms of the invention herein described, the composite, laminar panels (10, 10', 30) are designed to provide one of a plurality of different load bearing capacities dependent upon the type of use to which the panel is to be put; while in other exemplary forms of the invention, a given panel includes regions of differing density and/or of different numbers of face sheet plies; but, which is of uniform overall thickness so as to provide relatively high load bearing capacities in high traffic and/or high load environments and relatively low load bearing capacities in low traffic and/or low load environments.
Abstract:
A unitary structure access panel (10) for use particularly in aircraft wing tanks (32) having openings (30). The panel is made having a molded nylon fiberglass reinforced base (12) and having a high strength-to-weight core (96, 132) spaced between a nylon base first face (24) for extending into the tank and an outer second face (98) for extending outwardly of the tank. In a peripheral portion (20) of the base, there are multiple peripherally spaced recesses (50), each of which contains a lightweight simplified fastener retainer and anti-rotation device (66).
Abstract:
A "bilge-like" valve, adapted to be mounted on the lowermost wall of an aircraft fuselage, is disclosed in which the valve has a normally open condition to drain accumulated condensate through a registering opening in the fuselage wall when the interior cabin is depressurized, and assumes a closed condition in response to a differentially higher cabin pressure relative to outside air pressure to seal off the interior of the fuselage. A valve housing retainer is affixed to the inner surface of the fuselage wall in registration with the wall opening for detachably retaining a valve housing incorporating a piston-like reciprocating valve member and biasing spring that is insertable and removable through the wall opening from the exterior of the aircrafts fuselage for ease of servicing. The housing retainer is of a generally inverted cup shape and has a central, interiorally threaded opening arranged in overlying registration with the fuselage wall opening for receiving the valve housing which is cylindrically shaped and has cooperating exterior threads. The valve housing is installed and removed by a tool that is inserted in a specially shaped valve port and which is used to apply a rotating force to the valve housing from the exterior of the aircraft. The perimeter of the cup shaped retainer protectively surrounds the installed valve housing, and is formed with a plurality of fluid passing, debris blocking ports to ensure reliable valve operation and complete drainage of condensate when the valve is open.