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5451015 Crashworthy composite aircraft structure with integral fuel tank
5451015 CRASHWORTHY COMPOSITE AIRCRAFT STRUCTURE WITH INTEGRAL FUEL TANK Cronkhite James D; Berry Victor L; Smith Michael Hurst, TX, UNITED STATES Assigned to Bell Helicopter Textron Inc A dual-purpose bulkhead structure functions to support normal aircraft operational loads and to absorb energy in a controlled manner during a crash. An integral fuel tank comprises a fuel compartment and a crashworthy flexible fuel cell. The fuel compartment includes two dual-purpose bulkheads and crushable foam disposed between the sides of the fuel cell and the bulkheads and sides of the fuel compartment. The foam limits fuel pressure loads on fuel compartment bulkheads and sides during a crash, thereby preventing their failure.
5452867 SHELL STRUCTURAL COMPONENT MADE OF FIBER COMPOSITE MATERIAL Grunwald Gero; Hauschildt Michael Hamburg, GERMANY Assigned to Deutsche Aerospace Airbus GmbH An aircraft structure, such as a wing, is made of fiber composite material and includes a shell structural component also made of fiber composite material. The structural component has at least one access opening closeable by a cover. The shell structural component has a first area containing the access opening closeable by the cover. In the longitudinal direction of the wing the first area is predominantly flexible while a second area surrounding the first area is predominantly stiff, whereby these areas take up different longitudinally effective forces, relative to the length of the wing. Both areas are capable of transferring shear forces in the same manner.
A machine for producing a graphite fiber tape suitable for use in the production of metal matrix composites by physical vapor deposition. The machine consists of adjacent air-tight enclosures. Two venturi pipes are located within the enclosures and aligned with a gap between them. A vacuum pump draws air out of one of the air-tight enclosures. Graphite fibers are drawn through the venturi pipes and laterally spread from a tow bundle via the Venturi effect to form a thin tape.
5447668 METHOD AND APPARATUS FOR ELIMINATING FIBER DISTORTIONS AND SEPARATIONS IN METAL MATRIX MATERIALS Delangis Leo M Lomita, CA, UNITED STATES Assigned to Rockwell International Corporation Apparatus and a method are disclosed for eliminating fiber distortions ( fiber swimming ) and separations ( fiber fish eyes ) via a premliminary step taken prior to consolidation of green , fiber-reinforced metal matrix materials. The apparatus includes a first member for supporting the green metal matrix material pack, a second member to cover the green pack, the thermal coefficient of expansion of the first member being smaller than the thermal coefficient of expansion of the second member, the second member being secured to the first member atop the green pack to form a retort, and the entire retort being heated to an off-gassing temperature, where the second member bows outwardly away from the pack to relieve pressure from the pack.
5447680 FIBER-REINFORCED, TITANIUM BASED COMPOSITES AND METHOD OF FORMING WITHOUT DEPLETION ZONES Bowden David M St Louis County, MO, UNITED STATES Assigned to McDonnel Douglas Corporation
METALMATRIXCOMPOSZTES MANUFACTURE(FABRICATION) 5446952 PNEUMATIC INDUCTION FIBER SPREADER WITH LATERAL VENTURI RESTRICTORS Kim Chulko; Gray Robert A Burke, VA, UNITED STATES Assigned to The United States of America as represented by the Secretary of the Navy
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COMPOSITES
Microcracks in fiber-reinforced/titanium aluminide matrix composite materials are inhibited by employing a matrix comprising a titanium aluminide alloy having (1) from ten to twelve atomic percent niobium and (2) a critical admixture of from two to six atomic percent of a member selected from a group consisting of molybdenum, tungsten and vanadium. The tendency of the fiber/matrix interfacial reaction to increase the stability of the Alpha 2 phase in the matrix adjacent to the interface and the tendency to form beta phase depletion zone formation inhibits the formation and growth of interfacial microcracks, and allows the fabrication of crack-free titanium matrix composite The need for an extraneous beta phase materials. stabilization treatment at the fiber/matrix interface is eliminated.
PART A Volume 27A Number 2 1996
5452867 SHELL STRUCTURAL COMPONENT MADE OF FIBER COMPOSITE MATERIAL Grunwald Gero; Hauschildt Michael Hamburg, GERMANY Assigned to Deutsche Aerospace Airbus GmbH An aircraft structure, such as a wing, is made of fiber composite material and includes a shell structural component also made of fiber composite material. The structural component has at least one access opening closeable by a cover. The shell structural component has a first area containing the access opening closeable by the cover. In the longitudinal direction of the wing the first area is predominantly flexible while a second area surrounding the first area is predominantly stiff, whereby these areas take up different longitudinally effective forces, relative to the length of the wing. Both areas are capable of transferring shear forces in the same manner.
A machine for producing a graphite fiber tape suitable for use in the production of metal matrix composites by physical vapor deposition. The machine consists of adjacent air-tight enclosures. Two venturi pipes are located within the enclosures and aligned with a gap between them. A vacuum pump draws air out of one of the air-tight enclosures. Graphite fibers are drawn through the venturi pipes and laterally spread from a tow bundle via the Venturi effect to form a thin tape.
5447668 METHOD AND APPARATUS FOR ELIMINATING FIBER DISTORTIONS AND SEPARATIONS IN METAL MATRIX MATERIALS Delangis Leo M Lomita, CA, UNITED STATES Assigned to Rockwell International Corporation Apparatus and a method are disclosed for eliminating fiber distortions ( fiber swimming ) and separations ( fiber fish eyes ) via a premliminary step taken prior to consolidation of green , fiber-reinforced metal matrix materials. The apparatus includes a first member for supporting the green metal matrix material pack, a second member to cover the green pack, the thermal coefficient of expansion of the first member being smaller than the thermal coefficient of expansion of the second member, the second member being secured to the first member atop the green pack to form a retort, and the entire retort being heated to an off-gassing temperature, where the second member bows outwardly away from the pack to relieve pressure from the pack.
5447680 FIBER-REINFORCED, TITANIUM BASED COMPOSITES AND METHOD OF FORMING WITHOUT DEPLETION ZONES Bowden David M St Louis County, MO, UNITED STATES Assigned to McDonnel Douglas Corporation
METALMATRIXCOMPOSZTES MANUFACTURE(FABRICATION) 5446952 PNEUMATIC INDUCTION FIBER SPREADER WITH LATERAL VENTURI RESTRICTORS Kim Chulko; Gray Robert A Burke, VA, UNITED STATES Assigned to The United States of America as represented by the Secretary of the Navy
160
COMPOSITES
Microcracks in fiber-reinforced/titanium aluminide matrix composite materials are inhibited by employing a matrix comprising a titanium aluminide alloy having (1) from ten to twelve atomic percent niobium and (2) a critical admixture of from two to six atomic percent of a member selected from a group consisting of molybdenum, tungsten and vanadium. The tendency of the fiber/matrix interfacial reaction to increase the stability of the Alpha 2 phase in the matrix adjacent to the interface and the tendency to form beta phase depletion zone formation inhibits the formation and growth of interfacial microcracks, and allows the fabrication of crack-free titanium matrix composite The need for an extraneous beta phase materials. stabilization treatment at the fiber/matrix interface is eliminated.
PART A Volume 27A Number 2 1996