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The gray "Reinforced Carbon–Carbon (RCC)" panels on the space shuttle's wing leading edges and nose cone cost NASA $100,000/sq ft to produce, [clarification needed] although much of this cost was a result of the advanced geometry and research costs associated with the panels. This stage can also include manufacturing of the finished product.
It forms part of the Airbus A380 fuselage and the leading edge of the tail surfaces. In 1995, an aircraft freight container made out of Glare became the first container certified by the Federal Aviation Administration (FAA) for blast resistance; the container can absorb and neutralize the explosion and fire from a bomb such as the one used in ...
It is swept aft 16 degrees at the leading edge. The strakes are swept 49 degrees at the leading edge. These strakes, combined with a wet wing center-section area, form the bulk of the 2,200 lb (1000 kg, approximately 333 US gallons or 1,260 litres) fuel capacity.
The filler materials were made of either white AB312 fibers or black AB312 cloth covers (which contain alumina fibers). These materials were used around the leading edge of the nose cap, windshields, side hatch, wing, trailing edge of elevons, vertical stabilizer, the rudder/speed brake, body flap, and heat shield of the shuttle's main engines.
Associated terms are leading edge radius and leading edge stagnation point. [3] Seen in plan the leading edge may be straight or curved. A straight leading edge may be swept or unswept, the latter meaning that it is perpendicular to the longitudinal axis of the aircraft. As wing sweep is conventionally measured at the 25% chord line [3] an ...
The thermal protection system for the underside of the vehicle, comprising the nose, leading edges and lower surface of the wing, were designed and made by Herakles [32] using a ceramic matrix composite (CMC), carbon/silicon-carbide (C/SiC), in this case based on the liquid silicon infilration (LSI) process (see manufacturing procedures above ...
Basic metal-sparred wing using a honeycomb 'D' box leading edge. A typical metal spar in a general aviation aircraft usually consists of a sheet aluminium spar web, with L- or T-shaped spar caps being welded or riveted to the top and bottom of the sheet to prevent buckling under applied loads.
Plywood covering and polyester-filled laminate ribs form a box spar forward to the leading edge, with spruce ribs and polyester covering aft. Since 2006 all composite parts have been replaced by carbon fibre castings. Each wing has a single, faired lift strut to the lower fuselage.
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