Disposal solidifying and forming technique for frame and outer panel skin of wing profile
A technology of solidification forming and process method, which is applied in aircraft assembly, aircraft parts, ground installations, etc., can solve the problems of heavy weight, corrosion resistance, low fatigue resistance, high operating cost, etc., and achieve high rigidity, strength, and fatigue resistance The effect of low capacity and high operating costs
Inactive Publication Date: 2011-01-12
马献林 +1
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Problems solved by technology
[0002] The traditional airfoil frame and skin forming process is to assemble the airfoil metal frame first, and the frame has beams, ribs, and long beams; then riveted or glued the skin, the number of parts required is large, the process is complicated, and the efficiency is low; At the same time, the weight is large, the corrosion resistance and fatigue resistance are low, and the operating cost is high
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[0018] Below in conjunction with accompanying drawing, the present invention will be further described;
[0019] Figure 1-Figure 6 It is a single-beam airfoil structure, and the multi-beam airfoil structure has the same forming principle as it. combine figure 1 , the mold in this embodiment includes a detachable built-in combination mold, a group of modules from the front beam to the front edge, and a group of modules from the rear beam to the rear edge. For a multi-beam structure, a group of modules is formed between the beams, and the front and rear modules are respectively Consisting of 6 molds and a center slide rail, the front group mold includes the transverse bulkhead groove 1, the "I" shaped beam wing plate groove 2, the front edge forming die 6 of the front group mold, and the upper and lower forming molds of the front group mold 7. The center slide rail 8 of the front group mold, the longitudinal beam upper and lower forming molds 9 of the front group mold and the...
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The invention provides a technique for curing and molding an airfoil frame and an aircraft skin at one time. The technique adopts built-in detachable grouped dies; the dies are transversely divided into different die groups by carlings, and each die group is composed of a set of module and a central slideway; the module and the central slideway in each group can slide relatively and can be taken out from the die cavity sequentially; all the bulkheads and the carlings are provided with concave grooves which match with the airfoil frame in shape; the ventral shields of the airfoil carlings are the combination of composite material and I-shaped alloy plates; bulkhead fibre is laid inside the concave grooves through winding. After the frame fiber is laid, the skin fibre is uniformly laid, forming a hatch rim frame the same as the bulkheads; after that, a vacuum bag is arranged at the outer surface and grease injection and vacuum die press molding are adopted; the frame and the aircraft skin are molded and cured at one time through the technique of electron beam heating, high temperature stove heating or curing at normal temperature according the compounding technological requirements of the fibre resin substrate. The invention has fewer accessories, lighter weight, short production period, low cost and high safety factor and the anti-corrosion capability and anti-fatigue capability are improved by more than two times.
Description
(1) Technical field [0001] The invention relates to aircraft manufacturing technology, in particular to an airfoil frame and skin curing forming technology. (2) Background technology [0002] The traditional airfoil frame and skin forming process is to assemble the airfoil metal frame first, and the frame has beams, ribs, and long beams; then riveted or glued the skin, the number of parts required is large, the process is complicated, and the efficiency is low; At the same time, the weight is large, the corrosion resistance and fatigue resistance are low, and the operating cost is high. (3) Contents of the invention [0003] The purpose of the present invention is to provide a one-time solidification forming process of airfoil frame and skin with less parts, less weight, short production cycle, low cost, improved corrosion resistance and fatigue resistance by more than 2 times, and high safety factor. [0004] The purpose of the present invention is achieved in this way: ...
Claims
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IPC IPC(8): B64C1/00B64C1/12B64F5/00B64F5/10
Inventor 马献林张玉龙
Owner 马献林