Segmented Processing Method of Die Surface of Aircraft Composite Forming Die
A composite material and segmented processing technology, which is applied in the field of segmented processing of aircraft composite material forming die surfaces and forming die surface processing, can solve the problem that the composite material forming die is not easy to form, the die surface has good air tightness, and the air tightness is not good. Good and other problems, to achieve good air tightness, uniform wall thickness, and solve the effect of difficult molding
Inactive Publication Date: 2017-05-03
NORTHEAST FORESTRY UNIVERSITY
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Problems solved by technology
[0006] The purpose of the present invention is to solve the existing problems in the prior art, that is, the complex mold surface of the composite material forming mold is not easy to form, the airtightness after welding is not good, or the mold surface has good airtightness, and it is suitable for complex mold surfaces, but the cost high problem
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[0029] This specific embodiment provides a method for segmented processing of aircraft composite material molding die surface, the steps are as follows:
[0030] 1. Segmented process design of die surface
[0031] A block principle
[0032] a Segment the complex die surface according to the minimum entity principle;
[0033] Goal: Maximize material utilization rate and minimize processing volume; select sheet metal thickness of 50-240mm in sections;
[0034] b The optimal welding scheme, the selected surface should have as few interfaces as possible, and the weld bead should be as short as possible;
[0035] B datum and stiffener design
[0036] Reinforced vertical ribs: 10-20mm thick, reasonably distributed, mainly to prevent deformation, the bottom R is better than R8, which is convenient for processing; benchmark: processing benchmark - used for upside down turning processing and alignment. Cannot affect welding. Preference is given to stiffeners. Welding datum—the da...
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Abstract
The invention provides a mold surface subsection machining method of an aircraft composite material forming mold. A complex mold surface of the composite material forming mold is divided according to the least material principle; reinforcing ribs and datums are arranged; upper and lower mold surfaces are machined through numerical control with plate material separately; and finally, the combination and welding are performed according to the datums. The main process parameters are as follows: the thickness of the plate material for subsection machining is 50-240 mm; the thicknesses of the process ribs are 10-20 mm; the bottom R of the ribs is greater than R8; the subsection mold surfaces and the bracket welding surfaces are machined through numerical control; a knife of phi 30 is used for final machining, with the step being 0.7; the welding grooves are Y-shaped grooves according to GB985-88, with the groove angles being 40-60 degrees; P is 1.0-2.0 mm; and B is 1.5 mm. The core of the method is to section the complex mold surface of the composite material forming mold according to the least material principle, to machine the upper and lower mold surfaces through numerical control with the plate material separately, to maintain the datums and to finally perform the combination and welding according to the datums. The method solves the problems of difficult molding and poor welding air tightness of the complex mold surface of the composite material forming mold.
Description
technical field [0001] The invention relates to a method for segmentally processing the mold surface of an aircraft composite material molding die, and belongs to the technical field of processing methods for the molding die surface. Background technique [0002] Existing methods for manufacturing the mold surface of composite material forming molds are as follows: [0003] 1. Flat welding manufacturing process; for some flat die surfaces, steel plates can be used for direct welding. When welding with pressure, a little bit of welding with the frame. The mold frame should be fixed on the platform during welding to prevent stress deformation during welding. This process method has a limited range of application and is not valid for complex surfaces. [0004] 2. Rolling forming welding For the single curved surface, rolling forming can be used, and then welding can be done gradually. This method is not valid for hyperbolic die faces. [0005] 3. Mold forming (hot and cold...
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IPC IPC(8): B23P15/24
CPCB23P15/24
Inventor 刘楠
Owner NORTHEAST FORESTRY UNIVERSITY