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Reaming method of cfrp and titanium alloy laminated structure

A technology of laminated structure and reaming, which is applied in reaming device, reaming device, metal processing equipment, etc., can solve the problems of unreasonable optimization of the process parameters of laminated structure hole making and incomplete constraints, so as to improve the reaming. Hole efficiency, reasonable optimization results, reduction of reject rate and scrap rate

Active Publication Date: 2018-10-19
沈阳航远航空技术有限公司
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Problems solved by technology

These optimization methods have the following deficiencies: (1) The existing optimization methods do not consider the influence of structural geometric parameters such as reamer lead angle and outer edge relief angle on the reaming process, so the laminated structure cannot be rationally optimized according to the change of reamer structure (2) The constraints of existing optimization methods are not comprehensive, and the optimization results cannot comprehensively reflect the aperture size error, reamer flank wear, and tool life on the reaming process parameters of laminated structures. Impact

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  • Reaming method of cfrp and titanium alloy laminated structure
  • Reaming method of cfrp and titanium alloy laminated structure
  • Reaming method of cfrp and titanium alloy laminated structure

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Embodiment Construction

[0031] The specific implementation manners of the present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments. The following examples are used to illustrate the present invention, but are not intended to limit the scope of the present invention.

[0032] Taking the reaming process of T300 carbon fiber composite material and TC6 titanium alloy laminated structure as an example, the reaming conditions and accuracy requirements of the laminated structure are as follows:

[0033] (1) Structural geometric parameters of the reamer: the diameter is 6.6mm, the main deflection angle is 45 degrees, and the rear edge angle is 12 degrees;

[0034] (2) The tool material is K6UF (tungsten carbide);

[0035] (3) Reaming hole size accuracy requirements: the hole size meets the H9 accuracy;

[0036] (4) The thickness of the T300 composite material plate is 5mm, and the thickness of the TC6 titanium alloy plate is 3mm.

[0037] Su...

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Abstract

The invention provides an optimization method for a CFRP (carbon fiber reinforced plastics) and titanium alloy laminated structure reaming process and relates to the technical field of CFRP and titanium alloy laminated assembly. According to the optimization method for the CFRP and titanium alloy laminated structure reaming process, the constraints such as pore diameter size errors, rear knife face wear of a reaming tool, the service life of the reaming tool and the like are comprehensively considered, and the cutting speed and feed of the reamed hole are optimized according to the existing reamer structure parameter, pore diameter size accuracy standard and quantity of the formed pores. According to the method disclosed by the invention, the laminated structure reaming process is optimized by adopting multiple constraints, the reaming efficiency of the CFRP and titanium alloy laminated structure is effectively improved, and the reject rate and scrap rate of the parts are reduced, so that the reaming tool has the maximum reaming capacity.

Description

technical field [0001] The invention relates to the technical field of laminated assembly of carbon fiber composite materials and titanium alloys, in particular to a reaming method for laminated structures of CFRP and titanium alloys. Background technique [0002] Carbon fiber composite material (CFRP) has a series of advantages such as low density, high strength, high specific strength, and good vibration absorption, and has been widely used in aerospace, automobile, missile and other fields. For example, 90% of the fuselage surface of the Boeing 787 is made of carbon fiber composite materials. my country's new aviation aircraft is also gradually increasing the proportion of carbon fiber composite materials used. The application ratio of aviation aircraft composite materials and titanium alloys has become an important indicator to measure its advanced nature. one. [0003] With the widespread use of carbon fiber composite materials in advanced aerospace vehicles, the demand...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B23D75/00
CPCB23D75/00
Inventor 郑耀辉曹国强王奔王明海李晓鹏马书娟庄鑫
Owner 沈阳航远航空技术有限公司
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