Prediction method of tool life for cfrp and titanium alloy lamination reaming tool
A technology of laminated structure and tool life, applied in the direction of program control, instrument, computer control, etc., can solve the problems that the laminated structure is not applicable, and the method of reamer life prediction is not proposed, so as to reduce the failure rate and scrap rate of parts , high accuracy and large reaming capacity
A technology of laminated structure and tool life, applied in the direction of program control, instrument, computer control, etc., can solve the problems that the laminated structure is not applicable, and the method of reamer life prediction is not proposed, so as to reduce the failure rate and scrap rate of parts , high accuracy and large reaming capacity
CN106647632BActive Publication Date: 2018-10-19SHENYANG AEROSPACE UNIVERSITY
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[0027] 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.
[0028] 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:
[0029] (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;
[0030] (2) The tool material is K6UF (tungsten carbide);
[0031] (3) Reaming process parameters: cutting speed is 20m / min, feed rate is 0.03mm / r;
[0032] (4) Reaming hole size accuracy requirements: the hole size meets the H9 accuracy;
[0033] (5) The thickness of the T300 composite ma...
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Abstract
The invention provides a CFRP and titanium alloy laminated structure reamer service life prediction method, and relates to the technical field of carbon fiber composite material and titanium alloy lamination assembly. The method comprises the steps: building a CFRP and titanium alloy laminated structure reaming aperture size error analysis model and a reamer rear flank surface abrasion (AB value) analysis model; evaluating the service life of a reamer through various types of indexes, and giving comprehensive consideration to the two constraints: the aperture size precision of a laminated structure in a reaming process and the flank abrasion of the reamer; and predicting and analyzing the effective service life of the reamer according to the current structure parameters and perforation technological parameters of the reamer. The method provided by the invention is high in accuracy of a prediction result of the service life of the reamer, can effectively predict the maximum reaming number of the laminated structure, reduces the unqualified ratio and rejection rate because of the exceeding of the service life of the reamer, and enables the reamer to give full play to the maximum reaming capability.
Description
technical field [0001] The invention relates to the technical field of laminated assembly of carbon fiber composite material and titanium alloy, in particular to a method for predicting the service life of a reaming tool with a laminated structure of CFRP and titanium alloy. 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 i...
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Patent Timeline
19 Oct 2018
Publication
CN106647632B
- IPC
- G05B19/408
- CPC
- G05B19/4086; G05B2219/35356
- Inventors
- 郑耀辉; 王志坚