Method for obtaining porosity and interface strength of bonding interface ofcomposite material
A technology of interfacial strength and composite materials, which is used in the application of stable shear force to test the strength of materials, analyze materials, strength characteristics, etc. and other problems, to achieve the effect of saving research costs, simple manufacturing methods, and improving manufacturing efficiency
Pending Publication Date: 2020-12-04
AECC COMML AIRCRAFT ENGINE CO LTD
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Problems solved by technology
[0009] The technical problem to be solved by the present invention is to overcome the inhomogeneous porosity of the pilot test plate in the prior art and the inability to cut out the defects of mechanical performance test samples of suitable size, and to provide a method for obtaining the porosity and interface porosity of the bonded interface of composite materials. method of strength
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[0059] In order to make the above objects, features and advantages of the present invention more comprehensible, specific implementations of the present invention will be described in detail below in conjunction with the accompanying drawings.
[0060] Embodiments of the present invention will now be described in detail with reference to the accompanying drawings. Reference will now be made in detail to the preferred embodiments of the invention, examples of which are illustrated in the accompanying drawings. Wherever possible, the same numbers will be used throughout the drawings to refer to the same or like parts.
[0061] In addition, although the terms used in the present invention are selected from well-known and commonly used terms, some terms mentioned in the description of the present invention may be selected by the applicant according to his or her judgment, and the detailed meanings thereof are set forth herein described in the relevant section of the description. ...
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The invention provides a method for obtaining the porosity and the interface strength of a bonding interface of a composite material. The method comprises the following steps: S1, obtaining a series of bonding test pieces with different bonding strengths by pre-embedding polytetrafluoroethylene film defects with different pore proportions; S2, establishing a relation curve of an ultrasonic signaland porosity by means of ultrasonic detector A scanning , and performing performance test on the bonding test piece to obtain a relation curve of porosity and mechanical properties, thereby establishing a relation curve of the ultrasonic signal, porosity and mechanical properties; and S3, carrying out ultrasonic detector A scanning on the to-be-detected product to obtain a corresponding ultrasonicsignal, evaluating the porosity of the to-be-detected product, and evaluating the mechanical properties of the to-be-detected product. According to the invention, the traditional mode that a weak bonding test pieces needs to be accumulated in the long-term production process is changed, the test pieces with different bonding strengths can be manufactured in a short time, and the manufacturing efficiency of the test pieces is greatly improved.
Description
technical field [0001] The invention relates to the field of composite materials, in particular to a method for obtaining the porosity and interface strength of the bonding interface of composite materials. Background technique [0002] In the existing technology, compared with mechanical fasteners, the composite material bonding structure has obvious advantages in corrosion resistance, sealing, strength, density, etc. It is an important measure for structural weight reduction and is widely used in Aeronautical composite parts. For example, commercial aircraft airfoil stiffened panels, empennage leading edge, engine fan blades, etc. [0003] Generally, composite bonded structures can be divided into three forms according to different manufacturing methods: co-curing, co-bonding, and secondary bonding. According to the type of bonding substrate, it can be divided into: composite material-composite material bonding structure and composite material-metal material bonding stru...
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Login to View More IPC IPC(8): G01N15/08G01N19/04G01N3/24G01N29/04
CPCG01N15/088G01N19/04G01N3/24G01N29/04G01N2203/0025G01N2291/0231
Inventor 张婷杨坤白国娟
Owner AECC COMML AIRCRAFT ENGINE CO LTD