Fatigue damage imaging method for carbon fiber composite material
A technology for fatigue damage and composite materials, which is applied in the analysis of materials, material analysis using acoustic wave emission technology, and material analysis using sound waves/ultrasonic waves/infrasonic waves, etc. It can solve the problems of low imaging clarity, poor damage location accuracy, and poor visualization effects and other problems to achieve the effect of improving sensitivity and positioning accuracy
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Embodiment 1
[0058] see Figure 1 to Figure 19 As shown, a fatigue damage imaging method of carbon fiber composite material, the specific steps are:
[0059] Step1: Collect the baseline signal of each excitation-sensing channel of the structure to be tested and the real-time monitoring signal of each excitation-sensing channel when the structure to be tested is damaged;
[0060] Step1.1: Arrange a set of sensor arrays composed of M piezoelectric sensors on the upper and lower edges of the carbon fiber composite material plate, where M is a positive integer that increases from 2.
[0061] Step1.2: Among the two sensor arrays, one group is used as an exciter, numbered from right to left as 1, 2, ..., M, and the other group is used as a receiver, numbered from left to right as M+1, M+2, …, 2M.
[0062] Step1.3: The exciters 1, 2, ..., M excite the Lamb wave signal in turn, and each receiver receives the signal excited by each exciter, forming M*M=M2=L excitation-sensing channels.
[0063] ...
Embodiment 2
[0086] In the initial stage of fatigue damage of carbon fiber composite materials and the stage of fatigue crack initiation, a fatigue damage imaging method based on Lamb wave energy and flight time of the present invention can be used to accurately identify and locate the tiny damage of carbon fiber composite materials. Collect the reference signal and the real-time monitoring signal of the carbon fiber composite tensile fatigue experiment with 10,000 fatigue cycles and a load of 4kips, and image the fatigue damage under this condition. The method flow chart is as follows figure 1 shown;
[0087] The actual picture of the experimental specimen is as follows Figure 4 As shown, the experimental specimen is a dog-bone-shaped carbon fiber composite material plate with a length of 25.4 cm and a width of 15.24 cm. There is a rectangular notch with a length of 19.3 mm and a width of 5.08 mm in the middle of the left edge of the carbon fiber composite material plate. Induced load...
Embodiment 3
[0126] In the middle stage of fatigue damage development of carbon fiber composite materials and the stage of fatigue crack propagation, a fatigue damage imaging method based on Lamb wave energy and flight time of the present invention can be used to monitor and identify the expansion of fatigue damage of carbon fiber composite materials. Collect the reference signal and the real-time monitoring signal of the carbon fiber composite tensile fatigue experiment with 40,000 fatigue cycles, no load but clamping the sample, and image the fatigue damage under this condition.
[0127] Flow chart such as figure 1 shown;
[0128] The actual picture of the experimental specimen is as follows Figure 4 As shown, the experimental specimen is a dog-bone-shaped carbon fiber composite material plate with a length of 25.4 cm and a width of 15.24 cm. There is a rectangular notch with a length of 19.3 mm and a width of 5.08 mm in the middle of the left edge of the carbon fiber composite material...
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