DEVICE AND METHOD FOR EVALUATING SOUNDNESS OF FIBER-REINFORCED COMPOSITE MATERIAL

Abstract

The present invention is equipped with an AE sensor 12, a load test device 14, a storage device 22, a frequency center of gravity calculation unit 24 and a determination device 26. A loading pattern including, raising, retaining and unloading is repeatedly applied to a test subject 1 by the load test device 14, the maximum load is sequentially increased, and the AE waves 2 detected by the AE sensor 12 are stored with the load by the storage device 22. Next, the frequency center of gravity of the AE waves is obtained from the relationship between the frequency of the AE waves 2 and the intensity thereof by the frequency center of gravity calculation unit 24, and delamination preceding breakage is determined by the determination device 26 when the frequency center of gravity 5 is less than a prescribed first frequency.

Claims

1. A device for evaluating soundness of a fiber-reinforced composite material, comprising: an AE sensor attached to a test body made of the fiber-reinforced composite material to detect an AE wave; a load test device that applies a load to the test body by repeating a loading pattern including raising, retaining, and unloading the load, while increasing a maximum load in sequence; a storage device that stores the AE waves detected by the AE sensor together with the loads; a frequency center of gravity calculation unit that calculates a frequency center of gravity of the AE waves on the basis of a relationship between a frequency of the AE wave and an intensity thereof; and a determination device that determines that delamination immediately preceding breakage has occurred in the case where the frequency center of gravity is less than a predetermined first frequency.

2. A method for evaluating soundness of a fiber-reinforced composite material, comprising the steps of: (A) attaching an AE sensor that detects an AE wave to a test body made of the fiber-reinforced composite material; (B) applying a load to the test body by repeating a loading pattern including raising, retaining, and unloading the load, while increasing a maximum load in sequence; (C) storing the AE waves detected by the AE sensor together with the loads; (D) calculating a frequency center of gravity of the AE waves on the basis of a relationship between a frequency of the AE wave and an intensity thereof; and (E) determining that delamination immediately preceding breakage has occurred in the case where the frequency center of gravity is less than a predetermined first frequency.

3. The method for evaluating soundness of a fiber-reinforced composite material according to claim 2, including determining a tensile load at which the frequency center of gravity is less than the first frequency as a tensile load at which the delamination occurs.

4. The method for evaluating soundness of a fiber-reinforced composite material according to claim 2, including obtaining a relationship between the load and the frequency center of gravity, determining that only micro cracks have occurred in the case where the frequency center of gravity rises in a predetermined second range with respect to an increase of the load, determining that matrix cracks have occurred in the case where the frequency center of gravity falls in a predetermined third range with respect to an increase of the load in a higher load range, and determining that the delamination has occurred in the case where the frequency center of gravity is lower than the first frequency in a still higher load range.

5. The method for evaluating soundness of a fiber-reinforced composite material according to claim 2, wherein the step (C) is performed in response to the frequency of occurrence of the AE waves exceeding a predetermined threshold value.

Description

BRIEF DESCRIPTION OF DRAWINGS

[0043] FIG. 1 shows an overall configuration of a device for evaluating the soundness of a fiber-reinforced composite material according to the present invention;

[0044] FIG. 2 illustrates a relationship between the frequency of an AE wave and the intensity thereof;

[0045] FIG. 3 illustrates an overall flow of a method for evaluating the soundness of a fiber-reinforced composite material according to the present invention;

[0046] FIG. 4 shows a conventional example of the Kaiser effect;

[0047] FIG. 5 shows a loading pattern of an example of the present invention; and

[0048] FIG. 6 illustrates a relationship between the frequency center of gravity of AE waves and the intensity thereof.

[0049] Preferred embodiments of the present invention will be described below with reference to the drawings. Throughout the figures, common components are denoted by the same reference numerals, and description thereof will not be repeated.

[0050] FIG. 1 shows an overall configuration of a soundness evaluation device 10 for a fiber-reinforced composite material according to the present invention.

[0051] Referring to the figure, the soundness evaluation device 10 includes an AE sensor 12, a load test device 14, a storage device 22, a frequency center of gravity calculation unit 24, and a determination device 26.

[0052] The AE sensor 12 is attached to a test body 1 made of a fiber-reinforced composite material (FRP) to detect AE waves 2.

[0053] The FRP is CFRP in the example described below, although it may be any other FRP.

[0054] While the test body 1 is a test specimen for tensile testing in the example described below, it may be a pressure vessel (e.g., hydrogen storage tank) or another component (e.g., component of flying object or vehicle).

[0055] The AE sensor 12 is an ultrasonic sensor, and at least one AE sensor capable of detecting AE signals with a frequency of 20 to 200 kHz, preferably 20 to 150 kHz, and further preferably 20 to 100 kHz, is used.

[0056] For example, only an AE sensor 12 for a low frequency range, capable of detecting AE signals of 20 to 100 kHz, may be used.

[0057] This is because the AE signals (AE waves 2) immediately preceding the breakage of CFRP occur at less than 100 kHz, so there is little need to detect the AE waves 2 at 100 kHz or more.

[0058] Alternatively, a high-frequency sensor for 100 to 200 kHz and a low-frequency sensor for 20 to 75 kHz may be used.

[0059] The load test device 14 applies a load 3 to the test body 1 by repeating a loading pattern 4 including raising, retaining, and unloading the load, while increasing the maximum load 3a in sequence.

[0060] The load test device 14 is a tensile test device when the test body 1 is a test specimen for the tensile test, or a pressurization device when the test body 1 is a pressure vessel, although it may be any other device.

[0061] The load 3 is measured by a load detector 11 (e.g., strain gauge) attached to the test body 1.

[0062] The loading pattern 4 is preset such that the load 3 is raised, retained, and unloaded, with the maximum load 3a being increased in sequence. The loading pattern 4 is preferably based on the ASME standards (ASME Section V, Article 11), although any other loading pattern 4 can be applied.

[0063] In FIG. 1, 20 denotes a computer, which includes a storage device 22, a computing device, and an output device 28.

[0064] The computer 20 is preferably equipped with a frequency filter 21 to detect only AE signals in the low frequency range of 20 to 100 kHz.

[0065] The storage device 22 stores the AE waves 2 detected by the AE sensor 12 together with the loads.

[0066] The computing device includes the frequency center of gravity calculation unit 24 and the determination device 26.

[0067] The frequency center of gravity calculation unit 24 calculates a frequency center of gravity 5 of AE waves 2 on the basis of a relationship between the frequency of the AE wave 2 and the intensity thereof.

[0068] The determination device 26 determines that delamination immediately preceding breakage has occurred in the case where the frequency center of gravity 5 is less than a predetermined first frequency. The “predetermined first frequency” is 80 kHz in the example described below, although it may be set in the range of 60 to 100 kHz, for example, depending on the type of the FRP.

[0069] The output device 28 is, for example, an image display device, which at least displays the result of the determination. Preferably, the output device 28 also displays a diagram of the relationship between the frequency center of gravity 5 of the AE waves 2 and the intensity thereof.

[0070] FIG. 2 illustrates a relationship between the frequency of the AE wave 2 and the intensity thereof. In the figure, the horizontal axis represents frequency of the AE wave 2 (Frequency [kHz]) and the vertical axis represents intensity of the AE wave 2 (Amplitude [mV]).

[0071] The frequency center of gravity 5 of AE waves 2, or, FCOG (Frequency Center of Gravity), is the frequency at the center of gravity (figure center) in this figure, and can be calculated using the following expression (1).

FCOG=Σ(fi×Ai)/ΣAi  (1)

[0072] Here, fi is the frequency of the AE wave 2, and Ai is the magnitude (amplitude) of the AE wave 2 at the frequency fi. The suffix i is an index value to distinguish a plurality of frequencies from each other, and takes values from 1 to n (where n is an integer of 2 or greater, preferably a sufficiently large value), and Σ indicates the sum for all values of i.

[0073] FIG. 3 shows an overall flow of a method for evaluating the soundness of a fiber-reinforced composite material according to the present invention. Referring to the figure, the soundness evaluation method of the present invention uses the soundness evaluation device 10 described above and has steps (process steps) S1 to S6.

[0074] In step S1, an AE sensor 12 detecting an AE wave 2 is attached to a test body 1 made of a fiber-reinforced composite material (FRP).

[0075] In step S2, a load 3 is applied to the test body 1 by repeating a loading pattern 4 including raising, retaining, and unloading the load, with the maximum load 3a being increased in sequence.

[0076] In step S3, the AE waves 2 detected by the AE sensor 12 are stored together with the loads 3.

[0077] This step is preferably performed when the frequency of occurrence of AE waves 2 has exceeded a predetermined threshold value. The predetermined threshold value is, for example, 10 to 50 times per second per AE sensor 12, and preferably 10 to 20 times, although it may be changed as appropriate.

[0078] In step S4, the frequency center of gravity 5 of the AE waves 2 is calculated on the basis of the relationship between the frequency of the AE wave 2 and the intensity thereof.

[0079] In step S5, it is determined whether the frequency center of gravity 5 is less than the predetermined first frequency.

[0080] If the frequency center of gravity 5 is determined to be less (YES) than the predetermined first frequency in step S5, it is determined in step S6 that delamination immediately preceding breakage has occurred. If the frequency center of gravity 5 is determined to be not less (NO) than the predetermined first frequency in step S5, steps S2 to S4 are repeated.

[0081] In step S6, the tensile load at which the frequency center of gravity 5 is less than the first frequency can be determined to be the tensile load at which delamination occurs.

[0082] Further, in step S4, the relationship between the load 3 and the frequency center of gravity 5 can be obtained, and when the frequency center of gravity 5 rises in a predetermined second range with respect to the increase of the load 3, it can be determined that only micro cracks have occurred.

[0083] When the frequency center of gravity 5 falls in a predetermined third range with respect to the increase of the load 3 in a higher load range, it can be determined that matrix cracks have occurred.

[0084] When the frequency center of gravity 5 is lower than the first frequency in an even higher load range, it can be determined that delamination has occurred.

[0085] FIG. 4 shows a conventional example of the Kaiser effect.

[0086] In the figure, the horizontal axis represents time elapsed from the start of the test (Time [s]), the right vertical axis represents load (Load [kN]), and the left vertical axis represents magnitude of the AE wave 2 (Amp [dB]).

[0087] The thick solid line in the figure indicates the loading pattern 4, and the white circles (O) each indicate the detected AE wave 2.

[0088] The loading pattern 4 in FIG. 4 shows the load being raised, retained, and unloaded twice, with the maximum load 3a being increased in sequence, until the breakage finally takes place.

[0089] Within the dashed circle indicated by A in the figure, no AE wave 2 is generated. It can thus be seen that the Kaiser effect where no AE wave 2 is generated, even if reloaded, until the previous stress value is exceeded is occurring.

[0090] In conventional soundness evaluation methods, the soundness ratio (felicity ratio (FR)) is usually used.

[0091] The soundness ratio FR can be calculated using the following expression (2).

FR=(Load that has generated AE wave 2)/(Maximum load 3a immediately before)  (2)

[0092] When the FRP is sound, the FR is 1.0 because the AE waves 2 occur only after the previous stress value is exceeded in accordance with the Kaiser effect.

[0093] When the FRP is damaged, the Kaiser effect does not occur, and the FR decreases.

[0094] Therefore, the soundness can be evaluated by setting FR>0.95, for example, to be the range of soundness.

[0095] Within the dashed circle indicated by B in FIG. 4, the loads that have generated the AE waves 2 are low and the FR has decreased, which can be considered to be a sign that the FRP has been damaged.

[0096] The conventional soundness evaluation method, however, only shows that the FRP is damaged at approximately 85 dB or less in FIG. 4; the method fails to ascertain the point in time at which delamination immediately preceding breakage occurs and the load at the point.

EXAMPLE

[0097] A description will now be made of an example of the soundness evaluation method according to the present invention.

[0098] A tensile test was conducted using the soundness evaluation device 10 described above. In this test, firstly, AE sensors 12 detecting AE waves 2 were attached to a test body 1 made of a fiber-reinforced composite material (FRP). A strain gauge was also attached as a load detector 11.

[0099] As the test body 1, a test specimen for tensile testing was used. The test specimen was made of CFRP (specifically, T700SC), with four layers of lamination (fiber layers) of 0/45/90/−45.

[0100] As the AE sensors 12, a high-frequency sensor for 100 to 200 kHz and a low-frequency sensor for 20 to 75 kHz were used.

[0101] A frequency filter 21 was also used to detect only AE signals in the low frequency range of 20 to 100 kHz.

[0102] FIG. 5 shows a loading pattern 4 in an example of the present invention. As shown in the figure, the load was applied to the test body 1 by repeating the loading pattern 4 including raising, retaining, and unloading the load three times, with the maximum load 3a being increased in order of 238, 476, and 714 MPa.

[0103] The fourth raising of the load was carried out until the breakage of the test body 1. The load at the time of breakage was 825 MPa.

[0104] The AE waves 2 detected by the AE sensors 12 were stored in the storage device 22, together with the loads detected by the strain gauge. The frequency center of gravity 5 of the AE waves 2 was calculated by the frequency center of gravity calculation unit 24 on the basis of the relationship between the frequency of the AE wave 2 and the intensity thereof.

[0105] FIG. 6 shows the relationship between the frequency center of gravity 5 of the AE waves 2 and the intensity thereof. In the figure, the horizontal axis represents intensity (Tensile Stress [MPa]) and the vertical axis represents frequency center of gravity 5 (FCOG [kHz]). The white circles (O) in the figure each represent the frequency center of gravity 5 of the detected AE waves 2.

[0106] In FIG. 6, the AE waves 2 were detected starting at about 50 MPa, and the frequency center of gravity 5 of the AE waves 2 increased from about 85 kHz to about 115 kHz while the load was raised from 50 MPa to about 430 MPa. Cross-sectional observations showed the occurrence of micro cracks in the FRP during this period. The FR was 1.0 in the range of 210 to 340 MPa in this period.

[0107] The term “micro cracks” refers to cracks occurring in the matrix of the FRP with lengths of 20 μm or more and 100 μm or less.

[0108] From the above results, it can be determined that the FRP is sound and suffers only micro cracks in the case where the frequency center of gravity 5 rises in a predetermined second range with respect to the increase of the load. In this example, the second range is from about 80 kHz to about 120 kHz, and more specifically from about 85 kHz to about 115 kHz.

[0109] In FIG. 6, the frequency center of gravity 5 of the AE waves 2 decreased from about 115 kHz to about 83 kHz while the load was raised from about 430 MPa to about 720 MPa. Cross-sectional observations showed the occurrence of matrix cracks in the FRP during this period. The FR was 0.97 in the range of 440 to 580 MPa in this period.

[0110] The term “matrix cracks” refers to cracks that have developed from the micro cracks and have the crack lengths exceeding 100 μm in the matrix, where no delamination has occurred.

[0111] From the above results, it can be determined that matrix cracks have occurred in the case where the frequency center of gravity 5 falls in a predetermined third range with respect to the increase of the load in the load range even higher than the range where micro cracks occurred. In this example, the third range is from about 120 kHz to about 80 kHz, and more specifically from about 115 kHz to about 83 kHz.

[0112] In FIG. 6, the frequency center of gravity 5 is lower than about 75 kHz in the load range from about 720 MPa to 825 MPa (breaking strength). Cross-sectional observations showed the occurrence of delamination in the FRP during this period. The FR was 0.84 in the range of 670 to 810 MPa.

[0113] The term “delamination” refers to the state in which matrix cracks have developed and some of the laminated (stacked) fiber layers have delaminated.

[0114] From the above results, it can be determined that delamination has occurred in the case where the frequency center of gravity 5 is lower than the first frequency in the load range even higher than the range in which the matrix cracks occurred. The first frequency is lower than the minimum value of the third range in this example, and is about 80 kHz or about 75 kHz, although it may be set in the range of 60 to 100 kHz, for example, depending on the type of the FRP.

[0115] The above example has confirmed that the FRP failure occurs in the order of micro cracks, matrix cracks, delamination, and breakage. In the case of micro cracks and matrix cracks, the frequency center of gravity 5 is 80 kHz or more and 120 kHz or less, and the FR exceeds 0.95, indicating that the FRP is in the range of soundness.

[0116] It can also be determined that when the frequency center of gravity 5 is less than the predetermined first frequency, delamination immediately preceding breakage has occurred. In this example, the first frequency is 80 kHz, although it may be set in the range of 60 to 100 kHz, for example, depending on the type of the FRP.

[0117] Further, the tensile load at which the frequency center of gravity 5 is not more than the first frequency can be determined to be the tensile load at which delamination occurs.

[0118] According to the present invention described above, the load is applied to the test body 1 by repeating the loading pattern 4 including raising, retaining, and unloading the load, with the maximum load 3a being increased in sequence. As such, any given loading pattern 4 can be applied, without being limited to a loading pattern 4 that constantly increases the load over time.

[0119] The frequency center of gravity 5 of the AE waves 2 is calculated on the basis of the relationship between the frequency of the AE wave 2 and the intensity thereof, and it is determined that delamination immediately preceding breakage has occurred in the case where the frequency center of gravity 5 is less than the predetermined first frequency (e.g., less than 80 kHz). This enables easy and reliable detection of the delamination immediately preceding breakage.

[0120] Even if the maximum value of the load initially applied to the test body 1 is set incorrectly, the occurrence of the delamination immediately preceding breakage can be determined before the maximum value is reached, so the tensile strength of the test body 1 can be evaluated using the Kaiser effect.

[0121] In addition, since the test can be terminated at the time when the occurrence of the delamination immediately preceding breakage is determined, soundness evaluation can be done without testing until the breakage actually occurs.

[0122] Further, as long as the frequency center of gravity 5 is above the first frequency, the FRP can be determined to be in the range of soundness. The soundness evaluation can thus be omitted or simplified, and the evaluation time can be reduced even when applying a loading pattern 4 including load retention or load reduction (unloading).

[0123] Furthermore, the AE signals detected by the high-frequency sensor for 100 to 200 kHz have almost no effect on the frequency center of gravity 5 below the first frequency, so the high-frequency sensor can be omitted, leading to halving the number of sensors installed. In this case, it is preferable to use a frequency filter 21 to detect only the AE signals in the low frequency range of 20 to 100 kHz.

[0124] The present invention is not limited to the above-described embodiments, and various modifications are of course possible without departing from the gist of the present invention.

REFERENCE SIGNS LIST

[0125] 1: test body; 2: AE wave; 3: load; 3a: maximum load; 4: loading pattern; 5: frequency center of gravity; 10: soundness evaluation device; 11: load detector; 12: AE sensor; 14: load test device; 20: computer; 21: frequency filter; 22: storage device; 24: frequency center of gravity calculation unit; 26: determination device; and 28: output device.