CN113109429B - Reference block for aircraft defect evaluation and application method thereof - Google Patents
Reference block for aircraft defect evaluation and application method thereof Download PDFInfo
- Publication number
- CN113109429B CN113109429B CN202110302562.1A CN202110302562A CN113109429B CN 113109429 B CN113109429 B CN 113109429B CN 202110302562 A CN202110302562 A CN 202110302562A CN 113109429 B CN113109429 B CN 113109429B
- Authority
- CN
- China
- Prior art keywords
- defect
- reference block
- aircraft
- rib
- mark
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N27/00—Investigating or analysing materials by the use of electric, electrochemical, or magnetic means
- G01N27/72—Investigating or analysing materials by the use of electric, electrochemical, or magnetic means by investigating magnetic variables
- G01N27/82—Investigating or analysing materials by the use of electric, electrochemical, or magnetic means by investigating magnetic variables for investigating the presence of flaws
- G01N27/90—Investigating or analysing materials by the use of electric, electrochemical, or magnetic means by investigating magnetic variables for investigating the presence of flaws using eddy currents
Landscapes
- Chemical & Material Sciences (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Electrochemistry (AREA)
- Physics & Mathematics (AREA)
- Health & Medical Sciences (AREA)
- Life Sciences & Earth Sciences (AREA)
- Analytical Chemistry (AREA)
- Biochemistry (AREA)
- General Health & Medical Sciences (AREA)
- General Physics & Mathematics (AREA)
- Immunology (AREA)
- Pathology (AREA)
- Investigating Or Analyzing Materials By The Use Of Magnetic Means (AREA)
Abstract
The invention relates to the field of aircraft defect evaluation, in particular to a reference block for aircraft defect evaluation and a use method thereof, and the reference block is particularly a triangular reference block with identical external lines cut at the joint junction of horizontal ribs and vertical ribs and a wallboard, wherein the reference block is provided with a mark I-a mark II for marking defects, the rib part on the reference block is provided with a plurality of groups of bolt holes for assembling bolts, and the specific use steps are as follows: s1: selecting raw materials; s2: processing at a mark seven-mark nine mark position; s3: the horizontal direction and the vertical direction of the surface of the position marked by the seven marks and the nine marks at the bolt hole are respectively processed with defects; s4: eddy current flaw detection of the ribs and the R angle of the airplane; the risk level of defects is more accurately estimated by setting the reference block, important data support is provided for aircraft structure repair and service life estimation, and the special defect size design is designed for exposing 2-4mm at the R arc-shaped inner surface with curvature smaller than 4 and the bolt gasket.
Description
Technical Field
The invention relates to the field of aircraft defect evaluation, in particular to a reference block for aircraft defect evaluation and a using method thereof.
Background
The standard number HB 20193-2014 of aviation industry standard of the people's republic of China (4.4.4.2.2) prescribes that the material and the state of a comparison sample are the same as those of a detected piece in eddy current detection of near-surface defects; or the conductivity, the surface state, the shape and the position of the artificial defect should be similar to those of the detected piece ", and the standard appendix A gives the dimensions and the tolerance of an aluminum alloy standard sample, and the sample is suitable for reproducing the defect detection result of a large plane area, and has the defect of being not suitable for detecting sensitivity adjustment and defect size assessment of a part with a special structure shape, such as a large curvature or an inner arc surface part of an R angle. The structural shape and position of the detection area influence the distribution and density of the vortex field in the vortex detection process, so that false alarm of equipment and unreliable detection result are caused. In particular to an aircraft body with complex and changeable structure, the connection parts of horizontal ribs, vertical ribs and wall plates on the structural parts of a central wing, a horizontal tail, a vertical tail and the like of the aircraft are connected in an arc transition mode, and the parts are high-incidence areas of surface fatigue cracks. The test block and the use method of the reference for debugging the sensitivity of the eddy current detection of the defects in the special-shaped area and evaluating the sizes of the defects are not applicable to the national standard and the industry standard at present.
Another disadvantage of an aluminum alloy standard sample as set forth in appendix A of the navigation mark "HB 20193-2014" is that the effect of the size of the ratio of defect length to eddy current probe outer diameter on the eddy current probe defect detection sensitivity and defect size assessment is not fully accounted for. When the defect length is smaller than or equal to the outer diameter of the probe, the defect signal of the same size is weakened, and the defects are frequently generated in fatigue cracks of the machine body structure. For the surface fatigue crack defect detection of the aircraft structure, a shielding high-frequency point probe is generally adopted for eddy current detection, and the outer diameter of the probe is 2-4 mm. After the bolt gasket at the bolt hole of the machine body structure is assembled, the defect is exposed for 2-4 mm. Therefore, a reference block with proper defect size and special position is specially designed, the using method is researched, and the defects are more reasonably evaluated.
Disclosure of Invention
In order to solve the above problems, the present invention provides a reference block for evaluating the defects of an aircraft and a method for using the same.
A reference block for aircraft defect evaluation is a triangular reference block with identical external lines cut at the joint and junction of horizontal ribs, vertical ribs and wall plates, wherein a mark I-a mark nine for marking defects is arranged on the reference block, and a plurality of groups of bolt holes for assembling bolts are formed in the rib parts on the reference block.
The application method of the reference block for aircraft defect evaluation comprises the following specific steps:
s1: selecting a cutting base material at the joint junction of the horizontal rib and the vertical rib and the wallboard from the scrapped aircraft center wing as a raw material for manufacturing a test block;
s2: processing 9 defects at mark one-mark nine mark positions;
s3: the horizontal direction and the vertical direction of the surface of the marked seven-marked nine-marked position shown in the bolt hole are respectively processed into defects, and after the processing of the marked seven-marked nine-marked position is finished, a bolt and a gasket with uniform specification are assembled at the 3 positions, so that the length of the crack exposed outside the gasket in the horizontal direction of the marked seven-marked nine-marked position is 2mm, and the length of the crack exposed outside the gasket in the vertical direction is 4mm;
s4: airplane rib and R-angle eddy current flaw detection:
a: firstly, a high-frequency eddy current point probe KAS-34H-66.10.1 is used, the outer diameter size of the probe is 3mm, and the detection sensitivity is calibrated at the positions of the defect number seven and the defect number one respectively;
b: when the aircraft rib is detected, parameters of eddy current equipment are regulated, the probe lightly strokes through the defect number seven, and the signal impedance amplitude reaches 20% of the full scale of the screen, so that the surface quality condition of the aircraft rib can be detected;
c: when an amplitude signal appears on a screen of the vortex equipment for scanning the surface of the rib of the airplane, comparing whether the amplitude of the signal reaches 20%, and using a high-frequency point probe to gently repeat to retrace defects and observe the amplitude of the signal;
d: the high-frequency point probe is used for gently repeating to scan back the seventh defect, the eighth defect and the ninth defect, and the signal amplitude of the defect on the rib is compared with the amplitude of the seventh defect-ninth defect on the test block;
e: the height of the signal amplitude of the defect on the rib is closest to the height of the amplitude of the number defects on the test block, and the depth and the size of the defect at the position of the rib of the aircraft can be estimated;
f: when the defect signal amplitude of the position is far more than that of the No. nine defect of the reference block, the defect reaching scrapping level of the position can be directly estimated, and the defect estimation on the radian of the large curvature R angle is in the same way.
The marks one-nine in the step S2 are in one-to-one correspondence with the defects one to nine.
The 3 positions of the step S3 are respectively marked with seven bolt holes, marked with eight bolt holes and marked with nine bolt holes.
The first defect, the second defect and the third defect are positioned at the tangential position of the large curvature arc R and the horizontal rib, and the fourth defect, the fifth defect and the sixth defect are positioned at the right middle position of the surface of the large curvature arc R.
The specification of the defect number one and the defect number four in the step S2 is as follows: depth 0.2+ -0.02 mm, length 5+ -0.05 mm; the second defect and the fifth defect have the following specifications: depth 0.3+ -0.03 mm, length 5+ -0.05 mm; the defect number three and defect number six are: depth 0.5+ -0.05 mm, length 5+ -0.05 mm; the specification of the seventh position defect is: the depth in the horizontal direction is 0.2 plus or minus 0.02mm, the length is 4 plus or minus 0.04mm, the depth in the vertical direction is 0.2 plus or minus 0.02mm, and the length is 6 plus or minus 0.06mm; the eighth defect specification is: the depth in the horizontal direction is 0.3+/-0.03 mm, the length is 4+/-0.04 mm, the depth in the vertical direction is 0.3+/-0.03 mm, and the length is 6+/-0.06 mm; the defect specification of the ninth is: the depth in the horizontal direction is 0.5 plus or minus 0.05mm, the length is 4 plus or minus 0.04mm, the depth in the vertical direction is 0.5 plus or minus 0.05mm, and the length is 6 plus or minus 0.06mm.
If the amplitude of c in the step S4 is not 20%, it can be determined as the surface state interference signal.
If the value of c exceeds 20% in step S4, it can be determined that there is a defect.
The beneficial effects of the invention are as follows: the risk level of defects is estimated more accurately by setting the reference block, important data support is provided for aircraft structure repair and service life estimation, and a scientific and effective defect estimation method is provided for aiming at special defect size design of exposing 2-4mm at the R arc-shaped inner surface with curvature smaller than 4 and the bolt gasket, and the influence of the size of the ratio of the defect length to the outer diameter of the eddy current detection probe on eddy current detection defect detection sensitivity and defect size estimation is fully considered, so that the blank of the industry is filled.
Drawings
The invention will be further described with reference to the drawings and examples.
FIG. 1 is a schematic diagram of a front view of a reference block according to the present invention;
FIG. 2 is a schematic top view of a reference block according to the present invention;
FIG. 3 is a schematic diagram of a left-hand structure of a reference block according to the present invention;
FIG. 4 is a schematic cross-sectional view of a large curvature arc of the present invention;
fig. 5 is a schematic structural diagram of a defect after the rib part bolt hole is assembled.
Detailed Description
The present invention will be further described in the following to make the technical means, the creation characteristics, the achievement of the purpose and the effect of the present invention easy to understand.
As shown in fig. 1 to 5, a reference block for evaluating an aircraft defect, specifically, a triangular reference block with identical external lines is cut at the joint junction of a horizontal rib, a vertical rib and a wallboard, a mark 1-mark nine 9 for marking the defect is arranged on the reference block, and a plurality of groups of bolt holes 10 for assembling bolts are arranged at the rib part on the reference block.
The risk level of defects is estimated more accurately by setting the reference block, important data support is provided for aircraft structure repair and service life estimation, and a scientific and effective defect estimation method is provided for aiming at special defect size design of exposing 2-4mm at the R arc-shaped inner surface with curvature smaller than 4 and the bolt gasket, and the influence of the size of the ratio of the defect length to the outer diameter of the eddy current detection probe on eddy current detection defect detection sensitivity and defect size estimation is fully considered, so that the blank of the industry is filled.
The application method of the reference block for aircraft defect evaluation comprises the following specific steps:
s1: selecting a base material as shown in the attached drawings from the scraped aircraft center wing to cut the base material as a raw material for manufacturing a test block, wherein the three views of the test block are shown in fig. 1, 2 and 3, the sectional view of a large curvature circular arc R4 at the joint of the horizontal rib and a wall plate is shown in fig. 4, the assembling state of bolt holes on the horizontal rib is shown in fig. 5, and the material is cut from the aircraft in situ, so that the consistency of the conductivity, the surface state and the shape of the test block and the detected aircraft state is effectively ensured;
s2: as shown in fig. 2, 9 defects are processed at the mark positions of 1-9 marks, wherein the first defect, the second defect and the third defect are positioned at the positions where the large curvature circular arc R is tangent to the horizontal rib, the fourth defect, the fifth defect and the sixth defect are positioned at the position right in the middle of the surface of the large curvature circular arc R, the schematic diagram of the defect position on the large curvature circular arc is shown in fig. 4, A represents the defect at the position middle of the surface radian of the large curvature circular arc R, and B represents the defect at the position where the circular arc is tangent to the horizontal rib;
s3: the horizontal direction and the vertical direction of the surface of the marked position seven 7-9 in the bolt hole of the figure 2 are respectively processed into defects, and after the processing of the marked position seven 7-9 in the figure 2 is finished, a bolt and a gasket with uniform specification are assembled at the position 3, so that the crack length outside the gasket exposed in the horizontal direction of the marked position seven 7-9 is 2mm, and the crack length outside the gasket exposed in the vertical direction is 4mm;
s4: airplane rib and R-angle eddy current flaw detection:
a: firstly, a high-frequency eddy current point probe KAS-34H-66.10.1 is used, the outer diameter size of the probe is 3mm, and the detection sensitivity is calibrated at the positions of the defect number seven and the defect number one respectively;
b: when the aircraft rib is detected, parameters of eddy current equipment are regulated, the probe lightly strokes through the defect number seven, and the signal impedance amplitude reaches 20% of the full scale of the screen, so that the surface quality condition of the aircraft rib can be detected;
c: when an amplitude signal appears on a screen of the vortex equipment for scanning the surface of the rib of the airplane, comparing whether the amplitude of the signal reaches 20%, and using a high-frequency point probe to gently repeat to retrace defects and observe the amplitude of the signal;
d: the high-frequency point probe is used for gently repeating to scan back the seventh defect, the eighth defect and the ninth defect, and the signal amplitude of the defect on the rib is compared with the amplitude of the first defect-ninth defect on the test block;
e: the height of the signal amplitude of the defect on the rib is closest to the height of the amplitude of the number defects on the test block, and the depth and the size of the defect at the position of the rib of the aircraft can be estimated;
f: when the defect signal amplitude of the position is far more than that of the No. nine defect of the reference block, the defect reaching scrapping level of the position can be directly estimated, and the defect estimation on the radian of the large curvature R angle is in the same way.
The marks 1-9 in the step S2 are in one-to-one correspondence with the defects one-nine.
The first defect, the second defect and the third defect are positioned at the tangential position of the large curvature arc R and the horizontal rib, and the fourth defect, the fifth defect and the sixth defect are positioned at the right middle position of the surface of the large curvature arc R.
The specification of the defect number one and the defect number four in the step S2 is as follows: depth 0.2+ -0.02 mm, length 5+ -0.05 mm; the second defect and the fifth defect have the following specifications: depth 0.3+ -0.03 mm, length 5+ -0.05 mm; the defect number three and defect number six are: depth 0.5+ -0.05 mm, length 5+ -0.05 mm; the specification of the seventh position defect is: the depth in the horizontal direction is 0.2 plus or minus 0.02mm, the length is 4 plus or minus 0.04mm, the depth in the vertical direction is 0.2 plus or minus 0.02mm, and the length is 6 plus or minus 0.06mm; the eighth defect specification is: the depth in the horizontal direction is 0.3+/-0.03 mm, the length is 4+/-0.04 mm, the depth in the vertical direction is 0.3+/-0.03 mm, and the length is 6+/-0.06 mm; the defect specification of the ninth is: the depth in the horizontal direction is 0.5 plus or minus 0.05mm, the length is 4 plus or minus 0.04mm, the depth in the vertical direction is 0.5 plus or minus 0.05mm, and the length is 6 plus or minus 0.06mm.
The marks 1-9 are respectively mark 1, mark 2, mark 3, mark four 4, mark five 5, mark six 6, mark seven 7, mark eight 8 and mark nine 9.
The 3 positions of the step S3 are respectively provided with the 3 bolt holes marked with seven 7, eight 8 and nine 9.
If the amplitude of c in the step S4 is not 20%, it can be determined as the surface state interference signal.
If the value of c exceeds 20% in step S4, it can be determined that there is a defect.
Reference numeral 11 of fig. 5 is a bolt spacer.
The foregoing has shown and described the basic principles, principal features and advantages of the invention. It will be understood by those skilled in the art that the present invention is not limited to the embodiments described above, and that the above embodiments and descriptions are merely illustrative of the principles of the present invention, and various changes and modifications may be made without departing from the spirit and scope of the invention, which is defined in the appended claims. The scope of the invention is defined by the appended claims and equivalents thereof.
Claims (7)
1. The utility model provides a use method of reference block that aircraft defect was estimated and is used, this aircraft defect is estimated and is used the reference block specifically for horizontal rib, vertical rib and wallboard juncture cutting outside line identical triangle form reference block, is provided with on the reference block and is used for marking mark one (1) -mark nine (9) of defect, and the rib position on the reference block is provided with a plurality of bolt holes (10) of being used for assembly bolt, its characterized in that: the using method comprises the following specific steps:
s1: selecting a cutting base material at the joint junction of the horizontal rib and the vertical rib and the wallboard from the scrapped aircraft center wing as a raw material for manufacturing a test block;
s2: processing nine defects at mark one (1) -mark nine (9) mark positions;
s3: the positions of the bolt holes are marked with seven (7) -nine (9) marks, the surface of the positions is respectively processed with defects in the horizontal direction and the vertical direction, after the positions of the marks of the seven (7) -nine (9) marks are processed with the defects, the positions of the positions 3 are assembled with bolts and gaskets with uniform specifications, so that the lengths of the cracks exposed out of the gaskets in the horizontal direction of the positions of the marks seven (7) -nine (9) are 2mm, and the lengths of the cracks exposed out of the gaskets in the vertical direction are 4mm;
s4: airplane rib and R-angle eddy current flaw detection:
a: firstly, a high-frequency eddy current point probe KAS-34H-66.10.1 is used, the outer diameter size of the probe is 3mm, and the detection sensitivity is calibrated at the positions of the defect number seven and the defect number one respectively;
b: when the aircraft rib is detected, parameters of eddy current equipment are regulated, the probe lightly strokes through the defect number seven, and the signal impedance amplitude reaches 20% of the full scale of the screen, so that the surface quality condition of the aircraft rib can be detected;
c: when an amplitude signal appears on a screen of the vortex equipment for scanning the surface of the rib of the airplane, comparing whether the amplitude of the signal reaches 20%, and using a high-frequency point probe to gently repeat to retrace defects and observe the amplitude of the signal;
d: the high-frequency point probe is used for gently repeating to scan back the seventh defect, the eighth defect and the ninth defect, and the signal amplitude of the defect on the rib is compared with the amplitude of the seventh defect-ninth defect on the test block;
e: the height of the signal amplitude of the defect on the rib is closest to the height of the amplitude of the number defects on the test block, and the depth and the size of the defect at the position of the rib of the aircraft can be estimated;
f: when the defect signal amplitude of the position is far more than that of the No. 9 defect of the reference block, the defect reaching scrapping level of the position can be directly estimated, and the defect estimation on the radian of the large curvature R angle follows the same method.
2. The method of using a reference block for aircraft defect assessment according to claim 1, wherein: and the marks one (1) -nine (9) in the step S2 correspond to the defects one by one.
3. The method of using a reference block for aircraft defect assessment according to claim 1, wherein: the first defect, the second defect and the third defect are positioned at the tangential position of the large curvature arc R and the horizontal rib, and the fourth defect, the fifth defect and the sixth defect are positioned at the right middle position of the surface of the large curvature arc R.
4. The method of using a reference block for aircraft defect assessment according to claim 1, wherein: the specification of the defect number one and the defect number four in the step S2 is as follows: depth 0.2+ -0.02 mm, length 5+ -0.05 mm; the second defect and the fifth defect have the following specifications: depth 0.3+ -0.03 mm, length 5+ -0.05 mm; the defect number three and defect number six are: depth 0.5+ -0.05 mm, length 5+ -0.05 mm; the specification of the seventh position defect is: the depth in the horizontal direction is 0.2 plus or minus 0.02mm, the length is 4 plus or minus 0.04mm, the depth in the vertical direction is 0.2 plus or minus 0.02mm, and the length is 6 plus or minus 0.06mm; the eighth defect specification is: the depth in the horizontal direction is 0.3+/-0.03 mm, the length is 4+/-0.04 mm, the depth in the vertical direction is 0.3+/-0.03 mm, and the length is 6+/-0.06 mm; the defect specification of the ninth is: the depth in the horizontal direction is 0.5 plus or minus 0.05mm, the length is 4 plus or minus 0.04mm, the depth in the vertical direction is 0.5 plus or minus 0.05mm, and the length is 6 plus or minus 0.06mm.
5. The method of using a reference block for aircraft defect assessment according to claim 1, wherein: the 3 positions of the step S3 are respectively provided with 3 bolt holes of a mark seven (7), a mark eight (8) and a mark nine (9).
6. The method of using a reference block for aircraft defect assessment according to claim 1, wherein: if the amplitude of c in the step S4 is not 20%, it can be determined as the surface state interference signal.
7. The method of using a reference block for aircraft defect assessment according to claim 1, wherein: if the value of c exceeds 20% in step S4, it can be determined that there is a defect.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110302562.1A CN113109429B (en) | 2021-03-22 | 2021-03-22 | Reference block for aircraft defect evaluation and application method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110302562.1A CN113109429B (en) | 2021-03-22 | 2021-03-22 | Reference block for aircraft defect evaluation and application method thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113109429A CN113109429A (en) | 2021-07-13 |
| CN113109429B true CN113109429B (en) | 2023-09-19 |
Family
ID=76710447
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110302562.1A Active CN113109429B (en) | 2021-03-22 | 2021-03-22 | Reference block for aircraft defect evaluation and application method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113109429B (en) |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2006133031A (en) * | 2004-11-04 | 2006-05-25 | Toyota Motor Corp | Method and device for detecting defect of casting member |
| CN203587561U (en) * | 2013-11-14 | 2014-05-07 | 沈阳黎明航空发动机(集团)有限责任公司 | Eddy current flaw detection reference block |
| CN104330253A (en) * | 2014-11-28 | 2015-02-04 | 中航沈飞民用飞机有限责任公司 | Method applied to analysis of damage tolerance feature of stiffened wall panel |
| CN106841399A (en) * | 2016-12-19 | 2017-06-13 | 内蒙古北方重工业集团有限公司 | A kind of bar ultrasound automatic detection flat-bottom hole reference block and preparation method |
| CN108872363A (en) * | 2018-05-25 | 2018-11-23 | 中航金属材料理化检测科技有限公司 | The method of artificial cutting detection workpiece, defect based on depth consecutive variations |
| CN109239185A (en) * | 2018-08-24 | 2019-01-18 | 中国飞机强度研究所 | A kind of acoustic fatigue test part, design method, test method |
| CN109709206A (en) * | 2017-10-26 | 2019-05-03 | 中国商用飞机有限责任公司 | The measurement method of the defect of R corner structure based on ultrasonic phased array technology |
| CN110672390A (en) * | 2019-10-17 | 2020-01-10 | 成都飞机工业（集团）有限责任公司 | Nondestructive testing reference block for composite material assembly structure and manufacturing method |
| CN111323484A (en) * | 2020-04-17 | 2020-06-23 | 中国飞机强度研究所 | Method for manufacturing kiss-joint defect reference test block and method for detecting by using test block |
| CN111474238A (en) * | 2020-04-30 | 2020-07-31 | 国电锅炉压力容器检验有限公司 | Universal bolt hole inner wall eddy current detection method and detection device |
-
2021
- 2021-03-22 CN CN202110302562.1A patent/CN113109429B/en active Active
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2006133031A (en) * | 2004-11-04 | 2006-05-25 | Toyota Motor Corp | Method and device for detecting defect of casting member |
| CN203587561U (en) * | 2013-11-14 | 2014-05-07 | 沈阳黎明航空发动机(集团)有限责任公司 | Eddy current flaw detection reference block |
| CN104330253A (en) * | 2014-11-28 | 2015-02-04 | 中航沈飞民用飞机有限责任公司 | Method applied to analysis of damage tolerance feature of stiffened wall panel |
| CN106841399A (en) * | 2016-12-19 | 2017-06-13 | 内蒙古北方重工业集团有限公司 | A kind of bar ultrasound automatic detection flat-bottom hole reference block and preparation method |
| CN109709206A (en) * | 2017-10-26 | 2019-05-03 | 中国商用飞机有限责任公司 | The measurement method of the defect of R corner structure based on ultrasonic phased array technology |
| CN108872363A (en) * | 2018-05-25 | 2018-11-23 | 中航金属材料理化检测科技有限公司 | The method of artificial cutting detection workpiece, defect based on depth consecutive variations |
| CN109239185A (en) * | 2018-08-24 | 2019-01-18 | 中国飞机强度研究所 | A kind of acoustic fatigue test part, design method, test method |
| CN110672390A (en) * | 2019-10-17 | 2020-01-10 | 成都飞机工业（集团）有限责任公司 | Nondestructive testing reference block for composite material assembly structure and manufacturing method |
| CN111323484A (en) * | 2020-04-17 | 2020-06-23 | 中国飞机强度研究所 | Method for manufacturing kiss-joint defect reference test block and method for detecting by using test block |
| CN111474238A (en) * | 2020-04-30 | 2020-07-31 | 国电锅炉压力容器检验有限公司 | Universal bolt hole inner wall eddy current detection method and detection device |
Non-Patent Citations (1)
| Title |
|---|
| 飞机维修中涡流检测对比试块的设计和应用;张亚荣 等;无损检测;第37卷(第09期);第62-64、68页 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN113109429A (en) | 2021-07-13 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US7320241B2 (en) | Ultrasonic inspection reference standard for composite materials | |
| CN105973177B (en) | A kind of lossless detection method and PCB lossless detection method of back drill stub | |
| CN203587561U (en) | Eddy current flaw detection reference block | |
| CN205120670U (en) | A special reference block that is used for path pipe welding seam supersound to climb wave inspection | |
| CN109142533B (en) | Method and equipment for rapidly detecting internal defects of castings | |
| CN104515810B (en) | A kind of laser melting coating remanufactures part defect type ultrasound analysis method | |
| CN110441305B (en) | Surface coverage rate inspection method for secondary shot blasting | |
| CN106645433B (en) | Three-dimensional calibration test block for ultrasonic automatic detection system | |
| CN113109429B (en) | Reference block for aircraft defect evaluation and application method thereof | |
| CN106706759B (en) | Method for evaluating defects of welding joint of P92 steel main steam pipeline of ultra-supercritical generator set | |
| CN109596702B (en) | Nondestructive testing device and method for surface defects | |
| CN203838126U (en) | Ultrasonic flaw detection reference block of composite structure | |
| CN212228819U (en) | Universal bolt hole eddy current testing test block set | |
| CN107044815B (en) | Special gauge for size and position degree of spigot of engine bearing cover and detection method | |
| US20210010947A1 (en) | Multiple test panel assembly | |
| CN108845025B (en) | Eddy current detection system and method for pin hole with copper bush | |
| CN107101651B (en) | Equivalent M integral-based material damage area calibration method | |
| CN214278035U (en) | Cylindrical ultrasonic detection reference block | |
| CN215449121U (en) | Ultrasonic flaw detection test block for large-sized shaft part | |
| CN210220942U (en) | Improve frock of right side body inspection degree of accuracy and inspection efficiency | |
| CN213633291U (en) | Gas production tree/oil production tree bolt simulation test block | |
| CN216771610U (en) | Reference block for aluminum alloy ultrasonic phased array detection | |
| CN209386918U (en) | A kind of vehicle body protection cover board cubing of automatic measurement | |
| CN215678207U (en) | Contrast test tube suitable for in-service drilling rod detects | |
| CN106404921A (en) | Preparation method of sample for ultrasonic nondestructive detection proficiency testing |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |