CN112461895A - Thermal imaging detection system and method for aircraft tire through damage - Google Patents
Thermal imaging detection system and method for aircraft tire through damage Download PDFInfo
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- 238000001931 thermography Methods 0.000 title claims abstract description 78
- 238000001514 detection method Methods 0.000 title claims abstract description 58
- 238000000034 method Methods 0.000 title description 11
- 238000012360 testing method Methods 0.000 claims abstract description 29
- 238000013500 data storage Methods 0.000 claims abstract description 24
- 230000000149 penetrating effect Effects 0.000 claims abstract description 21
- 238000003860 storage Methods 0.000 claims abstract description 20
- 230000005540 biological transmission Effects 0.000 claims abstract description 10
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 claims description 14
- 239000007789 gas Substances 0.000 claims description 12
- 229910052757 nitrogen Inorganic materials 0.000 claims description 7
- 239000003086 colorant Substances 0.000 description 8
- 238000009826 distribution Methods 0.000 description 6
- 230000035515 penetration Effects 0.000 description 6
- 230000002950 deficient Effects 0.000 description 4
- 230000007613 environmental effect Effects 0.000 description 4
- 230000007547 defect Effects 0.000 description 3
- 239000000126 substance Substances 0.000 description 3
- 230000002159 abnormal effect Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000007689 inspection Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 230000005855 radiation Effects 0.000 description 2
- 238000013459 approach Methods 0.000 description 1
- 239000000872 buffer Substances 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000009191 jumping Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012634 optical imaging Methods 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 238000011179 visual inspection Methods 0.000 description 1
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N25/00—Investigating or analyzing materials by the use of thermal means
- G01N25/72—Investigating presence of flaws
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Abstract
The application discloses thermal imaging detecting system of aircraft tire penetrability damage includes: the system comprises an air storage tank for filling a pressure medium with a certain temperature into a tire, an inflating device capable of being communicated with the tire, a test bench connected with the aircraft tire, a thermal imaging detector arranged at a position with a certain distance from the aircraft tire, an automatic judgment system connected with the thermal imaging detector and an electronic data storage server; the gas storage tank is connected with the gas charging device through a gas transmission pipeline; the inflation device is connected with the aircraft tire connected in the test bench; the automatic judgment system is connected with the electronic data storage server through a data line. The application belongs to the technical field of tire detection, and solves the problems of low detection precision, low efficiency and low automation degree of the penetrating damage of the aircraft tire.
Description
Technical Field
The application belongs to the technical field of tire detection, and particularly relates to a thermal imaging detection system and method for penetrating damage of an aircraft tire.
Background
The aircraft tire bears the weight of an airplane, absorbs the bumping and jumping of the airplane during taxiing, buffers the impact of the airplane during landing and helps to absorb the impact energy, and the like, and is one of the important safety components in the airplane landing gear system. The aviation tires mostly adopt an inflatable and tubeless structure; when the tire is manufactured, used and repaired, the tire tread or the tire sidewall position is damaged by foreign matters in a penetrating way, the pressure maintaining performance of the tire is failed, the tire is delaminated or blown out, and the seaworthiness of an airplane and the life safety of passengers are seriously influenced.
In the prior art, detection means such as manual visual inspection and laser nondestructive detection are adopted for the penetrating damage of the aircraft tire, the manual detection efficiency is low, the precision is low, the laser nondestructive detection can only detect whether separation layers and bubbles occur inside the tire structure, and the tire cannot be detected whether penetrating prick or other damage occurs.
It is particularly important to design a thermal imaging detection system and a thermal imaging detection method for detecting the through damage of the aircraft tire, wherein the thermal imaging detection system and the thermal imaging detection method can detect the through damage of the aircraft tire, have high detection precision and high efficiency, do not damage the tire, and have the capabilities of automatic detection, judgment and data storage.
Disclosure of Invention
Aiming at the defects in the prior art, the thermal imaging detection system and method for the through damage of the aircraft tire are provided, and the through damage of the aircraft tire can be detected, and the thermal imaging detection system and method are high in detection precision, high in efficiency, free of damage to the tire and high in automation degree.
In order to solve the technical problem, the technical scheme adopted by the application is as follows:
the application provides a thermal imaging detecting system of aircraft tire through damage includes: the system comprises an air storage tank, an inflating device which can be communicated with a tire, a test board which is connected with the aircraft tire, a thermal imaging detector which is arranged at a position with a certain distance from the aircraft tire, an automatic judgment system which is connected with the thermal imaging detector and an electronic data storage server;
the gas storage tank is connected with the gas charging device through a gas transmission pipeline;
the inflation device is connected with the aircraft tire connected in the test bench;
the automatic judgment system is connected with the electronic data storage server through a data line.
Optionally, the test bench includes a test rack, a lifting device capable of transporting the aircraft tire, a clamping device fixed on the test rack, a chuck for clamping the aircraft tire, a motor fixed on the test rack, and a forward and backward rotation device connected to the motor;
one end of the inflating device is connected with the clamping device, and the other end of the inflating device is matched with the chuck and is connected with the aircraft tire through the chuck.
Optionally, the thermal imaging detection system for aircraft tire through damage, the lifting device is connected with the test rack through a hinge.
Optionally, a thermal imaging detecting system of aircraft tire penetrability damage, clamping device is pneumatic telescoping device, include with the stiff end that the test rack is connected to reach the flexible end that links to each other with the stiff end.
Optionally, the thermal imaging detection system for aircraft tire through damage comprises a chuck, a first clamping part and a second clamping part; the first clamping part and the second clamping part are provided with a first side attached to the aircraft tire and a second side connected with the telescopic end of the clamping device.
Optionally, the thermal imaging detection system for aircraft tire through damage, the flexible end of clamping device has the pivot, first clamping part with the second clamping part respectively with the flexible end of clamping device the pivot links to each other.
Optionally, a thermal imaging detecting system of aircraft tire penetrability damage, the chuck has the through-hole, aerating device with the through-hole of chuck is interference fit, aerating device passes through the through-hole of chuck is connected with the aircraft tire.
Optionally, the thermal imaging detection system for the penetrating damage of the aircraft tire is characterized in that the pressure medium in the air storage tank is high-pressure nitrogen, the chemical property of the nitrogen is stable, and the operation safety is improved.
Optionally, a thermal imaging detecting system of aircraft tire penetrability damage, the motor through the pivot with just reverse device is connected.
Optionally, in the thermal imaging detection system for aircraft tire penetration damage, the transmission mode between the forward and reverse rotation device and the aircraft tire clamped on the clamping disc is friction transmission.
Optionally, the thermal imaging detector detection location is no more than 1 meter from the aircraft tire being detected.
The application provides a thermal imaging detection method for penetrating damage of an aircraft tire, which comprises the following steps:
filling a pressure medium with a certain temperature into the aviation tire;
after the air pressure in the aircraft tire is stable, the thermal imaging detector senses the temperature of an area, opposite to the thermal imaging detector, on the aircraft tire and generates a thermal image;
driving the aircraft tire to rotate clockwise or anticlockwise;
during the rotation of the aircraft tire, the thermal imaging detector senses the temperature of an area, opposite to the thermal imaging detector, of the aircraft tire and generates a corresponding thermal image;
and the thermal image is transmitted to an automatic judgment system, and the automatic judgment system judges whether the aircraft tire has an air leakage point and the position of the air leakage point according to the generated thermal image.
The forward and reverse rotation device drives the aircraft tire to rotate clockwise or anticlockwise until the thermal imaging detector finishes detecting the whole aircraft tire. Because different colors on the thermograph represent the distribution of the surface temperature of the aircraft tire, the darker the color represents the lower the temperature, the detected aircraft tire can display low-temperature color on the thermograph under the same environmental temperature and humidity conditions, and if a penetrating air leakage point exists in the tire, the color is different from other colors which do not generate air leakage; thereby achieving the purpose of detecting the air leakage point of the penetrating damage of the aircraft tire. Before the thermal imaging detector detects, the surface of the aircraft tire is not allowed to be touched by hands or other foreign objects, so that the change of the surface temperature of the tire caused by the foreign objects is avoided, and the detection accuracy is ensured.
The thermal imaging detection method for the through damage of the aircraft tire provided by the application can further comprise the following steps:
the electronic data storage server stores the thermographic image and the decision data in real time.
The thermal imaging detector transmits a thermal image of the tire area to the automatic judging system, and the automatic judging system automatically identifies whether a low-temperature point exists on the thermal image; if yes, the automatic judging system marks the low-temperature point and automatically judges that the tire is a defective product; sending the data and the judgment result to an electronic data storage server for storage; if not, the automatic judging system automatically judges the tire to be qualified, and transmits the data and the judgment result to the electronic data storage server for storage.
The method can also comprise the following steps: the thermal image data, the judgment data, the historical photo data and the like in the electronic data storage server are accessed and retrieved in real time, and backup and storage control of the aircraft tire detection data are facilitated.
Compared with the prior art, the beneficial effect of this application lies in:
1. the method includes the steps that an aviation tire thermal imaging detection system is utilized, temperature change of a penetrating damage air leakage point of an aviation tire is induced based on a thermal imaging technology, and if the penetrating air leakage point exists, the detected aviation tire can display low-temperature color on a thermal image under the conditions of the same environmental temperature and humidity, and the color is different from other colors which do not generate air leakage; the application has the advantages of high detection precision, high efficiency and high safety, and does not have any damage to the tire.
2. The dynamic judgment system provided by the application automatically identifies and marks the thermal image pictures transmitted by the thermal imaging detector and identifies whether abnormal low-temperature points exist on the pictures; if a low temperature point exists, the point can be automatically marked, the tire is automatically judged to be a defective product, and the automation degree of the penetration damage of the aircraft tire is improved.
3. The electronic data storage server stores the thermal image photos and the judgment data in real time, accesses and retrieves the thermal image photos, the judgment data, the historical photo data and the like according to needs, and improves the intelligent level of the penetrating damage of the aircraft tire.
4. The high-pressure nitrogen with stable chemical properties is used as the inflating medium of the aircraft tire, so that the safety is high, and the feasibility is high.
5. The method is beneficial to improving the production efficiency of detecting the penetration damage when the aircraft tire is produced, realizing the intelligent manufacturing of a factory and preventing safety accidents caused by the penetration damage of the aircraft tire.
Drawings
FIG. 1 is an architectural diagram of an overall structure of one embodiment of the present application;
FIG. 2 is a schematic structural diagram of a test station according to an embodiment of the present application;
FIG. 3 is a flow chart of a method for thermal imaging detection of aircraft tire through damage according to an embodiment of the present application;
FIG. 4 is a schematic view of a chuck configuration according to an embodiment of the present application;
FIG. 5 is a schematic thermal image of an embodiment of the present application;
in the figure:
1. the device comprises an air storage tank, 2, a test bench, 21, a test rack, 22, a lifting device, 23, a clamping device, 231, a fixed end, 232, a telescopic end, 24, a chuck, 241, a first clamping part, 242, a second clamping part, 243, a through hole, 25, an air charging device, 26, a motor, 27, a forward and reverse rotating device, 28, an aircraft tire, 3, a thermal imaging detector, 4, an automatic judgment system, 5 and an electronic data storage server.
Detailed Description
The technical solutions in the embodiments of the present application will be described in detail and fully below with reference to the accompanying drawings. It is obvious that the described embodiments are only some specific implementations, not all implementations, of the general technical solutions of the present application. All other embodiments available to those of ordinary skill in the art based on the general concepts of the present application are intended to be within the scope of the present application.
In the description of the present application, it is to be understood that the terms "forward rotation," "reverse rotation," "clockwise," "counterclockwise," and the like refer to an orientation or positional relationship based on that shown in fig. 1, which is only for convenience of description and simplicity of description, and does not indicate or imply that the referenced device or element must have a particular orientation, be constructed in a particular orientation, and be operated, and therefore should not be taken as limiting the present application.
In the description of the present application, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present application can be understood in a specific case by those of ordinary skill in the art.
As shown in fig. 1, the present application provides a thermal imaging detection system for aircraft tire through damage, comprising: the device comprises an air storage tank 1 for filling a pressure medium with a certain temperature into an aircraft tire 28, an air filling device 25 capable of being communicated with the aircraft tire 28, a test bench 2 connected with the aircraft tire 28, a thermal imaging detector 3 arranged at a position with a certain distance from the aircraft tire 28, an automatic judgment system 4 connected with the thermal imaging detector 3 and an electronic data storage server 5;
the gas storage tank 11 is connected with the gas charging device 25 through a gas transmission pipeline, and supplies stable and sufficient pressure medium with a certain temperature for the gas charging device 25 through the gas transmission pipeline;
the inflation device 25 is connected to an aircraft tyre 28 connected in the test station 2, supplying the tyre with a stable, sufficient pressure medium at a certain temperature;
the thermal imaging detector 3 can circumferentially detect the surface of the aircraft tire 28 to obtain a thermal image and send the thermal image to the automatic determination system 4 through a data transmission path;
the thermal imaging detector 3 is a detector which receives an infrared radiation energy distribution pattern of a detected target by using an infrared detector and an optical imaging objective lens, and reflects the infrared radiation energy distribution pattern onto a photosensitive element of the infrared detector so as to obtain an infrared thermal image. Since the thermographic image corresponds one-to-one to the thermal distribution field of the surface of the aircraft tire 28 under inspection, the different colors displayed by the thermographic image represent the different temperatures of the surface of the aircraft tire 28 under inspection;
the automatic judgment system 4 is connected with the electronic data storage server 5 through a data line; the automatic judging system 4 is detection software for analyzing the color change of the picture by identification and contrast, and the automatic judging system 4 can automatically identify and mark the thermal image picture transmitted by the thermal imaging detector 3 and identify whether an abnormal low-temperature point exists on the picture;
the electronic data storage server 5 stores the thermography and the judgment data in real time; the thermal image data, the judgment data, the historical photo data and the like in the electronic data storage server 5 can be accessed and retrieved in real time, and backup and storage control of the aircraft tire detection data are facilitated.
As shown in fig. 2, in an alternative thermal imaging detection system for aircraft tire through damage, the test bench 2 includes a test rack 21, a lifting device 22 capable of transporting an aircraft tire 28, a clamping device 23 fixed on the test rack 21, a chuck 24 for clamping the aircraft tire, a motor 26 fixed on the test rack 21, and a forward and backward rotation device 27 connected with the motor 26;
one end of an inflating device 25 is connected with the clamping device 23, the other end of the inflating device 25 is matched with the chuck 24 and is connected with the aircraft tire 28 through the chuck 24, and stable and sufficient pressure medium with a certain temperature is supplied to the tire;
the positive and negative rotation device 27 is connected with the aircraft tire 28, and the aircraft tire 28 can rotate under the driving of the motor 26, so that the integrity of the circumferential detection of the tire is ensured.
Optionally, in the thermal imaging detection system for the aircraft tire through damage, the lifting device 22 is connected with the test rack 21 through a hinge; the aviation tire 28 of the corresponding specification is lifted through the lifting device 22, and the aviation tire 28 of the corresponding specification is matched and assembled with the chuck 24 of the corresponding specification, so that the installation and the disassembly of the tire are convenient, and the automation degree of the device is improved.
Optionally, in the thermal imaging detection system for aircraft tire through damage, the clamping device 23 is a pneumatic telescopic device, and includes a fixed end 231 connected to the test rack, and a telescopic end 232 connected to the fixed end.
Alternatively, in a thermal imaging detection system for aircraft tire through damage, the chuck 24 comprises a first clamping part 241 and a second clamping part 242, and the first clamping part 241 and the second clamping part 242 can be driven by the clamping device 23 to approach each other so as to clamp the aircraft tire 28 between the first clamping part 241 and the second clamping part; the first 241 and second 242 clamp portions each have a first side for engaging the aircraft tire 28 and a second side for engaging the telescoping end 232 of the clamping device.
Alternatively, in the thermal imaging detection system for the aircraft tire through damage, the telescopic end 232 of the clamping device is provided with a rotating shaft, and the first clamping portion 241 and the second clamping portion 242 are respectively connected with the rotating shaft of the telescopic end 232 of the clamping device, so that the chuck 24 can rotate along with the aircraft tire 28 after clamping the aircraft tire 28.
As shown in fig. 4, in an alternative thermal imaging detection system for aircraft tire through-penetration damage, the chuck 24 has a through hole 243, the inflator 25 is in interference fit with the through hole 243 of the chuck, and the inflator 25 is connected with the aircraft tire through the through hole 243 of the chuck.
Optionally, in the thermal imaging detection system for the penetrating damage of the aircraft tire, the pressure medium in the gas storage tank 1 is high-pressure nitrogen, the chemical property of the nitrogen is stable, and the operation safety is improved.
Alternatively, in the thermal imaging detection system for the penetrating damage of the aircraft tire, the motor 26 is connected with the forward and reverse rotation device 27 through a rotating shaft.
Optionally, in the thermal imaging detection system for aircraft tire penetration damage, the transmission mode between the forward and reverse rotation device 27 and the aircraft tire 28 clamped on the chuck 24 is friction transmission, and the forward rotation or reverse rotation of the forward and reverse rotation device 27 can drive the aircraft tire 28 to rotate.
Optionally, the thermal imaging detector detection location is no more than 1 meter from the aircraft tire 28 being tested; moreover, the surface of the aircraft tire 28 is not allowed to be touched by hands or other foreign objects before the detection is started, so that the influence of the foreign objects on the change of the surface temperature of the tire is avoided, and the detection accuracy is ensured.
As shown in fig. 3, the present application provides a method for thermal imaging detection of aircraft tire through-penetration damage, comprising the steps of:
filling the aircraft tire 28 with a pressure medium at a certain temperature;
after the air pressure in the aircraft tire 28 is stabilized, the thermal imaging detector 3 senses the temperature of the area of the aircraft tire 28 opposite to the thermal imaging detector 3 and generates a thermal image;
driving the aircraft tire 28 to rotate clockwise or counterclockwise;
during rotation of the aircraft tire 28, the thermal imaging detector 3 senses the temperature of the region of the aircraft tire 28 opposite the thermal imaging detector 3 and generates a corresponding thermographic image;
the thermal image is transmitted to the automatic determination system 4, and the automatic determination system 4 determines whether or not the aircraft tire 28 has a leak point and a location of the leak point based on the generated thermal image.
As shown in fig. 1, the forward and reverse rotation device 27 drives the aircraft tire 28 to rotate clockwise or counterclockwise until the thermal imaging detector 3 finishes detecting the entire aircraft tire 28. As shown in fig. 5, since different colors on the thermograph represent the distribution of the surface temperature of the aircraft tire 28, the darker the color represents the lower the temperature, the detected aircraft tire 28 will show a low-temperature color on the thermograph under the same environmental temperature and humidity conditions, and if there is a puncture point on the tire, the color is different from other colors that do not leak; thereby achieving the purpose of detecting the air leakage point of the penetrating damage of the aircraft tire. Before the thermal imaging detector 3 starts to detect, the surface of the aircraft tire 28 is not allowed to be touched by hands or other foreign objects, so that the influence of the foreign objects on the change of the surface temperature of the tire is avoided, and the detection accuracy is ensured.
The thermal imaging detection method for the through damage of the aircraft tire provided by the application can further comprise the following steps:
the electronic-data storage server 5 stores the thermal image photograph and the judgment data in real time.
The thermal imaging detector 3 transmits the thermal image of the aircraft tire 28 area to the automatic judging system 4, and the automatic judging system 4 automatically identifies whether a low-temperature point exists on the thermal image; if yes, the automatic determination system 4 marks the low temperature point and automatically determines that the aircraft tire 28 is a defective product; and sends the data and the judgment result to the electronic data storage server 5 for storage; if not, the automatic determination system 4 automatically determines that the aircraft tire 28 is a non-defective product, and transmits the data and the determination result to the electronic data storage server 5 for storage.
The method can also comprise the following steps: the backup and storage control of the test data of the aircraft tire 28 is facilitated by accessing and retrieving the thermal image data, the judgment data, the history photograph data, and the like in the electronic data storage server 5 in real time.
As shown in fig. 1-4, when inspecting the aircraft tire 28, the aircraft tire 28 to be inspected is raised to a suitable height for mounting with the chuck 24 by the lifting device 22; adjusting the clamping device 23, fixing the tire through the chuck 24, and connecting the inflating device 25 with the aircraft tire 28; opening a switch of the air storage tank 1 filled with high-pressure nitrogen to inflate the aircraft tire 28, and stopping inflating after the aircraft tire 28 is inflated to the standard air pressure; the thermal imaging detector 3 is used for carrying out circumferential scanning on the aircraft tire 28, and meanwhile, the starting motor 26 drives the forward and reverse rotation device 27 to drive the aircraft tire 28 to rotate clockwise or anticlockwise; after the aviation tire 28 is scanned, the scanned picture is uploaded to the automatic judging system 4, the automatic judging system 4 automatically marks the position of the defect and judges the position of the defect according to the color change of the picture, and the system automatically stores the data and the judgment result in the electronic data storage server 5 after the judgment is finished. Different colors on the thermograph represent the distribution of the surface temperature of the aircraft tire, the darker the color represents the lower the temperature, the detected aircraft tire 28 is in the same environmental temperature and humidity condition, if a penetrating air leakage point exists in the aircraft tire 28, the low-temperature color can be displayed on the thermograph and is different from other colors without air leakage; thereby detecting whether the aircraft tire 28 has a penetration damage air leakage point. As shown in fig. 5, in order to detect a thermographic image of a penetrating damage of an aircraft tire by using a thermographic detection system for the penetrating damage of the aircraft tire, as can be seen from fig. 5, a low temperature point appears on the thermographic image, it can be inferred that the aircraft tire has the penetrating damage, and the position of the penetrating damage on the aircraft tire can be found according to the position of the low temperature point on the thermographic image.
While there have been shown and described what are at present considered the fundamental principles and essential features of the application and its advantages, it will be understood by those skilled in the art that the application is not limited by the embodiments described above, which are merely illustrative of the principles of the application, but that various changes and modifications may be made therein without departing from the spirit and scope of the application, which is to be limited only by the claims appended hereto and their equivalents.
Claims (10)
1. The application provides a thermal imaging detecting system of aircraft tire penetrability damage which characterized in that includes: the system comprises an air storage tank, an inflating device which can be communicated with a tire, a test board which is used for connecting the aircraft tire, a thermal imaging detector which is arranged at a position with a certain distance from the aircraft tire, an automatic judgment system which is connected with the thermal imaging detector and an electronic data storage server;
the gas storage tank is connected with the gas charging device through a gas transmission pipeline;
the inflation device is connected with the aircraft tire connected in the test bench;
the automatic judgment system is connected with the electronic data storage server through a data line.
2. The thermal imaging detection system for the through damage of the aircraft tire as claimed in claim 1, wherein said test bed comprises a test frame, a lifting device capable of transporting the aircraft tire, a clamping device fixed on the test frame, a chuck for clamping the aircraft tire, a motor fixed on the test frame and a forward and backward rotation device connected with the motor;
one end of the inflating device is connected with the clamping device, and the other end of the inflating device is matched with the chuck and is connected with the aircraft tire through the chuck.
3. The system of claim 2, wherein the clamping device is a pneumatic telescoping device comprising a fixed end connected to the test frame and a telescoping end connected to the fixed end.
4. A thermal imaging detection system for aircraft tire through-penetration damage according to claim 3, wherein said chuck comprises a first clamping portion and a second clamping portion; the first clamping part and the second clamping part are provided with a first side attached to the aircraft tire and a second side connected with the telescopic end of the clamping device.
5. A thermal imaging detection system for aircraft tire through-penetration damage according to claim 4, wherein said telescoping end of said clamping device has a pivot, and said first clamping portion and said second clamping portion are respectively connected to said pivot of said telescoping end of said clamping device.
6. The system according to claim 1, wherein the pressure medium in the air tank is high-pressure nitrogen.
7. The system according to claim 2, wherein the motor is connected to the counter-rotating device via a rotating shaft.
8. The application provides a thermal imaging detection method for penetrating damage of an aircraft tire, which comprises the following steps:
filling a pressure medium with a certain temperature into the aviation tire;
after the air pressure in the aircraft tire is stable, the thermal imaging detector senses the temperature of an area, opposite to the thermal imaging detector, on the aircraft tire and generates a thermal image;
driving the aircraft tire to rotate clockwise or anticlockwise;
during the rotation of the aircraft tire, the thermal imaging detector senses the temperature of an area, opposite to the thermal imaging detector, of the aircraft tire and generates a corresponding thermal image;
and the thermal image is transmitted to an automatic judgment system, and the automatic judgment system judges whether the aircraft tire has an air leakage point and the position of the air leakage point according to the generated thermal image.
9. A thermal imaging detection system for aircraft tire through-penetration damage according to claim 8, further comprising the steps of:
the electronic data storage server stores the thermographic image and the decision data in real time.
10. A thermal imaging detection system for aircraft tire through-penetration damage according to claim 9, further comprising the steps of: the thermal image data, the judgment data, the historical photo data and the like in the electronic data storage server are accessed and retrieved in real time, and backup and storage control of the aircraft tire detection data are facilitated.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202011504004.5A CN112461895A (en) | 2020-12-18 | 2020-12-18 | Thermal imaging detection system and method for aircraft tire through damage |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202011504004.5A CN112461895A (en) | 2020-12-18 | 2020-12-18 | Thermal imaging detection system and method for aircraft tire through damage |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20230008450A1 (en) * | 2021-07-07 | 2023-01-12 | Paul E. Hawkinson Company | Tire Defect Detection System |
| CN116735663A (en) * | 2023-08-15 | 2023-09-12 | 菏泽天盈新能源有限公司 | Performance testing device for new energy automobile tire |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS57142341A (en) * | 1981-02-26 | 1982-09-03 | Kobe Steel Ltd | Method and apparatus for detecting pressure leakage in centering mechanism for tire vulcanizing machine |
| CN201229279Y (en) * | 2008-06-27 | 2009-04-29 | 青岛高校软控股份有限公司 | Tire pressure detection machine |
| CN202471354U (en) * | 2012-01-19 | 2012-10-03 | 武汉理工新能源有限公司 | Membrane electrode leak detection device utilizing infrared thermal imaging technology |
| CN106248402A (en) * | 2016-09-29 | 2016-12-21 | 上海热像机电科技股份有限公司 | A kind of tire detecting system based on infrared thermal imaging technique and method |
| CN109489904A (en) * | 2018-11-14 | 2019-03-19 | 中国航发动力股份有限公司 | A kind of detection system and method for the gas leakage of engine crankcase faying face |
| CN111070979A (en) * | 2019-12-31 | 2020-04-28 | 西安森兰科贸有限责任公司 | Non-contact infrared pressure gauge |
-
2020
- 2020-12-18 CN CN202011504004.5A patent/CN112461895A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS57142341A (en) * | 1981-02-26 | 1982-09-03 | Kobe Steel Ltd | Method and apparatus for detecting pressure leakage in centering mechanism for tire vulcanizing machine |
| CN201229279Y (en) * | 2008-06-27 | 2009-04-29 | 青岛高校软控股份有限公司 | Tire pressure detection machine |
| CN202471354U (en) * | 2012-01-19 | 2012-10-03 | 武汉理工新能源有限公司 | Membrane electrode leak detection device utilizing infrared thermal imaging technology |
| CN106248402A (en) * | 2016-09-29 | 2016-12-21 | 上海热像机电科技股份有限公司 | A kind of tire detecting system based on infrared thermal imaging technique and method |
| CN109489904A (en) * | 2018-11-14 | 2019-03-19 | 中国航发动力股份有限公司 | A kind of detection system and method for the gas leakage of engine crankcase faying face |
| CN111070979A (en) * | 2019-12-31 | 2020-04-28 | 西安森兰科贸有限责任公司 | Non-contact infrared pressure gauge |
Non-Patent Citations (1)
| Title |
|---|
| 刘承启: "《机械工人计算手册（第一分册）》", 30 April 1984, pages: 511 - 512 * |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20230008450A1 (en) * | 2021-07-07 | 2023-01-12 | Paul E. Hawkinson Company | Tire Defect Detection System |
| US11733126B2 (en) * | 2021-07-07 | 2023-08-22 | Paul E. Hawkinson Company | Tire defect detection system that images localized cooling at a defect |
| CN116735663A (en) * | 2023-08-15 | 2023-09-12 | 菏泽天盈新能源有限公司 | Performance testing device for new energy automobile tire |
| CN116735663B (en) * | 2023-08-15 | 2023-11-07 | 菏泽天盈新能源有限公司 | Performance testing device for new energy automobile tire |
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