CN111562052A - Method for detecting static balance difference of aircraft tire - Google Patents
Method for detecting static balance difference of aircraft tire Download PDFInfo
- Publication number
- CN111562052A CN111562052A CN202010456461.5A CN202010456461A CN111562052A CN 111562052 A CN111562052 A CN 111562052A CN 202010456461 A CN202010456461 A CN 202010456461A CN 111562052 A CN111562052 A CN 111562052A
- Authority
- CN
- China
- Prior art keywords
- static balance
- aircraft tire
- balance difference
- tire
- difference
- 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.)
- Withdrawn
Links
- 230000003068 static effect Effects 0.000 title claims abstract description 158
- 238000000034 method Methods 0.000 title claims abstract description 36
- 238000012360 testing method Methods 0.000 claims abstract description 44
- 238000001514 detection method Methods 0.000 claims abstract description 23
- 238000012797 qualification Methods 0.000 claims abstract description 7
- 239000007788 liquid Substances 0.000 claims description 14
- XLOMVQKBTHCTTD-UHFFFAOYSA-N Zinc monoxide Chemical compound [Zn]=O XLOMVQKBTHCTTD-UHFFFAOYSA-N 0.000 claims description 8
- 230000001680 brushing effect Effects 0.000 claims description 8
- 238000012937 correction Methods 0.000 claims description 8
- 230000008439 repair process Effects 0.000 claims description 8
- 239000011248 coating agent Substances 0.000 claims description 6
- 238000000576 coating method Methods 0.000 claims description 6
- 238000012986 modification Methods 0.000 claims description 6
- 230000004048 modification Effects 0.000 claims description 6
- 239000013589 supplement Substances 0.000 claims description 6
- 238000010998 test method Methods 0.000 claims description 5
- 238000009434 installation Methods 0.000 claims description 4
- 238000009966 trimming Methods 0.000 claims description 4
- 239000011787 zinc oxide Substances 0.000 claims description 4
- 238000001035 drying Methods 0.000 claims description 3
- 239000000463 material Substances 0.000 claims description 3
- 238000007781 pre-processing Methods 0.000 claims description 3
- 238000013102 re-test Methods 0.000 claims description 3
- 239000011347 resin Substances 0.000 claims description 3
- 229920005989 resin Polymers 0.000 claims description 3
- 238000010079 rubber tapping Methods 0.000 claims description 3
- 238000012795 verification Methods 0.000 claims description 3
- 238000007689 inspection Methods 0.000 claims 1
- 238000005259 measurement Methods 0.000 abstract description 19
- 238000000691 measurement method Methods 0.000 abstract 1
- 238000004364 calculation method Methods 0.000 description 4
- 230000000052 comparative effect Effects 0.000 description 4
- 230000007547 defect Effects 0.000 description 3
- 238000010586 diagram Methods 0.000 description 3
- 230000001050 lubricating effect Effects 0.000 description 2
- 230000007246 mechanism Effects 0.000 description 2
- 238000010422 painting Methods 0.000 description 2
- 239000011324 bead Substances 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 150000001875 compounds Chemical class 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 238000009472 formulation Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 230000008092 positive effect Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
Images
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M1/00—Testing static or dynamic balance of machines or structures
- G01M1/12—Static balancing; Determining position of centre of gravity
- G01M1/122—Determining position of centre of gravity
- G01M1/125—Determining position of centre of gravity of aircraft
- G01M1/127—Determining position of centre of gravity of aircraft during the flight
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Testing Of Balance (AREA)
Abstract
The invention provides a method for detecting static balance difference of an aircraft tire, belongs to the field of static balance measurement of tires, and can solve the technical problems of low detection efficiency, poor detection precision and the like of the conventional static balance difference measurement method. The detection method comprises the following steps: (1) testing the static balance difference and angle of the aircraft tire, and marking at the position which is symmetrical to the angle by 180 degrees; (2) calculating the allowable static balance difference degree of the aircraft tire; (3) comparing the static balance difference of the aircraft tire with an allowable static balance difference, and judging whether repairing is needed; (4) and (3) after repairing the marking position of the aircraft tire by using an aircraft tire repairing method, verifying the qualification rate of the static balance difference. The detection method is simple and easy to operate and has high measurement precision. The method has very wide application prospect in the field of static balance measurement of the aircraft tire.
Description
Technical Field
The invention belongs to the field of static balance measurement of tires, and particularly relates to a method for detecting static balance difference of an aircraft tire.
Background
In the process of high-speed takeoff and landing of the airplane, the highest speed can reach 400km/h, and the rotating speed of the aircraft tire can reach more than 30-40 r/s, so that the requirement on the static balance of the aircraft tire is very strict. According to the relevant regulations in GB/T-13655 2004 'aviation tyre static balance difference experimental method', the aviation tyre static balance difference must be strictly controlled within the standard range, otherwise, the aviation tyre static balance difference cannot be installed for use.
At present, a plurality of domestic aviation companies adopt a simple static balancing machine to detect the static balance difference of an aviation tire, but the method has the defects of low measurement efficiency, poor measurement precision and the like, and equipment for detecting the static balance of the aviation tire abroad is very expensive, the price of a single device is as high as 700 ten thousand yuan, and general enterprises are difficult to bear. Therefore, in order to solve the dilemma of the prior art, how to develop a detection method for static balance difference of an aircraft tire, which has high measurement accuracy and accurate and reliable data, is a problem to be solved urgently in the field.
Disclosure of Invention
The invention aims at the problem that the static balance difference detection method of the aircraft tire in the prior art is low in measurement efficiency. The technical problems of poor measurement precision and the like are solved, and the method for detecting the static balance difference of the aircraft tire is simple and convenient to operate, high in measurement precision, accurate and reliable in data.
In order to achieve the purpose, the invention adopts the technical scheme that:
a method for detecting the static balance difference of an aircraft tire comprises the following steps:
after testing the static balance difference and the angle of the aircraft tire, marking at the position which is symmetrical to the angle by 180 degrees;
calculating the allowable static balance difference degree of the aircraft tire;
comparing the static balance difference of the aircraft tire with an allowable static balance difference, and judging whether repairing is needed;
and (3) after repairing the marking position of the aircraft tire by using an aircraft tire repairing method, verifying the qualification rate of the static balance difference.
Preferably, the static balance difference and angle of the aircraft tire are tested by a dynamic balance testing machine.
Preferably, the allowable static balance difference of the aircraft tire is obtained by the following method comprising the following specific steps of:
calculating a static balance difference standard value of the aircraft tire by using a static balance standard formula (I);
and (5) substituting the standard value of the static balance difference into a repairing formula (II) to obtain the allowable static balance difference of the aircraft tire.
Preferably, the static balance amount standard formula (I) is specifically:
M≤0.00383D2；
in the formula: m is a static balance difference standard value (N cm), and D is the maximum inflation outer diameter (cm) of the aircraft tire.
Preferably, the repair formula (II) is specifically:
Msupplement device＝(1000*MQuiet)/(9.8*Dn/2)；
In the formula: mSupplement deviceTo allow for static balance differences (g), MQuietThe static balance difference (N cm) is shown, and Dn is the inside diameter (cm) of the top of the aircraft tire.
Preferably, the aircraft tire repairing method specifically comprises the following steps:
coating the modification liquid on the tire top inner side position corresponding to the marking angle position of the aircraft tire in multiple times, standing for 6-8h, and naturally drying;
wherein the single brushing area is less than or equal to 400cm2The amount of the finishing liquid is 35-45g during single brushing.
Preferably, the modification liquid comprises the following components in parts by weight: 15-20 parts of rubber material, 5-6 parts of octyl phenolic tackifying resin, 45-50 parts of indirect-method zinc oxide and 140 parts of gasoline.
Preferably, the static balance difference verification specifically comprises the following steps:
and (3) mounting the repaired aircraft tire on a dynamic balance testing machine to retest the static balance difference, and verifying the static balance difference qualification rate by using the static balance standard formula (I) and the repairing formula (II).
Preferably, a dynamic balance testing machine rim testing step and an aviation tire preprocessing step are further included before testing the static balance difference and angle of the aviation tire.
Preferably, the dynamic balancing machine rim testing step comprises: accurate installation of machine, volume calibration, eccentric correction and zero correction, aviation tire preliminary treatment step includes: rubber tapping and trimming rubber edges.
Compared with the prior art, the invention has the advantages and positive effects that:
1. the invention provides a method for detecting static balance difference of an aircraft tire, which utilizes the existing dynamic balance testing machine, obtains the static balance difference of the aircraft tire by measuring eccentric moment detection data caused by offset and rotation of the mass center of the aircraft tire through strict and careful calculation, fully utilizes the detection principle of a dynamic balancing machine, and solves the problems of low efficiency and low measurement precision of the simple static balancing machine in the prior art for measuring the static balance difference.
2. The invention provides a method for detecting the static balance difference of an aircraft tire, which further compares the static balance difference of the aircraft tire with an allowable static balance difference to judge whether the aircraft tire needs to be repaired or not, and then repairs the aircraft tire by using a tire repairing method to ensure that the aircraft tire reaches the standard.
Drawings
FIG. 1 is a flow chart of a method for detecting the static balance difference of an aircraft tire according to an embodiment of the invention;
FIG. 2 is a schematic diagram of a dynamic balance testing machine control system provided in an embodiment of the present invention;
FIG. 3 is a schematic diagram illustrating a static balance difference conversion for an aircraft tire test according to an embodiment of the present invention;
fig. 4 is a schematic diagram of a simple static balancing machine test provided in the embodiment of the present invention.
In the above figures, 1, the light point position; 2. the location of the emphasis; 3. aircraft tires; 4. a force measuring mechanism; 5. and (4) a clamp.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The embodiment of the invention provides a method for detecting static balance difference of an aircraft tire, which comprises the following steps:
s1, marking at a position which is symmetrical to the angle by 180 degrees after testing the static balance difference and the angle of the aircraft tire;
in the step, after testing the static balance difference and the angle of the aircraft tire, marking the angle as the tire key point position, and marking the position with 180 degrees of angle symmetry, wherein the marking position is marked as the tire light point position.
S2, calculating the allowable static balance difference of the aircraft tire;
s3, comparing the static balance difference of the aircraft tire with an allowable static balance difference, and judging whether repairing is needed;
and S4, after the marking position of the aircraft tire is repaired by using the aircraft tire repairing method, the qualification rate of the static balance difference is verified.
In a preferred embodiment, the static balance difference and angle of the aircraft tire are tested by using a dynamic balance testing machine.
The embodiment provides a method for detecting the static balance difference of an aircraft tire by using a dynamic balancing machine of a truck tire, the method selects the detection data of the eccentric moment caused by measuring the offset and rotation of the mass center of the aircraft tire of the conventional dynamic balancing machine of the truck radial tire, obtains the static balance difference of the aircraft tire through strict and careful calculation, fully utilizes the detection principle of a dynamic balancing machine, and solves the problems of low efficiency and low measurement precision of the simple static balancing machine in the prior art in measuring the static balance difference.
Based on the existing testing method of the tire dynamic balance testing machine, the unqualified tire is further repaired and verified by combining a static balance standard formula and a repairing formula, and finally the static balance difference of the aircraft tire is ensured to meet the relevant standard.
In a preferred embodiment, the allowable static balance difference of the aircraft tire is obtained by the following steps:
calculating a static balance difference standard value of the aircraft tire by using a static balance standard formula (I);
and (5) substituting the standard value of the static balance difference into a repairing formula (II) to obtain the allowable static balance difference of the aircraft tire.
In a preferred embodiment, the static balance amount standard formula (I) is specifically:
M≤0.00383D2；
in the formula: m is a static balance difference standard value (N cm), and D is the maximum inflation outer diameter (cm) of the aircraft tire.
In the preferred embodiment, the static balance amount standard formula (I) is obtained by using relevant standards in GB/T-13655 2004 static balance difference test method for aircraft tires.
In a preferred embodiment, the repairing formula (II) is specifically:
Msupplement device＝(1000*MQuiet)/(9.8*Dn/2)；
In the formula: mSupplement deviceTo allow for static balance differences (g), MQuietThe static balance difference (N cm) is shown, and Dn is the inside diameter (cm) of the top of the aircraft tire.
In the preferred embodiment, the static balance difference standard value (corresponding to a standard value) is calculated by using the static balance amount standard formula (I), and then the static balance difference standard value is substituted into the repairing formula (II) to calculate the allowable static balance difference of the aircraft tire. If the actual static balance difference measured by the dynamic balance testing machine is larger than the standard value, the aviation tire is not in accordance with the standard and needs to be repaired, otherwise, the aviation tire is in accordance with the standard.
In a preferred embodiment, the aircraft tire repair method is specifically as follows:
coating the modification liquid on the tire top inner side position corresponding to the marking angle position of the aircraft tire in multiple times, standing for 6-8h, and naturally drying;
wherein the single brushing area is less than or equal to 400cm2The amount of the finishing liquid is 35-45g during single brushing.
In the preferred embodiment, when the aircraft tire is coated with the finishing liquid in multiple times, only the single coating area and the single coating amount of the finishing liquid are limited, and the coating in multiple times is not performedThe specific number of times is limited because: when the aircraft tires of different models and specifications are repaired, the painting times cannot be clearly limited due to different amounts of the required finishing liquid, but only the single painting area is ensured to be controlled to be less than or equal to 400cm2The amount of the finishing liquid used in one brushing is 35-45g, wherein the amount of the finishing liquid used in one brushing can be 35, 40, 45g or any value within the above-mentioned limit range, and the amount falls within the protection scope of the invention.
In a preferred embodiment, the modification liquid comprises the following components in parts by weight: 15-20 parts of rubber material, 5-6 parts of octyl phenolic tackifying resin, 45-50 parts of indirect-method zinc oxide and 140 parts of gasoline.
In the above preferred embodiment, there is specifically provided a formulation for an aircraft tire modifying fluid, wherein the rubber compound is selected from 15, 16, 17, 18, 19, 20 parts or any value within the above-defined range falls within the scope of the present invention, the indirect zinc oxide is selected from 45, 46, 47, 48, 49, 50 parts or any value within the above-defined range falls within the scope of the present invention, and the gasoline is selected from 120, 130, 140 parts or any value within the above-defined range falls within the scope of the present invention.
In a preferred embodiment, the static balance difference verification specifically comprises:
and (3) mounting the repaired aircraft tire on a dynamic balance testing machine to retest the static balance difference, and verifying the static balance difference qualification rate by using the static balance standard formula (I) and the repairing formula (II).
In the above preferred embodiment, after the aircraft tire is repaired, the static balance difference of the aircraft tire needs to be verified, that is, the repaired aircraft tire is placed in a dynamic balance testing machine again to measure the actual static balance difference, and compared with the allowable static balance difference of the aircraft tire in the technical solution shown in the above preferred embodiment, if the actual static balance difference is less than the allowable static balance difference, it indicates that the tire is qualified for detection and repair, otherwise, it is not qualified.
In a preferred embodiment, a dynamic balancing machine rim testing step and an aircraft tire preprocessing step are further included before testing the static balance difference and angle of the aircraft tire.
In a preferred embodiment, the dynamic balancing machine rim testing step includes: accurate installation of machine, volume calibration, eccentric correction and zero correction, aviation tire preliminary treatment step includes: rubber tapping and trimming rubber edges.
In the preferred embodiment, before the static balance difference of the aircraft tire is measured, the rim test of the dynamic balance testing machine and the pretreatment of the aircraft tire are required, and the purposes are to improve the measurement precision and ensure the accuracy and reliability of data.
In order to more clearly describe the method for detecting the static balance difference of the aircraft tire provided by the embodiment of the invention in detail, the following description is given with reference to specific embodiments.
Example 1
The embodiment provides a method for detecting static balance difference of an aircraft tire, which selects 49 × 19R20 aircraft tires for static balance difference detection, and specifically comprises the following steps:
the detection target: 49 × 19R20 aircraft tire, with a maximum inflated outer diameter of 121.0cm and a summit inner diameter of 114.0 cm;
the detection method specifically comprises:
(1) pretreating an aircraft tire: performing foot cutting and tire rubber edge trimming work on 49 × 19R20 aircraft tire;
(2) testing a dynamic balance testing machine rim: the method comprises accurate installation of a machine, quantity calibration, eccentricity correction and zero correction;
(3) conveying the trimmed aircraft tire (49 × 19R20) to an input station of a dynamic balance testing machine, lubricating the tire bead part through a lubricating station, measuring and recording the static unbalance difference value and angle of the aircraft tire, marking at a symmetrical angle position, wherein the static unbalance amount is 105.72N · cm, and the corresponding angle is 183 degrees;
(4) substituting the maximum inflated outer diameter of the aircraft tire into a static balance standard formula (I), calculating a static balance difference standard value of the aircraft tire to obtain a 49 × 19R20 static balance difference standard value M of the aircraft tire to 56N cm, substituting the static balance difference standard value M to 56N cm into a repairing formula (II), and calculating to obtain the allowable static balance difference of the aircraft tire to be 100.25 g;
(5) substituting the static unbalance amount (105.72N cm) measured in the step (3) into a repairing formula (II) to obtain a repairing mass 189g, and comparing the repairing mass with the allowable static balance difference (100.25g) measured in the step (4), so that the actually measured static unbalance amount is larger than the allowable static balance difference, and the aviation tire is judged to be required to be repaired;
(6) the repairing amount 189g of the angle symmetric marking position to be repaired is calculated according to a repairing formula (II);
(7) the mass data of the static unbalance measured by the dynamic balancing machine is 67g, and the requirement of < the static balance differential standard value (100.25g) is met, so that the aviation tire is qualified in testing and repairing.
Comparative example 1
The comparative example provides a method for testing static balance difference of an aircraft tire by using a simple static balancing machine, which comprises the following specific contents:
test methods: the static balancing machine is horizontally installed, the tire is vertically measured, and the size of the wheel hub is matched with the static balancing tire to be measured. The static position can mark the light point position after the static balancing machine is assembled with the tire, the static unbalance force value read from the force measuring mechanism represents the static balance difference of the tire, the testing principle is shown in fig. 4, wherein fig. 4-A shows that the middle line fixed point position is the light point position 1 after the tire is completely stopped; the light point position is rotated by 190 degrees counterclockwise, and after the tire is completely stationary, the pointer points to the heavy point position 2 for measurement.
Static balance difference calculation method:
(1) static balancing machine and central strutting arrangement, the testing machine precision: not more than 10 g;
(2) calculating the static balance difference of the test tire according to the following formula:
M＝W×Dn/2(Ⅲ)；
wherein M is a static balance difference (N cm) of the test tire, W is a static unbalance force (N) of the test tire, and Dn/2 is a maximum inner radius (cm) of the test tire.
The disadvantages are that: the simple static balancing machine selected by the comparison example has the defects of relatively simple structural principle and tool equipment, low measurement efficiency, low measurement precision and the like. In addition, the main aviation tire manufacturers in China also use a static balancing machine produced by American Missigen Annberg to carry out static balance difference detection, but the company stops production at present.
Comparing the above examples with comparative examples, it can be seen that:
firstly, the comparative example 1 provides a method for measuring the static balance difference of an aircraft tire by using the existing simple static balancing machine, and the device has the defects of low measurement efficiency, low measurement precision and the like due to relatively simple structural principle and tool equipment, and is difficult to be widely applied to the field of static balance measurement of aircraft tires; secondly, the static balancing machine produced abroad at present is expensive, the price of a single machine is as high as about 700 ten thousand yuan, and common enterprises are difficult to bear.
Therefore, in order to solve the dilemma of the prior art, the invention provides a method for detecting the static balance difference of an aircraft tire, which selects the existing dynamic balance testing machine of the radial tire of the loading radial tire to detect data by measuring the eccentric moment caused by the offset and rotation of the mass center of the aircraft tire, obtains the static balance difference of the aircraft tire through strict and careful calculation, fully utilizes the detection principle of a dynamic balancing machine, further repairs and rechecks the determined unqualified tire by combining a static balance standard formula and a repair formula based on the existing testing method of the dynamic balance testing machine of the tire, and finally ensures that the static balance difference of the aircraft tire meets the relevant standards. The method not only ensures the detection precision and efficiency of the static balance difference of the aircraft tire, but also greatly reduces the cost of purchasing machines by enterprises, and has very wide application prospect in the field of static balance difference detection.
Claims (10)
1. A method for detecting the static balance difference of an aircraft tire is characterized by comprising the following steps:
after testing the static balance difference and the angle of the aircraft tire, marking at the position which is symmetrical to the angle by 180 degrees;
calculating the allowable static balance difference degree of the aircraft tire;
comparing the static balance difference of the aircraft tire with an allowable static balance difference, and judging whether repairing is needed;
and (3) after repairing the marking position of the aircraft tire by using an aircraft tire repairing method, verifying the qualification rate of the static balance difference.
2. The test method according to claim 1, wherein the aircraft tire static balance difference and angle are tested by a dynamic balance tester.
3. The detection method according to claim 1, wherein the allowable static balance difference of the aircraft tire is obtained by the following steps:
calculating a static balance difference standard value of the aircraft tire by using a static balance standard formula (I);
and (5) substituting the standard value of the static balance difference into a repairing formula (II) to obtain the allowable static balance difference of the aircraft tire.
4. The detection method according to claim 3, wherein the static balance criterion formula (I) is specifically:
M≤0.00383D2；
in the formula: m is a static balance difference standard value (N cm), and D is the maximum inflation outer diameter (cm) of the aircraft tire.
5. The detection method according to claim 3, wherein the repair formula (II) is specifically:
Msupplement device＝(1000*MQuiet)/(9.8*Dn/2)；
In the formula: mSupplement deviceTo allow for static balance differences (g), MQuietThe static balance difference (N cm) is shown, and Dn is the inside diameter (cm) of the top of the aircraft tire.
6. The inspection method according to claim 1, wherein the aircraft tire repair method is specifically:
coating the modification liquid on the tire top inner side position corresponding to the marking angle position of the aircraft tire in multiple times, standing for 6-8h, and naturally drying;
wherein the single brushing area is less than or equal to 400cm2The amount of the finishing liquid is 35-45g during single brushing.
7. The detection method according to claim 6, wherein the modification liquid comprises the following components in parts by weight: 15-20 parts of rubber material, 5-6 parts of octyl phenolic tackifying resin, 45-50 parts of indirect-method zinc oxide and 140 parts of gasoline.
8. The detection method according to claim 1 or 2, characterized in that the static balance difference verification specifically comprises:
and (3) mounting the repaired aircraft tire on a dynamic balance testing machine to retest the static balance difference, and verifying the static balance difference qualification rate by using the static balance standard formula (I) and the repairing formula (II).
9. The test method according to claim 1, further comprising a dynamic balancing machine rim test step and an aircraft tire preprocessing step before testing the aircraft tire static balance difference and angle.
10. The method of testing of claim 9, wherein the dynamic balancing machine rim testing step comprises: accurate installation of machine, volume calibration, eccentric correction and zero correction, aviation tire preliminary treatment step includes: rubber tapping and trimming rubber edges.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010456461.5A CN111562052A (en) | 2020-05-26 | 2020-05-26 | Method for detecting static balance difference of aircraft tire |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010456461.5A CN111562052A (en) | 2020-05-26 | 2020-05-26 | Method for detecting static balance difference of aircraft tire |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111562052A true CN111562052A (en) | 2020-08-21 |
Family
ID=72074892
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010456461.5A Withdrawn CN111562052A (en) | 2020-05-26 | 2020-05-26 | Method for detecting static balance difference of aircraft tire |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111562052A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117261300A (en) * | 2023-08-07 | 2023-12-22 | 青岛森麒麟轮胎股份有限公司 | A tire rolling correction mechanism |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1394173A (en) * | 2000-10-31 | 2003-01-29 | 本田技研工业株式会社 | Assembling method for tire wheel assembly and assembling line for tire wheel assembly and wheel and production method for wheel |
| CN101368866A (en) * | 2007-07-27 | 2009-02-18 | 施耐宝仪器股份有限公司 | How to balance a wheel |
| CN101788368A (en) * | 2009-01-27 | 2010-07-28 | 施耐宝仪器股份有限公司 | Method and wheel balancer for balancing a wheel |
| US20110197672A1 (en) * | 2010-02-16 | 2011-08-18 | Schenck Rotec Gmbh | Method and device for unbalance correction on a vehicle wheel |
| CN103289596A (en) * | 2013-06-20 | 2013-09-11 | 中橡集团曙光橡胶工业研究设计院 | Rubber cement for static balance patching of aircraft tire |
| CN103465483A (en) * | 2013-09-25 | 2013-12-25 | 无锡翼龙航空设备有限公司 | Process for repairing radial tyre of high-speed coach |
| CN104748912A (en) * | 2015-02-04 | 2015-07-01 | 青岛森麒麟轮胎有限公司 | Static balance correction method for aircraft tire |
| CN107121236A (en) * | 2017-04-27 | 2017-09-01 | 特拓(青岛)轮胎技术有限公司 | Tire static unbalance ameliorative way based on Vector operation |
| CN110576709A (en) * | 2018-06-08 | 2019-12-17 | 住友橡胶工业株式会社 | Tire unbalance correction method and tire |
| US20200041373A1 (en) * | 2016-02-09 | 2020-02-06 | Carlo Buzzi | Method and machine for balancing a vehicle wheel |
-
2020
- 2020-05-26 CN CN202010456461.5A patent/CN111562052A/en not_active Withdrawn
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1394173A (en) * | 2000-10-31 | 2003-01-29 | 本田技研工业株式会社 | Assembling method for tire wheel assembly and assembling line for tire wheel assembly and wheel and production method for wheel |
| CN101368866A (en) * | 2007-07-27 | 2009-02-18 | 施耐宝仪器股份有限公司 | How to balance a wheel |
| CN101788368A (en) * | 2009-01-27 | 2010-07-28 | 施耐宝仪器股份有限公司 | Method and wheel balancer for balancing a wheel |
| US20110197672A1 (en) * | 2010-02-16 | 2011-08-18 | Schenck Rotec Gmbh | Method and device for unbalance correction on a vehicle wheel |
| CN103289596A (en) * | 2013-06-20 | 2013-09-11 | 中橡集团曙光橡胶工业研究设计院 | Rubber cement for static balance patching of aircraft tire |
| CN103465483A (en) * | 2013-09-25 | 2013-12-25 | 无锡翼龙航空设备有限公司 | Process for repairing radial tyre of high-speed coach |
| CN104748912A (en) * | 2015-02-04 | 2015-07-01 | 青岛森麒麟轮胎有限公司 | Static balance correction method for aircraft tire |
| US20200041373A1 (en) * | 2016-02-09 | 2020-02-06 | Carlo Buzzi | Method and machine for balancing a vehicle wheel |
| CN107121236A (en) * | 2017-04-27 | 2017-09-01 | 特拓(青岛)轮胎技术有限公司 | Tire static unbalance ameliorative way based on Vector operation |
| CN110576709A (en) * | 2018-06-08 | 2019-12-17 | 住友橡胶工业株式会社 | Tire unbalance correction method and tire |
Non-Patent Citations (1)
| Title |
|---|
| 盛保信: "航空轮胎成品检测的最新方法", 《特种橡胶制品》 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117261300A (en) * | 2023-08-07 | 2023-12-22 | 青岛森麒麟轮胎股份有限公司 | A tire rolling correction mechanism |
| CN117261300B (en) * | 2023-08-07 | 2026-01-02 | 青岛森麒麟轮胎股份有限公司 | A tire rolling correction mechanism |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102853730B (en) | Automobile engine hood hinge inspection tool | |
| CN112345273B (en) | Tire high-speed uniformity equipment controlled tire monitoring method | |
| CN102183346B (en) | Method for detecting leakage flow of automobile oil tank cover | |
| US8186215B2 (en) | Method and system for determining non-uniformity characteristics of a vehicle tire and rim | |
| CN100562734C (en) | Measurement method of tire out-of-roundness | |
| CN111562052A (en) | Method for detecting static balance difference of aircraft tire | |
| EP1624294B1 (en) | Tire uniformity testing | |
| CN100582710C (en) | Method for calibrating and measuring unbalance amount of tire | |
| CN111998792B (en) | On-line detection method and on-line detection device for tire blank out-of-roundness of tire building machine | |
| CN118268930A (en) | Self-checking method for contact type measuring head application | |
| CN115014188A (en) | Method and device for judging qualified bottle wall thickness | |
| CN209727063U (en) | A kind of Vehicular hub bounce testing machine verifying simulation wheel hub | |
| CN2516334Y (en) | Thickness measuring device for type curing bag | |
| CN113029602B (en) | Precision verification method of high-precision rim for tire high-speed uniformity equipment | |
| CN114341612A (en) | Method for testing a tyre | |
| CN108519501A (en) | Coasting time detector and non-contact speed gage calibrating installation and calibration method | |
| CN111595223A (en) | Wheel hub unit sealing washer detector of beating | |
| CN213121136U (en) | Bicycle and electric vehicle inflation-free tire knocking-over test device | |
| CN109764840B (en) | Simulation hub for verifying motor vehicle hub runout testing machine and verification method | |
| CN216348317U (en) | Fast check tool for crankshaft flywheel positioning pin hole angle | |
| US3760633A (en) | Method and apparatus for balancing pneumatic tire and support | |
| CN113028938B (en) | Integrated flexible flywheel detection device | |
| CN215573434U (en) | Device for monitoring temperature of solid tire in use on line | |
| KR102054766B1 (en) | Accurate meter for flush head on aircraft and Evaluation Method for flush head using that | |
| CN208537581U (en) | Calibration device for taxi time detector and non-contact speedometer |
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 | ||
| WW01 | Invention patent application withdrawn after publication |
Application publication date: 20200821 |
|
| WW01 | Invention patent application withdrawn after publication |