CN102069917B - Method for detecting and assembling aircraft carbon brake discs - Google Patents
Method for detecting and assembling aircraft carbon brake discs Download PDFInfo
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- CN102069917B CN102069917B CN2010105576620A CN201010557662A CN102069917B CN 102069917 B CN102069917 B CN 102069917B CN 2010105576620 A CN2010105576620 A CN 2010105576620A CN 201010557662 A CN201010557662 A CN 201010557662A CN 102069917 B CN102069917 B CN 102069917B
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Abstract
The invention discloses a method for detecting and assembling aircraft carbon brake discs, which provides a detection method for circular distribution and two-side measurement according to the manufacturing characteristics of the aircraft carbon brake discs and the using characteristics of a Shore hardness tester and can better characterize the Shore hardness of each aircraft carbon brake disc. During assembling, the Shore hardness differences of two adjacent aircraft carbon brake discs and the whole set of aircraft carbon brake discs are controlled to effectively reduce the gully phenomenon of frication surfaces, prolong the service life of the aircraft carbon brake discs and avoid the abnormal vibration generated by the aircraft carbon brake discs.
Description
Technical field
The invention belongs to the detection technique field of airplane carbon brake disc, be specifically related to a kind of test set method of completing the square of airplane carbon brake disc.
Background technology
The C/C composite material has excellent high temperature friction performance, and lightweight, intensity is high, is the preferred material of airplane brake system.Since 1973 after the VC-10 aircraft is installed the charcoal brake gear and is taken a flight test, the C/C composite material more and more is widely used on the brake system of modern military and civil aircraft, becomes the field of C/C composite material use amount maximum.
Compare with the metal brake dish, carbon/carbon brake disc also because the C/C composite material is soft material, has the advantage that frictional vibration is little, noise is little except lightweight, distinguishing features such as frictional behavior good, high temperature resistant, long service life.Yet find that in use carbon/carbon brake disc is after use after a while, the serious overbalance of the abrasion loss of each position of friction face obvious gully phenomenon occurs along the radial direction of friction face.This gully phenomenon is when having accelerated the carbon/carbon brake disc wearing and tearing, and one of root that abnormal vibrations produces when also being aircraft brake becomes the hidden danger that aircraft safety is runed.
Summary of the invention
Technical matters to be solved by this invention is for above-mentioned the deficiencies in the prior art, provides a kind of method of inspection simple and easy to do, and detection technique is ripe, the test set method of completing the square of lower-cost airplane carbon brake disc.The present invention is by the Shore hardness difference of adjacent two airplane carbon brake discs of control group timing, and the Shore hardness difference of a whole set of airplane carbon brake disc, effectively reduce the gully phenomenon of friction face when using, improve the service life of airplane carbon brake disc, avoided the generation of the abnormal vibrations that causes because of airplane carbon brake disc.
For solving the problems of the technologies described above, the technical solution used in the present invention is: a kind of test set method of completing the square of airplane carbon brake disc is characterized in that the method may further comprise the steps:
(1) with the airplane carbon brake disc horizontal positioned, get a plurality of positions as measurement point at friction face, adopt Shore hardometer that described measurement point is carried out the Shore hardnes figure that Shore hardness measures each measurement point; Described measurement point is even circle distribution;
(2) cast out described in the step (1) 1～5 value of deviation maximum in the Shore hardnes figure, calculate again the center line average values of remaining Shore hardnes figure, obtain the average Shore hardness HS of friction face
1
(3) with airplane carbon brake disc upset, repeating step (1) and step (2) obtain the average Shore hardness HS of another friction face
2
(4) calculate average Shore hardness HS
1With average Shore hardness HS
2Center line average values as the standard Shore hardness of airplane carbon brake disc;
The airplane carbon brake disc that (5) will record the standard Shore hardness carries out assembly, and the standard Shore hardness difference of controlling adjacent two airplane carbon brake discs is no more than 10 degree, and the standard Shore hardness difference of a whole set of carbon/carbon brake disc is no more than 20 degree.
The number of measurement point is 6～20 described in the above-mentioned steps (1).
The present invention compared with prior art has the following advantages:
1, method of inspection of the present invention is simple and easy to do, and detection technique is ripe, and check implement is easy and simple to handle, and cost is lower.
2, the present invention is directed to the manufacturing characteristics of airplane carbon brake disc, in conjunction with the handling characteristics of Shore hardometer, proposed the method for inspection of circle distribution, two planar survey, can be good at characterizing the Shore hardness of every airplane carbon brake disc.
3, pass through the Shore hardness difference of adjacent two airplane carbon brake discs of control group timing, and the Shore hardness difference of a whole set of airplane carbon brake disc, effectively reduce the gully phenomenon of friction face when using, improve the service life of airplane carbon brake disc, avoided the generation of the abnormal vibrations that causes because of airplane carbon brake disc.
Description of drawings
Fig. 1 is the measurement point distribution figure of the embodiment of the invention 1 and embodiment 2.
Fig. 2 is the measurement point distribution figure of the embodiment of the invention 3.
Fig. 3 is the measurement point distribution figure of the embodiment of the invention 4.
Fig. 4 is the measurement point distribution figure of the embodiment of the invention 5.
The specific embodiment
Embodiment 1
(1) with the airplane carbon brake disc horizontal positioned, get 8 positions as measurement point at friction face as shown in Figure 1, adopt Shore hardometer that described measurement point is carried out the Shore hardnes figure that Shore hardness measures 8 measurement points;
(2) cast out 2 values of deviation maximum in 8 Shore hardnes figures, calculate again the center line average values of remaining Shore hardnes figure, obtain the average Shore hardness HS of friction face
1
(3) with airplane carbon brake disc upset, repeating step (1) and step (2) obtain the average Shore hardness HS of another friction face
2
(4) calculate HS
1And HS
2Center line average values as the standard Shore hardness of airplane carbon brake disc;
The airplane carbon brake disc that (5) will record the standard Shore hardness carries out assembly, and the standard Shore hardness difference of controlling adjacent two airplane carbon brake discs is no more than 10 degree, and the standard Shore hardness difference of a whole set of carbon/carbon brake disc is no more than 20 degree.
The airplane carbon brake disc that present embodiment detects assembly in actual applications, the gully phenomenon of friction face has obtained effective reduction, also increase the service life of airplane carbon brake disc, and avoided the generation of the abnormal vibrations that causes because of airplane carbon brake disc.
Embodiment 2
(1) with the airplane carbon brake disc horizontal positioned, get 8 positions as measurement point at friction face as shown in Figure 1, adopt Shore hardometer that described measurement point is carried out the Shore hardnes figure that Shore hardness measures 8 measurement points;
(2) cast out 2 values of deviation maximum in 8 Shore hardnes figures, calculate again the center line average values of remaining Shore hardnes figure, obtain the average Shore hardness HS of friction face
1
(3) with airplane carbon brake disc upset, repeating step (1) and step (2) obtain the average Shore hardness HS of another friction face
2
(4) calculate HS
1And HS
2Center line average values as the standard Shore hardness of airplane carbon brake disc;
The airplane carbon brake disc that (5) will record the standard Shore hardness carries out assembly, and the standard Shore hardness difference of controlling adjacent two airplane carbon brake discs is no more than 3 degree, and the standard Shore hardness difference of a whole set of carbon/carbon brake disc is no more than 5 degree.
The airplane carbon brake disc that present embodiment detects assembly in actual applications, the gully phenomenon of friction face has obtained effective reduction, also increase the service life of airplane carbon brake disc, and avoided the generation of the abnormal vibrations that causes because of airplane carbon brake disc.
Embodiment 3
(1) with the airplane carbon brake disc horizontal positioned, get 6 positions as measurement point at friction face as shown in Figure 2, adopt Shore hardometer that described measurement point is carried out the Shore hardnes figure that Shore hardness measures 6 measurement points;
(2) cast out 1 value of deviation maximum in 6 Shore hardnes figures, calculate again the center line average values of remaining Shore hardnes figure, obtain the average Shore hardness HS of friction face
1
(3) with airplane carbon brake disc upset, repeating step (1) and step (2) obtain the average Shore hardness HS of another friction face
2
(4) calculate HS
1And HS
2Center line average values as the standard Shore hardness of airplane carbon brake disc;
The airplane carbon brake disc that (5) will record the standard Shore hardness carries out assembly, and the standard Shore hardness difference of controlling adjacent two airplane carbon brake discs is no more than 2 degree, and the standard Shore hardness difference of a whole set of carbon/carbon brake disc is no more than 5 degree.
The airplane carbon brake disc that present embodiment detects assembly in actual applications, the gully phenomenon of friction face has obtained effective reduction, also increase the service life of airplane carbon brake disc, and avoided the generation of the abnormal vibrations that causes because of airplane carbon brake disc.
Embodiment 4
(1) with the airplane carbon brake disc horizontal positioned, get 10 positions as measurement point at friction face as shown in Figure 3, adopt Shore hardometer that described measurement point is carried out the Shore hardnes figure that Shore hardness measures 10 measurement points;
(2) cast out 3 values of deviation maximum in 10 Shore hardnes figures, calculate again the center line average values of remaining Shore hardnes figure, obtain the average Shore hardness HS of friction face
1
(3) with airplane carbon brake disc upset, repeating step (1) and step (2) obtain the average Shore hardness HS of another friction face
2
(4) calculate HS
1And HS
2Center line average values as the standard Shore hardness of airplane carbon brake disc;
The airplane carbon brake disc that (5) will record the standard Shore hardness carries out assembly, and the standard Shore hardness difference of controlling adjacent two airplane carbon brake discs is no more than 5 degree, and the standard Shore hardness difference of a whole set of carbon/carbon brake disc is no more than 10 degree.
The airplane carbon brake disc that present embodiment detects assembly in actual applications, the gully phenomenon of friction face has obtained effective reduction, also increase the service life of airplane carbon brake disc, and avoided the generation of the abnormal vibrations that causes because of airplane carbon brake disc.
Embodiment 5
(1) with the airplane carbon brake disc horizontal positioned, get 20 positions as measurement point at friction face as shown in Figure 4, adopt Shore hardometer that described measurement point is carried out the Shore hardnes figure that Shore hardness measures 20 measurement points;
(2) cast out 5 values of deviation maximum in 20 Shore hardnes figures, calculate again the center line average values of remaining Shore hardnes figure, obtain the average Shore hardness HS of friction face
1
(3) with airplane carbon brake disc upset, repeating step (1) and step (2) obtain the average Shore hardness HS of another friction face
2
(4) calculate HS
1And HS
2Center line average values as the standard Shore hardness of airplane carbon brake disc;
The airplane carbon brake disc that (5) will record the standard Shore hardness carries out assembly, and the standard Shore hardness difference of controlling adjacent two airplane carbon brake discs is no more than 10 degree, and the standard Shore hardness difference of a whole set of carbon/carbon brake disc is no more than 20 degree.
The airplane carbon brake disc that present embodiment detects assembly in actual applications, the gully phenomenon of friction face has obtained effective reduction, also increase the service life of airplane carbon brake disc, and avoided the generation of the abnormal vibrations that causes because of airplane carbon brake disc.
Claims (2)
1. the test set method of completing the square of an airplane carbon brake disc is characterized in that the method may further comprise the steps:
(1) with the airplane carbon brake disc horizontal positioned, get a plurality of positions as measurement point at friction face, adopt Shore hardometer that described measurement point is carried out the Shore hardnes figure that Shore hardness measures each measurement point; Described measurement point is even circle distribution;
(2) cast out described in the step (1) 1～5 value of deviation maximum in the Shore hardnes figure, calculate again the center line average values of remaining Shore hardnes figure, obtain the average Shore hardness HS of friction face
1
(3) with airplane carbon brake disc upset, repeating step (1) and step (2) obtain the average Shore hardness HS of another friction face
2
(4) calculate average Shore hardness HS
1With average Shore hardness HS
2Center line average values as the standard Shore hardness of airplane carbon brake disc;
The airplane carbon brake disc that (5) will record the standard Shore hardness carries out assembly, and the standard Shore hardness difference of controlling adjacent two airplane carbon brake discs is no more than 10 degree, and the standard Shore hardness difference of a whole set of carbon/carbon brake disc is no more than 20 degree.
2. the test set method of completing the square of a kind of airplane carbon brake disc according to claim 1 is characterized in that, the number of measurement point is 6～20 described in the step (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010105576620A CN102069917B (en) | 2010-11-24 | 2010-11-24 | Method for detecting and assembling aircraft carbon brake discs |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010105576620A CN102069917B (en) | 2010-11-24 | 2010-11-24 | Method for detecting and assembling aircraft carbon brake discs |
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| Publication Number | Publication Date |
|---|---|
| CN102069917A CN102069917A (en) | 2011-05-25 |
| CN102069917B true CN102069917B (en) | 2013-04-17 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2010105576620A Active CN102069917B (en) | 2010-11-24 | 2010-11-24 | Method for detecting and assembling aircraft carbon brake discs |
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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3482430A (en) * | 1966-12-05 | 1969-12-09 | Uniroyal Inc | Portable rebound or skid resistance tester |
| JP3553490B2 (en) * | 2000-11-30 | 2004-08-11 | 株式会社アカシ | Hardness tester |
| CN101082357A (en) * | 2007-05-08 | 2007-12-05 | 南阳二机石油装备(集团)有限公司 | Wear resistant brake disc and manufacturing method therefor |
| CN201096155Y (en) * | 2007-04-05 | 2008-08-06 | 王淑敏 | Landing gear braking disc pair for airplane |
-
2010
- 2010-11-24 CN CN2010105576620A patent/CN102069917B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3482430A (en) * | 1966-12-05 | 1969-12-09 | Uniroyal Inc | Portable rebound or skid resistance tester |
| JP3553490B2 (en) * | 2000-11-30 | 2004-08-11 | 株式会社アカシ | Hardness tester |
| CN201096155Y (en) * | 2007-04-05 | 2008-08-06 | 王淑敏 | Landing gear braking disc pair for airplane |
| CN101082357A (en) * | 2007-05-08 | 2007-12-05 | 南阳二机石油装备(集团)有限公司 | Wear resistant brake disc and manufacturing method therefor |
Non-Patent Citations (3)
| Title |
|---|
| JP特许第3553490号B2 2004.08.11 |
| 公交客车用高性能双层刹车片研制;林荣会等;《润滑与密封》;20100930;第35卷(第9期);102-106 * |
| 林荣会等.公交客车用高性能双层刹车片研制.《润滑与密封》.2010,第35卷(第9期),102-106. |
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|---|---|
| CN102069917A (en) | 2011-05-25 |
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