CN114922924A - Aircraft brake disc manufacturing process - Google Patents
Aircraft brake disc manufacturing process Download PDFInfo
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- CN114922924A CN114922924A CN202210576134.2A CN202210576134A CN114922924A CN 114922924 A CN114922924 A CN 114922924A CN 202210576134 A CN202210576134 A CN 202210576134A CN 114922924 A CN114922924 A CN 114922924A
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- 238000004519 manufacturing process Methods 0.000 title claims abstract description 42
- 239000002346 layers by function Substances 0.000 claims abstract description 182
- 239000010410 layer Substances 0.000 claims abstract description 93
- 238000000034 method Methods 0.000 claims abstract description 32
- 230000008569 process Effects 0.000 claims abstract description 21
- 239000002131 composite material Substances 0.000 claims description 9
- 238000000280 densification Methods 0.000 claims description 5
- CREMABGTGYGIQB-UHFFFAOYSA-N carbon carbon Chemical compound C.C CREMABGTGYGIQB-UHFFFAOYSA-N 0.000 claims description 4
- 239000011203 carbon fibre reinforced carbon Substances 0.000 claims description 4
- 239000000919 ceramic Substances 0.000 claims description 4
- 238000000227 grinding Methods 0.000 abstract description 6
- 238000005299 abrasion Methods 0.000 abstract description 5
- 238000012545 processing Methods 0.000 abstract description 5
- 239000000463 material Substances 0.000 description 30
- 238000002360 preparation method Methods 0.000 description 20
- 238000004064 recycling Methods 0.000 description 5
- 238000005516 engineering process Methods 0.000 description 4
- 238000010586 diagram Methods 0.000 description 2
- 238000005265 energy consumption Methods 0.000 description 2
- 238000005470 impregnation Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 239000004557 technical material Substances 0.000 description 2
- 239000010426 asphalt Substances 0.000 description 1
- 238000004364 calculation method Methods 0.000 description 1
- 238000005229 chemical vapour deposition Methods 0.000 description 1
- 125000004122 cyclic group Chemical group 0.000 description 1
- 238000007598 dipping method Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 238000004663 powder metallurgy Methods 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 239000011347 resin Substances 0.000 description 1
- 229920005989 resin Polymers 0.000 description 1
- 239000002699 waste material Substances 0.000 description 1
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16D—COUPLINGS FOR TRANSMITTING ROTATION; CLUTCHES; BRAKES
- F16D65/00—Parts or details
- F16D65/02—Braking members; Mounting thereof
- F16D65/12—Discs; Drums for disc brakes
- F16D65/127—Discs; Drums for disc brakes characterised by properties of the disc surface; Discs lined with friction material
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16D—COUPLINGS FOR TRANSMITTING ROTATION; CLUTCHES; BRAKES
- F16D69/00—Friction linings; Attachment thereof; Selection of coacting friction substances or surfaces
- F16D69/02—Composition of linings ; Methods of manufacturing
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16D—COUPLINGS FOR TRANSMITTING ROTATION; CLUTCHES; BRAKES
- F16D69/00—Friction linings; Attachment thereof; Selection of coacting friction substances or surfaces
- F16D69/04—Attachment of linings
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16D—COUPLINGS FOR TRANSMITTING ROTATION; CLUTCHES; BRAKES
- F16D65/00—Parts or details
- F16D65/02—Braking members; Mounting thereof
- F16D2065/13—Parts or details of discs or drums
- F16D2065/1304—Structure
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16D—COUPLINGS FOR TRANSMITTING ROTATION; CLUTCHES; BRAKES
- F16D65/00—Parts or details
- F16D65/02—Braking members; Mounting thereof
- F16D2065/13—Parts or details of discs or drums
- F16D2065/134—Connection
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16D—COUPLINGS FOR TRANSMITTING ROTATION; CLUTCHES; BRAKES
- F16D69/00—Friction linings; Attachment thereof; Selection of coacting friction substances or surfaces
- F16D69/04—Attachment of linings
- F16D2069/0425—Attachment methods or devices
- F16D2069/0433—Connecting elements not integral with the braking member, e.g. bolts, rivets
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16D—COUPLINGS FOR TRANSMITTING ROTATION; CLUTCHES; BRAKES
- F16D2250/00—Manufacturing; Assembly
- F16D2250/0061—Joining
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Braking Arrangements (AREA)
Abstract
The invention discloses a manufacturing process of an aircraft brake disc, which comprises the following steps: manufacturing a first structural layer, a second structural layer, a first functional layer and a second functional layer; respectively placing and fixing a first functional layer and a second functional layer on two sides of a first structural layer, and performing a first round of service; splitting the first functional layer, the second functional layer and the first structural layer, and processing and grinding the first functional layer and the second functional layer to a target thickness; and respectively placing the first functional layer and the second functional layer on two sides of the second structural layer, fixing and carrying out second round of service. According to the aircraft brake disc manufacturing process provided by the invention, the first brake disc main body is used for the first round of service, the second brake disc main body is used for the second round of service, and the first functional layer and the second functional layer both use the optimal functional surface as the friction surface in the two-round service process, so that the aircraft brake disc manufacturing process always has the optimal friction and abrasion characteristics and can be selected unconditionally, and the adaptability of product market application is greatly improved.
Description
Technical Field
The invention relates to the field of brake disc manufacturing methods, in particular to a manufacturing process of an airplane brake disc.
Background
The airplane brake disc is the most important consumable in daily operation of airplanes, and common brake disc materials at present comprise carbon-carbon composite materials, carbon-ceramic composite materials and powder metallurgy composite materials. The preparation process of the aircraft brake disc is long in period and large in energy consumption, and in the actual use process, the actual use proportion is small, so that the operation cost of an airline company is high.
In the prior art, the brake disc of the airplane comprises two modes of single use and service life disc reuse: the brake disc is used for a single time, and the brake disc is scrapped integrally after the service abrasion loss is finished; and (4) recycling the longevity plate, namely recycling the longevity plate, processing and grinding the longevity plate flat, and reusing the longevity plate 2 in 1.
The single-use scrapping mode in the prior art is the most common structural form in the industry, the brake disc is scrapped integrally after the service is finished, and the method has the advantages of material utilization rate of only 17%, poor economy and high waste; the service life disc recycling mode is a structural form which is firstly adopted by some leading enterprises abroad, the brake discs are recycled after the first round of service is completed, and two brake discs which reach the service life are recombined into the thickness of a new brake disc for secondary service by a method of processing, grinding and grinding. The method improves the material utilization rate by about 30 percent.
However, due to the recycling mode of the service life disc, the requirement on the preparation process level of the brake material is very high, because the optimal functional surface of the original brake disc is worn and consumed after the original brake disc is subjected to first service, and a new functional surface generated by secondary grinding needs to obtain the friction and wear performance equivalent to the original optimal functional surface under the condition of very small attenuation. Therefore, although the method can improve the utilization rate of the material, the method also puts forward higher requirements on the preparation process and the preparation process, and the material with good uniformity can be used only under the condition of larger thickness, thereby increasing the cost; and moreover, the new functional surface obtained by secondary processing and grinding cannot be randomly mixed with the old and new brake discs due to the performance difference with the original optimal functional surface. Therefore, the method is not popularized and applied in the industry at present.
Therefore, how to improve the material utilization rate of the aircraft brake disc on the premise of ensuring the performance of the aircraft brake disc is a technical problem to be solved by technical personnel in the field at present.
Disclosure of Invention
The invention aims to provide a manufacturing process of an aircraft brake disc, which is used for ensuring the stability of materials and performance to the maximum extent in the whole service process of a brake material.
In order to achieve the purpose, the invention provides the following technical scheme:
a manufacturing process of an aircraft brake disc comprises the following steps:
step S1: manufacturing a first structural layer, a second structural layer, a first functional layer and a second functional layer, wherein the first functional layer and the second functional layer respectively comprise a first friction surface and a second friction surface;
step S2: respectively placing the first functional layer and the second functional layer on two sides of the first structural layer and fixing the first functional layer and the second functional layer, so that the first friction surface of the first functional layer and the first friction surface of the second functional layer are positioned on the outer sides to form a first brake disc main body and perform first service;
step S3: when the thickness of the first functional layer and/or the second functional layer is worn to be smaller than a preset thickness, the first functional layer, the second functional layer and the first structural layer are disassembled, and the first functional layer and the second functional layer are machined and ground to be flat to a target thickness;
step S4: and respectively placing the first functional layer and the second functional layer at two sides of the second structural layer and fixing the first functional layer and the second functional layer, so that the second friction surface of the first functional layer and the second friction surface of the second functional layer are positioned at the outer sides to form a second brake disc main body and perform service of a second wheel.
Preferably, the thickness of the second structural layer is greater than the thickness of the first structural layer.
Preferably, the first structural layer and the second structural layer are both structural layers prepared by a dipping and densifying technology.
Preferably, the first functional layer and/or the second functional layer is a carbon-carbon composite layer or a carbon-ceramic composite layer.
Preferably, the first friction surface and the second friction surface of the first functional layer and the second functional layer are both provided with a carburized or siliconized wear-resistant layer.
Preferably, riveting holes are formed in the edges of the first structural layer, the second structural layer, the first functional layer and the second functional layer;
the step S2 includes: placing the first functional layer and the second functional layer on two sides of the first structural layer respectively and fixing the functional layers through rivets;
the step S4 includes: and respectively placing the first functional layer and the second functional layer on two sides of the second structural layer and fixing.
Preferably, the thickness of the first brake disc body is the same as the thickness of the second brake disc body.
Preferably, the first functional layer and the second functional layer are identical in structure and size.
The invention provides a process for manufacturing an aircraft brake disc, which comprises the following steps: step S1: manufacturing a first structural layer, a second structural layer, a first functional layer and a second functional layer, wherein the first functional layer and the second functional layer respectively comprise a first friction surface and a second friction surface; step S2: respectively placing the first functional layer and the second functional layer on two sides of the first structural layer and fixing the first functional layer and the second functional layer, so that a first friction surface of the first functional layer and a first friction surface of the second functional layer are both positioned on the outer sides to form a first brake disc main body and perform first wheel service; step S3: when the thickness of the first functional layer and/or the second functional layer is abraded to be smaller than a preset thickness, the first functional layer, the second functional layer and the first structural layer are disassembled, and the first functional layer and the second functional layer are machined and abraded to reach a target thickness; step S4: and respectively placing the first functional layer and the second functional layer at two sides of the second structural layer and fixing the first functional layer and the second functional layer, so that the second friction surface of the first functional layer and the second friction surface of the second functional layer are positioned at the outer sides to form a second brake disc main body and perform second wheel service. According to the aircraft brake disc manufacturing process provided by the invention, the first brake disc main body is used for the first round of service, the second brake disc main body is used for the second round of service, and the first functional layer and the second functional layer both use the optimal functional surface as the friction surface in the two-round service process, so that the aircraft brake disc manufacturing process always has the optimal friction and abrasion characteristics, can be selected unconditionally, and further greatly improves the adaptability of product market application.
In a preferred embodiment, the first structural layer, the second structural layer, the first functional layer and the second functional layer are all provided with riveting holes at the edge parts; the step S2 includes: placing the first functional layer and the second functional layer on two sides of the first structural layer respectively and fixing the functional layers through rivets; the step S4 includes: and respectively placing the first functional layer and the second functional layer on two sides of the second structural layer and fixing. According to the arrangement, the first functional layer and the second functional layer are fixedly connected with the first structural layer or the second structural layer in a rivet mode, so that the connection strength between the first functional layer and the second functional layer and between the first structural layer or the second structural layer can be effectively improved, the thickness of the first functional layer and the thickness of the second functional layer can be effectively reduced on the premise that the use requirements can be met, and the production period and the cost can be further effectively reduced.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the drawings without creative efforts.
FIG. 1 is a process diagram of one embodiment of a process for manufacturing an aircraft brake disc according to the present invention;
FIG. 2 is a flow chart of one embodiment of a process for manufacturing an aircraft brake disc according to the present invention;
wherein: 1-a first structural layer; 2-a second structural layer; 3-a first functional layer; 4-a second functional layer.
Detailed Description
The core of the invention is to provide a manufacturing process of the aircraft brake disc, which can obviously improve the preparation efficiency of the aircraft brake disc and reduce the preparation cost.
In order that those skilled in the art will better understand the disclosure, the invention will be described in further detail with reference to the accompanying drawings and specific embodiments.
Referring to fig. 1 and 2, fig. 1 is a schematic process diagram of an embodiment of a manufacturing process of an aircraft brake disc according to the present invention; fig. 2 is a flow chart of an embodiment of the manufacturing process of the aircraft brake disc provided by the invention.
In this embodiment, the aircraft brake disc manufacturing process comprises the following steps:
step S1: manufacturing a first structural layer 1, a second structural layer 2, a first functional layer 3 and a second functional layer 4, wherein the first functional layer 3 and the second functional layer 4 respectively comprise a first friction surface and a second friction surface, specifically, the first friction surface and the second friction surface of the first functional layer 3 are respectively positioned at two sides of the first functional layer 3, and the first friction surface and the second friction surface of the second functional layer 4 are respectively positioned at two sides of the second functional layer 4;
step S2: respectively placing and fixing the first functional layer 3 and the second functional layer 4 on two sides of the first structural layer 1, as shown in fig. 1, so that the first friction surface of the first functional layer 3 and the first friction surface of the second functional layer 4 are both positioned on the outer side to form a first brake disc main body and perform first wheel service; that is to say, the two friction surfaces of the first brake disc body are respectively the first friction surface of the first functional layer 3 and the first friction surface of the second functional layer 4;
step S3: when the thickness of the first functional layer 3 and/or the second functional layer 4 is worn to be smaller than the preset thickness, namely the first friction surface of the first functional layer 3 and/or the second functional layer 4 does not meet the use requirement any more, the first functional layer 3, the second functional layer 4 and the first structural layer 1 are disassembled, and the first functional layer 3 and the second functional layer 4 are machined and ground to be the target thickness;
step S4: respectively placing and fixing the first functional layer 3 and the second functional layer 4 on two sides of the second structural layer 2, so that a second friction surface of the first functional layer 3 and a second friction surface of the second functional layer 4 are positioned on the outer sides to form a second brake disc main body and perform second wheel service; that is to say, the two friction surfaces of the second brake disc body are respectively the second friction surface of the first functional layer 3 and the second friction surface of the second functional layer 4;
the preparation process of the aircraft brake disc material has the characteristics of high energy consumption and long period, so that the aim of the invention is to improve the utilization rate of the material on the premise of ensuring the friction and wear performance of the material; meanwhile, the thicker the material of the aircraft brake disc is, the more difficult the material is to prepare, and the higher the preparation cost is, so that the invention can reduce the material thickness, improve the preparation efficiency and reduce the preparation cost; the aircraft brake disc manufacturing process provided by the invention can ensure that the stability of the material and the performance of the brake material can be ensured to the maximum extent in the whole service process.
In addition to the above embodiments, in step S1, the thickness of the second structure layer 2 is greater than the thickness of the first structure layer 1, and the thickness of the second structure layer 2 is greater than the thickness of the first structure layer 1, so that the reduction in thickness of the first functional layer 3 and the second functional layer 4 due to the processing and the leveling can be compensated for.
In addition to the above embodiments, in step S1, the first structural layer 1 and the second structural layer 2 are both prepared by using an impregnation densification technique, and preferably, the first structural layer 1 and the second structural layer 2 are formed into a structure with high density and high strength by using an inexpensive resin or asphalt impregnation densification technique; the functional layer adopts a precise chemical vapor deposition technology to form a structure with good friction and wear characteristics. Specifically, the first structural layer 1 and the second structural layer 2 are prepared by adopting a densification technology with lower cost, compared with the traditional brake material preparation technology, the structural layer material has low requirements on the process level and short preparation period, and the structural layers adopted in the invention can be recycled for a long time in the service process of the brake material, so that the production cost is greatly saved.
In addition to the above embodiments, in step S1, the first functional layer 3 and/or the second functional layer 4 are/is a carbon-carbon composite layer or a carbon-ceramic composite layer, but other materials used for a conventional brake disc may also be selected.
In addition to the above embodiments, in step S1, the first friction surface and the second friction surface of the first functional layer 3 and the second functional layer 4 are provided with the carburized or siliconized wear-resistant layer having excellent friction and wear, and the life of the friction surfaces is increased.
In addition to the above embodiments, the first structural layer 1, the second structural layer 2, the first functional layer 3, and the second functional layer 4 are provided with staking holes at their edges;
step S2 includes: placing the first functional layer 3 and the second functional layer 4 on two sides of the first structural layer 1 respectively and fixing by rivets;
step S4 includes: the first functional layer 3 and the second functional layer 4 are placed on both sides of the second structural layer 2 and fixed, respectively.
According to the arrangement, the first functional layer 3 and the second functional layer 4 are fixedly connected with the first structural layer 1 or the second structural layer 2 in a rivet mode, so that the connection strength between the first functional layer 3 and the second functional layer 4 and the first structural layer 1 or the second structural layer 2 can be effectively improved, the thickness of the first functional layer 3 and the thickness of the second functional layer 4 can be effectively reduced on the premise of meeting the use requirements, and the production period and the cost can be effectively reduced.
On the basis of the above embodiments, the thickness of the first brake disc main body is the same as that of the second brake disc main body, and as shown in fig. 1, the thickness of the first brake disc main body and that of the second brake disc main body are both a, so that the service effect of two wheels is basically consistent.
In addition to the above embodiments, the first functional layer 3 and the second functional layer 4 have the same structure and size, and thus the positions can be interchanged, thereby improving the applicability.
In a specific embodiment, the aircraft brake disc manufactured by the aircraft brake disc manufacturing process comprises two functional layers and a structural layer, wherein the functional layers are processed and ground by a conventional brake disc material preparation process, and the thickness of the functional layers is greatly reduced, so that the required production period is shorter and the production cost is lower in the preparation process; in the first round of service process, the first functional layer 3, the second functional layer 4 and the first structural layer 1 form a brake disc, after the service is finished, the first structural layer 1 is reserved, the first functional layer 3 and the second functional layer 4 are processed and ground to be flat, and are recombined with the second structural layer 2 with larger thickness to form the brake disc with the same thickness, the second round of service is carried out, the second round of service is finished, and the first functional layer 3 and the second functional layer 4 are scrapped after two rounds of service are finished; the first structural layer 1 and the second structural layer 2 are respectively reserved to participate in the combination of the next round, and the material recycling at the maximum is realized.
The aircraft brake disc manufacturing process provided by the invention has the following advantages:
1. the material utilization rate is greatly improved, the material utilization rate can reach 75 percent by twice combination of the functional layers and cyclic utilization of the structural layer, the utilization rate of the technical material widely applied at present is only 17 percent, and the best utilization rate of the technical material is only 30 percent;
2. the functional layer designed by the invention greatly reduces the thickness of the material, so that the preparation period can be shortened, the production cost can be reduced, and meanwhile, the material with better material consistency and better frictional wear performance can be obtained, and through measurement and calculation, the preparation method provided by the invention can shorten the preparation period by 40 percent and save the production cost by 50 percent;
3. the brake disc of the airplane takes the optimal functional surface as the friction surface in the two-wheel service process, so that the brake disc always has the optimal friction and abrasion characteristics and can be selected and matched unconditionally, thereby greatly improving the adaptability of the market application of products;
4. the preparation method designed by the invention separates the functional layer participating in friction and abrasion from the structural layer only providing structural support, adopts the conventional brake material preparation process to produce the functional layer, and can obtain a higher-quality brake material due to the smaller thickness, shortened preparation period and provided manufacturability; the structural layers are produced by adopting a low-cost rapid densification method, the structural layers can be prepared in batches at low cost and high efficiency, and the structural layers can be recycled in the combination process.
The manufacturing process of the aircraft brake disc provided by the invention is described in detail above. The principles and embodiments of the present invention have been described herein using specific examples, which are presented only to assist in understanding the method and its core concepts of the present invention. It should be noted that, for those skilled in the art, it is possible to make various improvements and modifications to the present invention without departing from the principle of the present invention, and those improvements and modifications also fall within the scope of the claims of the present invention.
Claims (8)
1. The manufacturing process of the aircraft brake disc is characterized by comprising the following steps:
step S1: manufacturing a first structural layer (1), a second structural layer (2), a first functional layer (3) and a second functional layer (4), wherein the first functional layer (3) and the second functional layer (4) respectively comprise a first friction surface and a second friction surface;
step S2: respectively placing the first functional layer (3) and the second functional layer (4) at two sides of the first structural layer (1) and fixing the first functional layer and the second functional layer, so that a first friction surface of the first functional layer (3) and a first friction surface of the second functional layer (4) are positioned at the outer sides to form a first brake disc main body and perform first wheel service;
step S3: when the thickness of the first functional layer (3) and/or the second functional layer (4) is worn to be smaller than a preset thickness, the first functional layer (3), the second functional layer (4) and the first structural layer (1) are disassembled, and the first functional layer (3) and the second functional layer (4) are machined and ground to a target thickness;
step S4: and respectively placing the first functional layer (3) and the second functional layer (4) at two sides of the second structural layer (2) and fixing the first functional layer and the second functional layer, so that the second friction surface of the first functional layer (3) and the second friction surface of the second functional layer (4) are positioned at the outer sides to form a second brake disc main body and perform second wheel service.
2. Process for manufacturing an aircraft brake disc according to claim 1, characterized in that the thickness of the second structural layer (2) is greater than the thickness of the first structural layer (1).
3. The aircraft brake disc manufacturing process according to claim 1, wherein the first structural layer (1) and the second structural layer (2) are both structural layers prepared by a dip densification technique.
4. Process for manufacturing an aircraft brake disc according to claim 1, characterized in that the first functional layer (3) and/or the second functional layer (4) are carbon-carbon composite layers or carbon-ceramic composite layers.
5. Process for manufacturing an aircraft brake disc according to claim 1, characterized in that the first friction surface and the second friction surface of the first functional layer (3) and the second functional layer (4) are provided with a carburized or siliconized wear layer.
6. Process for manufacturing an aircraft brake disc according to any one of claims 1 to 5, characterized in that the first structural layer (1), the second structural layer (2), the first functional layer (3) and the second functional layer (4) are provided with riveting holes at their edges;
the step S2 includes: placing the first functional layer (3) and the second functional layer (4) on two sides of the first structural layer (1) respectively and fixing by rivets;
the step S4 includes: and respectively placing the first functional layer (3) and the second functional layer (4) on two sides of the second structural layer (2) and fixing.
7. Process for manufacturing an aircraft brake disc according to any one of claims 1 to 5, wherein the thickness of the first brake disc body is the same as the thickness of the second brake disc body.
8. Process for manufacturing an aircraft brake disc according to any one of claims 1 to 5, characterized in that the first functional layer (3) and the second functional layer (4) are of the same structure and dimensions.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210576134.2A CN114922924B (en) | 2022-05-25 | 2022-05-25 | Manufacturing process of aircraft brake disc |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210576134.2A CN114922924B (en) | 2022-05-25 | 2022-05-25 | Manufacturing process of aircraft brake disc |
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| Publication Number | Publication Date |
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| CN114922924A true CN114922924A (en) | 2022-08-19 |
| CN114922924B CN114922924B (en) | 2023-08-22 |
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| CN202210576134.2A Active CN114922924B (en) | 2022-05-25 | 2022-05-25 | Manufacturing process of aircraft brake disc |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115504801A (en) * | 2022-09-01 | 2022-12-23 | 湖南博云新材料股份有限公司 | Preparation method of carbon/carbon composite material brake disc |
| CN115823151A (en) * | 2023-02-15 | 2023-03-21 | 西安超码科技有限公司 | Carbon/ceramic brake disc with sandwich structure |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| US4982818A (en) * | 1989-10-17 | 1991-01-08 | Allied-Signal Inc. | Cyclic brake disc overhaul technique and structure |
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| CN115823151A (en) * | 2023-02-15 | 2023-03-21 | 西安超码科技有限公司 | Carbon/ceramic brake disc with sandwich structure |
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| CN114922924B (en) | 2023-08-22 |
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