CN114922924B - Manufacturing process of aircraft brake disc - Google Patents
Manufacturing process of aircraft brake disc Download PDFInfo
- Publication number
- CN114922924B CN114922924B CN202210576134.2A CN202210576134A CN114922924B CN 114922924 B CN114922924 B CN 114922924B CN 202210576134 A CN202210576134 A CN 202210576134A CN 114922924 B CN114922924 B CN 114922924B
- Authority
- CN
- China
- Prior art keywords
- functional layer
- layer
- brake disc
- structural
- functional
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 238000004519 manufacturing process Methods 0.000 title claims abstract description 39
- 239000002346 layers by function Substances 0.000 claims abstract description 174
- 239000010410 layer Substances 0.000 claims abstract description 93
- 239000002131 composite material Substances 0.000 claims description 10
- 238000005516 engineering process Methods 0.000 claims description 10
- 238000000280 densification Methods 0.000 claims description 6
- 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
- 238000000034 method Methods 0.000 abstract description 18
- 238000000227 grinding Methods 0.000 abstract description 7
- 239000000463 material Substances 0.000 description 30
- 238000002360 preparation method Methods 0.000 description 18
- 238000004064 recycling Methods 0.000 description 4
- 238000005299 abrasion Methods 0.000 description 3
- 238000005470 impregnation Methods 0.000 description 3
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 2
- 230000006978 adaptation Effects 0.000 description 2
- 229910052799 carbon Inorganic materials 0.000 description 2
- 238000005265 energy consumption Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 239000010426 asphalt Substances 0.000 description 1
- 230000002238 attenuated effect Effects 0.000 description 1
- 238000004364 calculation method Methods 0.000 description 1
- 238000005229 chemical vapour deposition Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000004663 powder metallurgy Methods 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
Classifications
-
- 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
-
- 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
-
- 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
-
- 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
-
- 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
-
- 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
-
- 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
-
- 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
Landscapes
- 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; the first functional layer and the second functional layer are respectively placed on two sides of the first structural layer and fixed, and a first round of service is carried out; 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 the first functional layer and the second functional layer, and performing second-round service. According to the manufacturing process of the aircraft brake disc, the first wheel service is performed through the first brake disc main body, the second wheel service is performed through the second brake disc main body, and in the two-wheel service process, the first functional layer and the second functional layer are both the optimal functional surfaces as friction surfaces, so that the aircraft brake disc has optimal friction and wear characteristics all the time, can be subjected to unconditional matching, and greatly improves the suitability of product market application.
Description
Technical Field
The invention relates to the field of brake disc manufacturing methods, in particular to an aircraft brake disc manufacturing process.
Background
The aircraft brake disc is the most important consumable in the daily operation of the aircraft, and the common brake disc materials at present are carbon-carbon composite materials, carbon-ceramic composite materials and powder metallurgy composite materials. The preparation process of the aircraft brake disc has long period and high energy consumption, and in the actual use process, the actual use part has small duty ratio, so that the operation cost of an airline company is high.
In the prior art, an aircraft brake disc comprises two modes of single use and service life disc recycling: the brake disc is used for one time, and is scrapped integrally after finishing the service wear amount; and (3) recycling the service life plate, recovering the service life plate, processing and grinding the service life plate until the service life plate is flat, and then reusing the service life plate in a 2-in-1 mode.
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 completed, and the method has the advantages of low material utilization rate of only 17%, low economical efficiency and high waste; the service disc recycling mode is a structural form adopted by some leading enterprises abroad at first, the brake disc is recycled after the first-wheel service is completed, and the two service-life brake discs are recombined into the thickness of a new brake disc to carry out the second service by a method of processing, grinding and leveling to grinding. The material utilization rate of the method is improved by about 30 percent.
However, the requirement on the preparation technology level of the brake material is very high due to the fact that the service life of the service life disc is reached, because the original brake disc is worn and consumed by the optimal functional surface after the first round of service, and the new functional surface generated by secondary grinding can obtain friction and wear performance equivalent to the original optimal functional surface only under the condition of very small attenuation. Therefore, although the method can improve the utilization rate of materials, higher requirements are put on the preparation process and the preparation process, materials with good uniformity can be used only under the condition of larger thickness, and the cost is increased; and the new functional surface obtained by secondary processing and grinding can not be randomly mixed with the new and old brake discs due to the difference in performance between the new functional surface and the original optimal functional surface. Therefore, the method in the industry is not popularized and applied 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 which needs to be solved by the technicians 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 performances to the greatest extent in the whole service process of a brake material.
In order to achieve the above purpose, the present invention provides the following technical solutions:
the manufacturing process of the aircraft brake disc comprises the following steps of:
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 both comprise a first friction surface and a second friction surface;
step S2: the first functional layer and the second functional layer are respectively placed on two sides of the first structural layer and fixed, 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 side to form a first brake disc main body, and a first wheel service is performed;
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 detached, and the first functional layer and the second functional layer are processed and ground to be the target thickness;
step S4: and respectively placing and fixing the first functional layer and the second functional layer on two sides of the second structural layer, so that the second friction surface of the first functional layer and the second friction surface of the second functional layer are both positioned on the outer side to form a second brake disc main body, and performing second wheel service.
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 impregnation densification 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, carburized or siliconized wear-resistant layers are arranged on the first friction surface and the second friction surface of the first functional layer and the second functional layer.
Preferably, the edges of the first structural layer, the second structural layer, the first functional layer and the second functional layer are provided with riveting holes;
the step S2 includes: the first functional layer and the second functional layer are respectively placed on two sides of the first structural layer and fixed 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 the first functional layer and the second functional layer.
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 the same in structure and size.
The invention provides a manufacturing process of 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 both comprise a first friction surface and a second friction surface; step S2: the first functional layer and the second functional layer are respectively placed on two sides of the first structural layer and fixed, 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 side to form a first brake disc main body, and a first wheel service is performed; 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 detached, and the first functional layer and the second functional layer are processed and ground to be the target thickness; step S4: and respectively placing and fixing the first functional layer and the second functional layer on two sides of the second structural layer, so that the second friction surface of the first functional layer and the second friction surface of the second functional layer are both positioned on the outer side to form a second brake disc main body, and performing second wheel service. According to the manufacturing process of the aircraft brake disc, the first wheel service is performed through the first brake disc main body, the second wheel service is performed through the second brake disc main body, and in the two wheel service processes, the first functional layer and the second functional layer are both the optimal functional surfaces serving as friction surfaces, so that the aircraft brake disc has optimal friction and wear characteristics all the time, can be subjected to unconditional matching, and greatly improves the suitability of product market application.
In a preferred embodiment, the edges of the first structural layer, the second structural layer, the first functional layer and the second functional layer are provided with riveting holes; the step S2 includes: the first functional layer and the second functional layer are respectively placed on two sides of the first structural layer and fixed 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 the first functional layer and the second functional layer. Above-mentioned setting, first functional layer with the second functional layer with first structural layer or adopt the mode of rivet to connect fixedly between the second structural layer, can effectively improve first functional layer the second functional layer with first structural layer or the joint strength between the second structural layer can satisfy under the prerequisite of operation requirement, effectively with first functional layer with the thickness of second functional layer, and then effectively reduce production cycle and cost.
Drawings
In order to more clearly illustrate the embodiments of the invention or the technical solutions in the prior art, the drawings that are required in the embodiments or the description of the prior art will be briefly described, it being obvious that the drawings in the following description are only some embodiments of the invention, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic illustration of a process for one embodiment of an aircraft brake disc manufacturing process provided by the present invention;
FIG. 2 is a flow chart of an embodiment of an aircraft brake disc manufacturing process provided by 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 manufacturing efficiency of the aircraft brake disc and reduce the manufacturing cost.
In order to better understand the aspects of the present invention, the present invention will be described in further detail with reference to the accompanying drawings and detailed description.
Referring to fig. 1 and 2, fig. 1 is a schematic process diagram of an embodiment of an aircraft brake disc manufacturing process according to the present invention; fig. 2 is a flowchart of an embodiment of an aircraft brake disc manufacturing process provided by the invention.
In this embodiment, the aircraft brake disc manufacturing process comprises the steps of:
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 comprise a first friction surface and a second friction surface, and 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: the first functional layer 3 and the second functional layer 4 are respectively placed and fixed on two sides of the first structural layer 1, as shown in fig. 1, so that a first friction surface of the first functional layer 3 and a 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 a first wheel service is performed; that is, the two friction surfaces of the first brake disc body are the first friction surface of the first functional layer 3 and the first friction surface of the second functional layer 4, respectively;
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 no longer meets the use requirement, the first functional layer 3, the second functional layer 4 and the first structural layer 1 are detached, and the first functional layer 3 and the second functional layer 4 are processed and ground to be the target thickness;
step S4: the first functional layer 3 and the second functional layer 4 are respectively placed and fixed 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 side to form a second brake disc main body, and second wheel service is performed; that is, the two friction surfaces of the second brake disc body are the second friction surface of the first functional layer 3 and the second friction surface of the second functional layer 4, respectively;
because the preparation process of the aircraft brake disc material has the characteristics of high energy consumption and long period, the aim of the invention is to improve the utilization rate of the material on the premise of ensuring the friction and abrasion performance of the material; meanwhile, the preparation of the aircraft brake disc material also has the characteristics of thicker thickness, harder preparation and higher preparation cost, so that the preparation efficiency is improved and the preparation cost is reduced; the aircraft brake standby material is a composite material, and has performance difference along the surface to the inside of the material, and is particularly characterized in that the density is from high to low, and friction and abrasion performance are attenuated.
On the basis of the above embodiments, in step S1, the thickness of the second structural layer 2 is greater than the thickness of the first structural layer 1, and the thickness of the second structural layer 2 is greater than the thickness of the first structural layer 1, so that the thickness reduction of the first functional layer 3 and the second functional layer 4 due to the process and the grinding to the flat can be filled.
Based on the above embodiments, in step S1, the first structural layer 1 and the second structural layer 2 are both structural layers prepared by using an impregnation densification technology, 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 technology; 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 technological level and short preparation period, and the structural layer 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 the above embodiments, in step S1, the first functional layer 3 and/or the second functional layer 4 are carbon-carbon composite layers or carbon ceramic composite layers, and of course, other materials used for a conventional brake disc may be selected.
In step S1, carburized or siliconized wear-resistant layers having excellent friction and wear are provided on the first and second friction surfaces of the first and second functional layers 3 and 4, respectively, so that 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 rivet holes at the edges thereof;
the step S2 comprises the following steps: the first functional layer 3 and the second functional layer 4 are respectively placed on two sides of the first structural layer 1 and fixed by rivets;
the 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.
Above-mentioned setting adopts the mode of rivet to connect fixedly between first functional layer 3 and second functional layer 4 and first structural layer 1 or the second structural layer 2, can effectively improve the joint strength between first functional layer 3, second functional layer 4 and first structural layer 1 or the second structural layer 2, can satisfy under the prerequisite of operation requirement, effectively with the thickness of first functional layer 3 and second functional layer 4, and then effectively reduce production cycle and cost.
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, as shown in fig. 1, the thickness of the first brake disc main body and the thickness of the second brake disc main body are both a, so that the service effects of two wheels are basically consistent.
On the basis of the above embodiments, the first functional layer 3 and the second functional layer 4 have the same structure and size, so that the position exchange can be realized and the applicability can be improved.
In a specific embodiment, the aircraft brake disc manufactured by adopting the aircraft brake disc manufacturing process provided by the invention comprises two functional layers and one structural layer, wherein the functional layers are processed and ground to be flat by adopting the conventional brake disc material manufacturing process; the first wheel service process comprises the steps of forming a brake disc by the first functional layer 3, the second functional layer 4 and the first structural layer 1, reserving the first structural layer 1 after the service is completed, processing and leveling the first functional layer 3 and the second functional layer 4, recombining the first functional layer 3 and the second functional layer 4 with the second structural layer 2 with larger thickness to form the brake disc with the same thickness, performing the second wheel service, completing the second wheel service, and scrapping the first functional layer 3 and the second functional layer 4 after the two wheels of service are completed; the first structural layer 1 and the second structural layer 2 are reserved to participate in the combination of the next round respectively, so that the material recycling to the maximum extent 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% through twice combination of the functional layers and the structural layers, the material utilization rate of the technology widely applied at present is only 17%, and the best technology material utilization rate is also only 30%;
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, meanwhile, the material with better material consistency and better friction and wear performance can be obtained, and through calculation, the preparation method disclosed by the invention can shorten the preparation period by 40%, and the production cost can be saved by 50%;
3. in the two-wheel service process, the aircraft brake disc provided by the invention takes the optimal functional surface as the friction surface, so that the aircraft brake disc always has optimal friction and wear characteristics, can be subjected to unconditional matching, and greatly improves the suitability of the product for market application;
4. the preparation method provided by the invention is characterized in that the functional layer which participates in friction and abrasion is separated from the structural layer which only provides structural support, and the functional layer is produced by adopting a conventional brake material preparation process, so that the preparation period is shortened due to the smaller thickness, and the manufacturability is provided, so that a brake material with higher quality can be obtained; the structural layer is produced by adopting a low-cost rapid densification method, so that the structural layer can be prepared in batches with low cost and high efficiency and can be recycled in the combination process.
The aircraft brake disc manufacturing process provided by the invention is described in detail above. The principles and embodiments of the present invention have been described herein with reference to specific examples, the description of which is intended only to facilitate an understanding of the method of the present invention and its core ideas. It should be noted that it will be apparent to those skilled in the art that various modifications and adaptations of the invention can be made without departing from the principles of the invention and these modifications and adaptations are intended to be within the scope of the invention as defined in the following claims.
Claims (7)
1. The manufacturing process of the aircraft brake disc is characterized by comprising the following steps of:
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) comprise a first friction surface and a second friction surface; carburized or siliconized wear-resistant layers are arranged on the first friction surface and the second friction surface of the first functional layer (3) and the second functional layer (4);
step S2: the first functional layer (3) and the second functional layer (4) are respectively placed on two sides of the first structural layer (1) and fixed, 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 on the outer side to form a first brake disc main body, and a first wheel service is performed;
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 detached, and the first functional layer (3) and the second functional layer (4) are processed and leveled to a target thickness;
step S4: and 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 the second friction surface of the first functional layer (3) and the second friction surface of the second functional layer (4) are positioned on the outer side to form a second brake disc main body, and performing second wheel service.
2. Aircraft brake disc manufacturing process 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, characterized in that the first structural layer (1) and the second structural layer (2) are both structural layers produced by dip densification technology.
4. Aircraft brake disc manufacturing process 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. Aircraft brake disc manufacturing process according to any one of claims 1 to 4, characterized in that the edges of 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;
the step S2 includes: the first functional layer (3) and the second functional layer (4) are respectively placed on two sides of the first structural layer (1) and fixed by rivets;
the step S4 includes: the first functional layer (3) and the second functional layer (4) are respectively placed on two sides of the second structural layer (2) and fixed.
6. The aircraft brake disc manufacturing process according to any one of claims 1 to 4, wherein the thickness of the first brake disc body is the same as the thickness of the second brake disc body.
7. Aircraft brake disc manufacturing process according to any one of claims 1 to 4, characterized in that the first functional layer (3) is of the same structure and dimensions as the second functional layer (4).
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 |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210576134.2A CN114922924B (en) | 2022-05-25 | 2022-05-25 | Manufacturing process of aircraft brake disc |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114922924A CN114922924A (en) | 2022-08-19 |
| CN114922924B true CN114922924B (en) | 2023-08-22 |
Family
ID=82810479
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210576134.2A Active CN114922924B (en) | 2022-05-25 | 2022-05-25 | Manufacturing process of aircraft brake disc |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114922924B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115504801B (en) * | 2022-09-01 | 2023-07-21 | 湖南博云新材料股份有限公司 | Preparation method of carbon/carbon composite brake disc |
| CN115823151B (en) * | 2023-02-15 | 2023-06-20 | 西安超码科技有限公司 | Sandwich-structured carbon/ceramic brake disc |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4982818A (en) * | 1989-10-17 | 1991-01-08 | Allied-Signal Inc. | Cyclic brake disc overhaul technique and structure |
| FR2661866A1 (en) * | 1990-05-10 | 1991-11-15 | Lorraine Carbone | Multilayer friction element made of carbon-carbon composite material having a differential texture, and its method of manufacture |
| CN1823234A (en) * | 2003-07-15 | 2006-08-23 | 都恩罗普空间技术有限公司 | Composite article |
| CN101413558A (en) * | 2008-11-28 | 2009-04-22 | 杨力 | The reconditioning technology and the technology thereof of the carbon/carbon/carbon aviation brake disc after the longevity |
| CN102635651A (en) * | 2012-04-20 | 2012-08-15 | 陕西蓝太航空设备有限责任公司 | Airplane carbon brake disc with big-thickness difference structure and maintenance method for airplane carbon brake disc |
| FR3013412A1 (en) * | 2013-11-21 | 2015-05-22 | Messier Bugatti Dowty | METHOD FOR RENOVATING AND USING REAR STATOR BRAKE DISC BRAKES, ASSEMBLED DISK AND CORRESPONDING DISC BATTERY. |
| DE102019121698A1 (en) * | 2019-08-12 | 2021-05-06 | Thyssenkrupp Steel Europe Ag | Multi-layer composite and method for producing a multi-layer composite |
| CN112824697A (en) * | 2019-11-21 | 2021-05-21 | 霍尼韦尔国际公司 | Brake disc assembly |
-
2022
- 2022-05-25 CN CN202210576134.2A patent/CN114922924B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4982818A (en) * | 1989-10-17 | 1991-01-08 | Allied-Signal Inc. | Cyclic brake disc overhaul technique and structure |
| FR2661866A1 (en) * | 1990-05-10 | 1991-11-15 | Lorraine Carbone | Multilayer friction element made of carbon-carbon composite material having a differential texture, and its method of manufacture |
| CN1823234A (en) * | 2003-07-15 | 2006-08-23 | 都恩罗普空间技术有限公司 | Composite article |
| CN101413558A (en) * | 2008-11-28 | 2009-04-22 | 杨力 | The reconditioning technology and the technology thereof of the carbon/carbon/carbon aviation brake disc after the longevity |
| CN102635651A (en) * | 2012-04-20 | 2012-08-15 | 陕西蓝太航空设备有限责任公司 | Airplane carbon brake disc with big-thickness difference structure and maintenance method for airplane carbon brake disc |
| FR3013412A1 (en) * | 2013-11-21 | 2015-05-22 | Messier Bugatti Dowty | METHOD FOR RENOVATING AND USING REAR STATOR BRAKE DISC BRAKES, ASSEMBLED DISK AND CORRESPONDING DISC BATTERY. |
| DE102019121698A1 (en) * | 2019-08-12 | 2021-05-06 | Thyssenkrupp Steel Europe Ag | Multi-layer composite and method for producing a multi-layer composite |
| CN112824697A (en) * | 2019-11-21 | 2021-05-21 | 霍尼韦尔国际公司 | Brake disc assembly |
Also Published As
| Publication number | Publication date |
|---|---|
| CN114922924A (en) | 2022-08-19 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN114922924B (en) | Manufacturing process of aircraft brake disc | |
| CN101100930B (en) | Surface strengthening steel tooth wheel and manufacturing method thereof | |
| CN111590053B (en) | Manufacturing method of easily-machined and repairable high-wear-resistance metal ceramic composite grinding roller | |
| CN1843644A (en) | Hard alloy composite roll collar for high-speed wire production line and method for manufacturing the same | |
| CN103273651B (en) | The associated methods of metal parts and carbon fibre composite in aviation structural member | |
| CN104313518B (en) | Ceramic composite material as well as preparation method and application thereof | |
| JP3227854U (en) | Diamond composite brazed coating layer structure | |
| CN101870092A (en) | Millstone for processing crystal and manufacturing method thereof | |
| CN114774759A (en) | Layered gradient SiC ceramic reinforced iron-based wear-resistant material and preparation method thereof | |
| CN101869985A (en) | Method for preparing metal ceramic coating material with plasma/combustion synthesis/quasistatic pressing process | |
| CN101963199A (en) | Motor vehicle aluminium alloy brake with micro-arc oxidation ceramic coating braking surface | |
| CN114774907A (en) | Preparation method of nano diamond particle enhanced wear-resistant coating on titanium alloy surface | |
| CN108728785A (en) | A kind of preparation method of nickel chromium triangle borosilicate niobium alloy wear-resistant coating | |
| CN113373439B (en) | Composite coating for improving surface wear resistance of 35CrMoV steel and preparation method thereof | |
| JPH11107913A (en) | Shoe and its manufacture | |
| CN104388891A (en) | Hardening method of inner surface of cylinder barrel of titanium and titanium alloy hydraulic cylinder | |
| EP1359339A2 (en) | Method of manufacturing a friction plate | |
| CN103264359B (en) | Micro-drill lip half fine grinding resin wheel and preparation method thereof | |
| CN105196651A (en) | Multi-dimensional fiber high-performance friction material and preparation method thereof | |
| CN105750809A (en) | Repairing technique for impeller of circulating pump | |
| CN107498454A (en) | A kind of manufacture craft of abrasive disk | |
| CN100402169C (en) | Composite Roll Collar | |
| CN113843662A (en) | Grinding method of runway part | |
| CN114262888A (en) | In-situ ceramic antifriction coating on steel surface and preparation method thereof | |
| US20080265218A1 (en) | Composite layer and method of forming same |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |