CN108526491B - Machine tool machining method for multi-component blank body of high-temperature-resistant heat-insulation sandwich material - Google Patents
Machine tool machining method for multi-component blank body of high-temperature-resistant heat-insulation sandwich material Download PDFInfo
- Publication number
- CN108526491B CN108526491B CN201710121140.8A CN201710121140A CN108526491B CN 108526491 B CN108526491 B CN 108526491B CN 201710121140 A CN201710121140 A CN 201710121140A CN 108526491 B CN108526491 B CN 108526491B
- Authority
- CN
- China
- Prior art keywords
- layer
- component
- processing
- positioning
- sandwich
- 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
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23B—TURNING; BORING
- B23B1/00—Methods for turning or working essentially requiring the use of turning-machines; Use of auxiliary equipment in connection with such methods
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23B—TURNING; BORING
- B23B5/00—Turning-machines or devices specially adapted for particular work; Accessories specially adapted therefor
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23C—MILLING
- B23C3/00—Milling particular work; Special milling operations; Machines therefor
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Milling Processes (AREA)
- Laminated Bodies (AREA)
Abstract
The invention provides a machine tool processing method of a multi-component green body of a high-temperature-resistant heat-insulating sandwich material, which comprises the following steps: (1) placing the component material blank in a processing tool; (2) positioning the component material blank by using the positioning features; (3) fixing the positioned component material blank; (4) performing edge cutting processing on the component material blank to obtain an edge cutting processed component; (5) further cutting the edge cutting process member into a plurality of multilayer members by a dividing process; wherein the component material blank has a heterogeneous layer structure and comprises a plurality of multilayer components, and the edge cutting process and/or the dividing process is performed by means of a machine tool. The method is simple, is easy and convenient to operate, has little pollution to the environment, and can greatly improve the processing precision and the processing efficiency of the component.
Description
Technical Field
The invention relates to the technical field of heat insulation materials, in particular to a processing method of a high-temperature-resistant heat insulation sandwich material member.
Background
In the process of long-term high-speed cruising of the hypersonic aircraft in the atmosphere, the hypersonic aircraft is subjected to severe air and heat load effects. In order to ensure the complete appearance structure of the aircraft and the normal operation of the internal components, a thermal protection system with temperature resistance, heat insulation and bearing functions is required to protect the aircraft from being burnt and overheated in a pneumatic heating environment.
The heat protection system needs to have multiple functions of temperature resistance, heat insulation, bearing and the like, so a high-temperature-resistant heat insulation component with a sandwich structure, namely a high-temperature-resistant heat insulation sandwich material component, is generally adopted. At present, the research on the high-temperature resistant heat-insulating sandwich material member mainly focuses on the material and the integrated preparation technology of each layer in the sandwich structure.
For example, CN201320526457.7 discloses a high-temperature resistant integrated rigid thermal insulation member comprising: a rigid fibrous insulation layer; an aerogel permeable layer impregnated into the rigid fibrous insulation layer; a fibrous fabric panel reinforcement layer on at least one side of the rigid fibrous insulation layer, wherein the rigid fibrous insulation layer and the fibrous fabric panel reinforcement layer are sewn together by sewing a fiber thread, but this patent does not disclose a final edge cutting process.
However, the high temperature resistant heat insulation sandwich material member is generally assembled outside the aircraft cabin body, and a plurality of members need to be spliced together when in use, so that the requirements on the inner and outer profiles and the peripheral profile precision of a single member are very high. On the other hand, since the member is made of the interlayer, the manufacturing process involves not only the step of preparing each layer but also the step of integrating each layer, and the performance or contour of the edge portion of the green body obtained by integration often cannot satisfy the use requirements, and therefore, the edge of the green body needs to be further processed.
As described above, the current research is mainly focused on the properties of the respective layers and the technology of integrating the respective layers, and few researches are conducted on the processing technology for improving the accuracy of the contour of the high-temperature resistant heat insulating sandwich structure. If the existing processing mode, such as a lathe or a milling machine, is adopted, the problems that the positioning precision is low, the automation degree is not high, the edge state of the processed component is not good, the production and preparation progress of the component is influenced, even a part of the component with a special shape cannot be processed and the like exist.
Therefore, a processing method for ensuring and improving the shape and precision of the high-temperature resistant heat insulation sandwich material member and improving the processing efficiency is highly required. The processing method of the sandwich material member has the characteristics or difficulties of how to utilize high-precision positioning reference to ensure the processing precision and how to ensure that the sandwich material structure integrating different materials is processed to ensure that the edge state of the sandwich material member meets the use requirement.
Disclosure of Invention
In order to solve one or more of the above problems, the present invention provides a method of processing a sandwich structure, in particular a sandwich material member, such as a high temperature resistant insulation material.
Specifically, the invention is realized by the following technical scheme:
1. a method of machining a multi-component green body of a high temperature resistant heat insulating sandwich material, the method comprising the steps of:
(1) placing the component material blank in a processing tool;
(2) positioning the component material blank by using the positioning features;
(3) fixing the positioned component material blank;
(4) performing edge cutting processing on the component material blank to obtain an edge cutting processed component;
(5) further cutting the edge cutting process member into a plurality of the multilayer members by a dividing process;
wherein the component material blank has a heterogeneous layer structure and comprises a plurality of multilayer components, and the edge cutting process and/or the dividing process is performed by means of a machine tool.
2. The method of claim 1, wherein the heterostructure is a heterostructure having at least 3 layers; preferably, the outer two layers and at least one inner core layer in the heterostructure have hardness heterogeneity and/or brittleness heterogeneity.
3. According to the method of claim 1, the heterostructure is a three-layer sandwich heterostructure having an upper layer, a core layer and a lower layer; it is further preferred that the heterostructure consists of an upper, a core and a lower ply, and that the core material is a semi-flexible material and the upper and/or lower ply material is a brittle material with respect to the panel and core layers.
4. According to the method of claim 1, the error of the edge cutting process and/or the dividing process is not more than 0.4%.
5. According to the method of any one of claims 1 to 4, the machining tool is a clamping type machining tool, and the fixing is realized by a clamp.
6. According to the method of any one of claims 1 to 4, the positioning features comprise profile positioning features and/or positioning datum features on the machining tool and matched with the sandwich material members; and/or a locating member located on the blank of component material in alignment with the location of the locating datum feature.
7. According to the method of any one of claims 1 to 4, the positioning member comprises a ceramic column having a high temperature resistance not lower than a green body preparation temperature; and/or the profile-locating feature comprises a peripheral mating profile-locating feature having a mating fit with the sandwich material member.
8. The method according to any of claims 1-4, wherein the sandwich material member has a flat surface and/or the sandwich material member has a non-flat profiled surface.
9. The method according to any one of claims 1 to 4, wherein the sandwich material member has high temperature resistance, heat insulation and load bearing properties; preferably, the upper limit of the service temperature of the sandwich material member is 1000-1200 ℃; the heat conductivity coefficient at room temperature is less than or equal to 0.05W/m.K; the compressive strength is more than 1 MPa; and/or strain performance > 2000 μ; more preferably, the sandwich material element is used for forming a thermal protection structure outside the cabin of the hypersonic aircraft by splicing.
10. The method according to any one of claims 1 to 4, wherein the machine tool is a lathe or a milling machine.
The method of the invention has the following advantages:
(1) the sandwich structure processed by the method, such as the high-temperature resistant heat insulation sandwich material member, has higher precision of the inner and outer profiles and the surrounding profiles, and reduces the loss caused by the member failing to meet the use requirement. In particular, in some embodiments, the present invention can ensure positioning accuracy by utilizing profile positioning features and positioning reference features, such as peripheral mating profile positioning features and/or positioning reference features, such as positioning surfaces, positioning holes, positioning pins or posts, and/or by introducing positioning elements that do not change during the material preparation process, such as high temperature resistant dense ceramic posts.
(2) In some embodiments, the present invention utilizes the mold surface attaching and positioning features and/or positioning reference features (such as positioning surfaces, positioning holes, positioning pins, positioning nails, or positioning posts), the random mold tire, the three-dimensional theoretical model, the fixture to fix the random mold tire, and the clamping type processing tool, such as the upper and lower clamping type processing tools, to process the random mold tire, so as to remove the excess material, thereby achieving a high precision with an error not more than 0.4%.
(3) The method has high processing efficiency, can greatly shorten the preparation period of the component and save time and cost. The clamping type machining tool is simple and convenient to clamp, fix and operate, so that the efficiency is high, the time is saved, the precision is high, the rejection rate is low, the waste can be reduced, and the cost is saved.
(4) The method is simple, is easy and convenient to operate and has little pollution to the environment;
(5) the method can be used for processing components with various shapes and specifications, such as flat components or special-shaped components, and is particularly suitable for various special-shaped components with complex profiles.
Drawings
FIG. 1 shows a diagrammatic view of a green material component being machined using an up-down clamp type machining tool.
Figure 2 shows a representation of a single blank of material comprising a plurality (4 in the figure) of sandwich material members.
FIG. 3 is a photograph of a cut surface of the material cut in example 1.
Fig. 4 is a photograph of a cut surface of a cutting process employed in the prior art.
In the figure: 13: a green body; 14: an upper clamping member; 15 lower clamping piece; 16: and (5) an upper clamping type processing tool and a lower clamping type processing tool.
Detailed Description
The invention provides a machine tool processing method of a high-temperature resistant heat insulation sandwich material component, and the invention is further explained by combining with an embodiment. These embodiments are merely illustrative of the preferred embodiments of the present invention and the scope of the present invention should not be construed as being limited to these embodiments.
As described above, the present invention provides a machine tool processing method of a high temperature resistant heat insulation sandwich material member, the method comprising the steps of:
(1) placing the component material blank in a processing tool;
(2) positioning the component material blank by using the positioning features;
(3) fixing the positioned component material blank;
(4) performing edge cutting processing on the component material blank to obtain an edge cutting processed component;
(5) further cutting the edge cutting process member into a plurality of the multilayer members by a dividing process;
wherein the component material blank has a heterogeneous layer structure and comprises a plurality of multilayer components, and the edge cutting process and/or the dividing process is performed by means of a machine tool.
Heterostructure
In some embodiments, the heterostructure is a heterostructure having at least 2 layers, more preferably at least 3 layers, for example, can be 3 to 5 layers (e.g., 3, 4, or 5 layers), or can have more intervening heterostructure layers.
In the heterogeneous layer structure, the outer two layers and the at least one inner core layer preferably have hardness heterogeneity (hardness is different). In other embodiments, the outer two layers and the at least one inner core layer preferably have a brittle heterogeneity (brittleness or toughness is not the same); in more preferred embodiments, the outer two layers and the at least one inner core layer have hardness heterogeneity and brittleness heterogeneity. The hardness and/or brittleness of the outer two layers may be the same or different.
In some preferred embodiments, the heterostructure has 3 layers. For example, the heterostructure is a three-layer sandwich heterostructure having an upper layer, a core layer, and a lower layer.
In some embodiments, the heterolayer structure is comprised of an upper sheet layer, a core layer, and a lower sheet layer, and the core layer material is a semi-flexible material, and the upper sheet layer material and/or the lower sheet layer material is a brittle material, relative to the panel layer and the core layer. More preferably, the upper and lower plies are both of a brittle material relative to the core. However, the materials of the upper and lower cover sheets may be the same or different.
In a more specific embodiment, the sandwich material element is a typical three-layer sandwich structural element for thermal protection of the exterior of the cabin of a hypersonic aircraft. The upper plate layer and the lower plate layer of the three-layer sandwich structure are composed of high-temperature-resistant ceramic fibers, are generally obtained by compounding a fiber preform with a three-dimensional woven structure and a high-temperature-resistant sol precursor, have high rigidity and have good high-temperature resistance and high-speed airflow scouring resistance; the middle core layer is made of high-temperature resistant aerogel, is generally obtained by compounding a flexible high-temperature resistant fiber preform and an aerogel sol precursor, and has certain flexibility and better heat insulation performance. A blank having such a structure is difficult to prepare in one step due to the large difference in the properties at the edge positions from those at the middle portion, and each layer contains reinforcing fibers but has a significant difference in flexibility, which is particularly difficult when performing edge cutting processing.
Component
The component is obtained by processing a blank of the material component. More specifically, in the present invention, the edge-cut-processed member includes a plurality of sandwich material members, that is, a blank for obtaining the edge-cut-processed member through the edge-cut process is a multi-member blank. For example, the edge cutting processing member may have at least 2, at least 3, or at least 4 sandwich material members. For example, there may be 2, 3, 4, 5, 6, 7, 8, 9, 10, 15 or 20 or even more sandwich material members.
In some embodiments, the sandwich material member has a flat surface. In other embodiments, the sandwich material member has a non-flat profiled surface.
In some preferred embodiments, the sandwich material member has high temperature resistance, thermal insulation and/or load bearing properties, preferably high temperature resistance, thermal insulation and load bearing properties. In some embodiments, the sandwich material member has an upper use temperature limit of 1000 to 1200 ℃; the heat conductivity coefficient at room temperature is less than or equal to 0.05W/m.K; the compressive strength is more than 1 MPa; and/or strain performance > 2000 mu.
In some more preferred embodiments, the sandwich material member is used to form a thermal protection structure outside the cabin of the hypersonic aircraft by splicing.
As mentioned above, the ultra-high speed aircrafts require a thermal protection structure with both temperature-resistant, heat-insulating and load-bearing functions to avoid burnout and overheating in a pneumatic heating environment, and such a structure (hereinafter referred to as a high temperature-resistant heat-insulating sandwich structure) generally has a structure of at least three layers, which generally includes two outer layers and at least one inner core layer. The core layer is typically made of a relatively flexible, e.g., semi-flexible, material that is both temperature resistant and thermally insulating. The outer two layers may be the same or different materials and are typically made of a material having a high degree of brittleness and hardness to provide load bearing functionality. For example, the refractory heat insulating sandwich structure may have a sandwich-like three-layer structure.
Due to the sandwich structure, the manufacturing process not only involves the preparation process of each layer, but also involves the process of integrating each layer. Because the sandwich structure has the problem of non-uniform material properties of each layer, the sandwich structure is obviously different from a homogeneous material member in preparation and processing, and the problem of deformation matching needs to be considered in the aspect of preparation, which has an influence on the final profile precision of a product. The sandwich structure is mainly characterized in that the performance difference between the core layer material and the upper and lower panel materials is large in processing, the core layer material is a semi-flexible material, the panel material is a brittle material, and the sandwich structure is processed at the same time basically in one step in processing. Therefore, the performance or profile of the edge portion of the blank obtained after the integration of such a sandwich structure often cannot meet the use requirements, and further processing of the edge is required. If the traditional processing mode, such as a lathe, a milling machine and the like, is adopted, the problems of low positioning precision and poor edge state of the processed component (as shown in figure 4) exist. On the other hand, such a structure for fitting outside the cabin of a hypersonic aircraft requires, in use, a plurality of structures to be joined together, so that the requirements on the precision of the inner and outer profiles and the peripheral profile of the individual sandwich insulation structure are very high. Therefore, it is necessary to machine such a member with high accuracy. The machining accuracy and difficulty of such components is significantly increased because of the heterogeneity of the layers and the high performance requirements due to the high precision of the profiles and edge profiles required for splicing and the application.
In some preferred embodiments, the blank has a locating feature. In the case that the sandwich material member is a high temperature resistant heat insulation sandwich structure, the positioning member may be, for example, a ceramic column having a high temperature resistance not lower than the green body preparation temperature, such as a high temperature resistant dense ceramic column, which is used for precise positioning on a machining tool, thereby ensuring the machining accuracy.
Processing tool
As known to those skilled in the art, a tool is an abbreviation of a processing device, and a processing tool is a processing device for processing. In the invention, the processing tool is mainly used for positioning, fixing and cutting or dividing the component material blank to be processed or the edge cutting processing component subjected to edge cutting processing. In some embodiments, the processing tool may be a clamping-type processing tool. The clamping type processing tool can be an up-and-down clamping type processing tool, a front-and-back clamping type processing tool or a left-and-right clamping type processing tool. If the clamping type machining work is adopted, an upper clamping type machining tool and a lower clamping type machining tool are preferably used.
One skilled in the art understands that the clamping type machining and assembling tool can be provided with a profile matched and attached with the related component, and can only comprise one side profile; positioning reference features for determining the relative position of the component, such as a positioning surface, a positioning hole, a positioning pin, a positioning post, a positioning pile or a positioning nail, and the like; and a machining tool locating feature included in itself that can locate a machining tool, which may be, for example, a datum profile, such as any sharp corner comprising three mutually perpendicular faces.
In addition, the clamping type processing tool can comprise a profile positioning feature which is matched and attached with at least two opposite profiles of the component; a positioning reference feature for determining the relative position of the member; and a tool or a tool for fixing the upper clamping tool and the lower clamping tool.
The clamp type tooling may have various locating features for positioning, such as point locating features (e.g., spuds), line locating features, or profile locating features (e.g., perimeter mating profile locating features) to improve the accuracy of the positioning. In addition, the clamping type machining tool can further comprise a clamp used for fixing the blank or the component.
Mode of processing
The invention can be processed by a machining method by a machine tool, for example, the edge cutting machining or the dividing machining can be processed by the machining method. In some embodiments, the machining mode is performed by a conformal mold and a three-dimensional theoretical model. Specifically, firstly, the component can be precisely fitted and fixed on the mould by using the positioning datum and the moulding surface matched with the component and the conformal mould, and the component and the mould can be regarded as a whole at the moment; then, positioning and aligning are carried out on a machine tool by utilizing a positioning datum plane contained in the mould tire, generally, a coordinate origin is determined, and the coordinate origin can be processed after being matched with the coordinate of a three-dimensional theoretical model (the state of a component after being attached to the mould tire).
In some embodiments, the machine tool is a manually operated machine tool, such as a lathe or milling machine, which may be used for edge cutting machining. The manual operation processing is simple and easy to implement, the processing cost is low, and the method is particularly suitable for processing the condition that the number of the components with the same specification is small. By adopting the method, the edge cutting processing is carried out on the multi-component blank in a machine tool processing mode, and the precision error can reach not more than 0.4%.
In some particularly preferred embodiments, positioning features, particularly profile positioning features (large area alignment and protection of the blank surface from damage during machining) on the machining tool and positioning elements on the blank can be used for positioning and fixing by means of a clamp, which can significantly improve machining accuracy. Thus, in some embodiments, the error of the edge cutting process and/or the separating process is not more than 0.4%, such as not more than 0.4, 0.3, 0.2 or 0.1%, preferably not more than 0.05%, so as to sufficiently satisfy the high requirements of the high temperature resistant and heat insulating sandwich structure as a heat protection structure for splicing and forming an outer cabin of a hypersonic aircraft.
The invention will be further explained with reference to the drawings.
FIG. 1 shows a diagrammatic view of a green material component being machined using an up-down clamp type machining tool. Clamping the blank body 13 between an upper clamping piece 14 and a lower clamping piece 15 of an upper and lower clamping type machining tool 16, attaching the lower surface of the upper clamping piece 14 to the upper surface of the blank body 13, attaching the upper surface of the lower clamping piece 15 to the lower surface of the blank body 13, and then performing edge cutting machining. The upper and/or lower clamps 14, 15 have a profile that conforms to the sandwich material member and that may cover most or all of the surface of the sandwich material member, thereby reducing or eliminating damage to the surface of the member during processing, which is important for high temperature resistant, thermally insulating sandwich structures for ultra-high pitch aircraft where the surface needs careful protection.
Figure 2 shows a representation of a single blank of material comprising a plurality (4 in the figure) of sandwich material members. As shown in fig. 2, a single blank 23 includes 4 (which may be less than or greater than 4) members 24, wherein the 4 members may be the same or different in shape and size, but preferably at least two of the members have at least one edge aligned, which may improve the efficiency of the edge finishing. Moreover, the main advantages of preparing a plurality of components by a single blank body are that the production efficiency is improved, the time for preparing the blank body can be greatly saved, and in addition, the uniformity of the performance of the components (namely, the stability of the product quality) can be improved to a certain extent due to one-time preparation of the blank body.
Examples
The present invention is further illustrated by the following examples, which are provided for illustrative purposes only and are not intended to limit the scope of the present invention.
Example 1
Processing a multi-component material (comprising 4 sandwich structures) with a three-layer structure of an upper plate layer, a lower plate layer and a core layer by a manual milling machine, wherein each layer of material is shown in table 1, and the upper plate layer and the lower plate layer are obtained by compounding a fiber preform with a three-dimensional woven structure and a high-temperature resistant sol precursor (aluminum oxide); the middle core layer is obtained by compounding a flexible high-temperature-resistant fiber preform and an aerogel sol precursor (aluminum oxide). As shown in fig. 1, a component material blank including 4 sandwich material components is placed in an upper and lower clamping type processing tool; then positioning the component material blank by utilizing the positioning characteristics; fixing the positioned component material blank; the member material blank is subjected to an edge cutting process to obtain an edge-cut processed member whose edge is subjected to a cutting process, and then the edge-cut processed member is divided into four finally obtained members (see fig. 1 and 2). The machining accuracy error, temperature resistance and strain property are shown in the following table 1. The photograph of the cut surface of the cutting process is shown in FIG. 3.
Example 2
Processing a single-component material with a three-layer structure of an upper plate layer, a lower plate layer and a core layer by a manual milling machine, wherein the material diagram of each layer is shown as a material diagram 1, and the upper plate layer and the lower plate layer are obtained by compounding a fiber preform with a three-dimensional woven structure and a high-temperature-resistant sol precursor (mullite); the middle core layer is obtained by compounding a flexible high-temperature-resistant fiber preform and an aerogel sol precursor (mullite). As shown in fig. 1, a component material blank including 4 sandwich material components is placed in an upper and lower clamping type processing tool; then positioning the component material blank by utilizing the positioning characteristics; fixing the positioned component material blank; the member material blank is subjected to an edge cutting process to obtain an edge-cut processed member whose edge is subjected to a cutting process, and then the edge-cut processed member is divided into four finally obtained members (see fig. 1 and 2). The machining accuracy errors are shown in table 1 below.
Comparative example 1
The green body of the member material used in example 1 was machined in a conventional cutting machining manner, specifically, an edge profile of the member to be obtained was measured and drawn from the green body in accordance with the size of the sandwich structure to be obtained, and then cutting machining was performed along the drawn profile line by a manual milling machine. The machining accuracy errors are shown in table 1 below.
Table 1 shows the blank materials, the processing precision error, the temperature resistance and the strain property in the examples
"-" indicates no measurement.
Claims (7)
1. A machine tool processing method of a multi-component green body of a high-temperature resistant heat insulation sandwich material, which is characterized by comprising the following steps:
(1) placing the component material blank in a processing tool;
(2) positioning the component material blank by using the positioning features;
(3) fixing the positioned component material blank;
(4) performing edge cutting processing on the component material blank to obtain an edge cutting processed component;
(5) further cutting the edge cutting process member into a plurality of multilayer members by a dividing process;
the component material blank has a heterogeneous layer structure and comprises a plurality of multilayer components, the edge cutting and/or dividing processing is carried out in a machine tool processing mode, the error of the edge cutting and/or dividing processing is not more than 0.4%, and the upper limit of the service temperature of the sandwich material component is 1000-1200 ℃; the heat conductivity coefficient at room temperature is less than or equal to 0.05W/m.K; the compressive strength is more than 1 MPa; and/or strain performance > 2000 μ;
the positioning features comprise profile positioning features and positioning reference features which are positioned on the processing tool and matched and attached with the interlayer material member; and a locating member located on the component material blank in registration with the location of the locating datum feature;
the positioning piece comprises a ceramic column with high temperature resistance not lower than the preparation temperature of the blank body; the profile locating features comprise peripheral mating profile locating features in mating engagement with the sandwich material members;
the heterogeneous layer structure is a three-layer sandwich heterogeneous layer structure with an upper layer, a core layer and a lower layer;
the heterogeneous layer structure is composed of an upper plate layer, a core layer and a lower plate layer, and relative to the panel layer and the core layer, the core layer is made of semi-flexible materials, and the upper plate layer material and/or the lower plate layer material are/is brittle materials;
the upper plate layer and the lower plate layer are both composed of ceramic fibers and are obtained by compounding a ceramic fiber preform and a sol precursor; the core layer is aerogel and is obtained by compounding a flexible fiber prefabricated body and an aerogel precursor.
2. The method of claim 1, wherein the machining tool is a clamp-type machining tool and the securing is accomplished by a clamp.
3. A method according to claim 1, characterised in that the sandwich material element has a flat surface and/or the sandwich material element has a non-flat profiled surface.
4. The method of claim 1, wherein:
the sandwich material member has high temperature resistance, heat insulation performance and bearing performance.
5. The method of claim 4, wherein:
the sandwich material member is used for forming a thermal protection structure outside a cabin body of the hypersonic aircraft through splicing.
6. The method of claim 1, wherein the machine tool is a lathe or a milling machine.
7. The method of claim 1, wherein:
the outer two layers and at least one inner core layer in the heterostructure have hardness heterogeneity and/or brittleness heterogeneity.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710121140.8A CN108526491B (en) | 2017-03-02 | 2017-03-02 | Machine tool machining method for multi-component blank body of high-temperature-resistant heat-insulation sandwich material |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710121140.8A CN108526491B (en) | 2017-03-02 | 2017-03-02 | Machine tool machining method for multi-component blank body of high-temperature-resistant heat-insulation sandwich material |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108526491A CN108526491A (en) | 2018-09-14 |
| CN108526491B true CN108526491B (en) | 2020-08-07 |
Family
ID=63489223
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710121140.8A Active CN108526491B (en) | 2017-03-02 | 2017-03-02 | Machine tool machining method for multi-component blank body of high-temperature-resistant heat-insulation sandwich material |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108526491B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111559746B (en) * | 2020-05-25 | 2021-12-14 | 航天特种材料及工艺技术研究所 | Processing method of flexible ultra-low density aerogel composite material |
| CN115159954B (en) * | 2022-07-15 | 2023-05-09 | 航天特种材料及工艺技术研究所 | Aerogel heat insulation layer and preparation method thereof |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4790221A (en) * | 1986-02-01 | 1988-12-13 | Akebono Brake Industry Co., Ltd. | Method of machining a brake caliper |
| CN103411098A (en) * | 2013-08-28 | 2013-11-27 | 航天特种材料及工艺技术研究所 | Integrated high-temperature-resistant rigid heat insulation component and production method thereof |
| CN104529384A (en) * | 2014-12-16 | 2015-04-22 | 山东工业陶瓷研究设计院有限公司 | Aerogel irregular part and preparation method thereof |
| CN104959565A (en) * | 2015-05-26 | 2015-10-07 | 深圳市中联讯科技有限公司 | Zinc alloy mobile phone middle frame manufacturing process |
| CN105817842A (en) * | 2016-01-13 | 2016-08-03 | 广东工业大学 | Diamond tool with gradient and multilayered structure and preparation method of diamond tool |
-
2017
- 2017-03-02 CN CN201710121140.8A patent/CN108526491B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4790221A (en) * | 1986-02-01 | 1988-12-13 | Akebono Brake Industry Co., Ltd. | Method of machining a brake caliper |
| CN103411098A (en) * | 2013-08-28 | 2013-11-27 | 航天特种材料及工艺技术研究所 | Integrated high-temperature-resistant rigid heat insulation component and production method thereof |
| CN104529384A (en) * | 2014-12-16 | 2015-04-22 | 山东工业陶瓷研究设计院有限公司 | Aerogel irregular part and preparation method thereof |
| CN104959565A (en) * | 2015-05-26 | 2015-10-07 | 深圳市中联讯科技有限公司 | Zinc alloy mobile phone middle frame manufacturing process |
| CN105817842A (en) * | 2016-01-13 | 2016-08-03 | 广东工业大学 | Diamond tool with gradient and multilayered structure and preparation method of diamond tool |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108526491A (en) | 2018-09-14 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106826337B (en) | A kind of numerical-control processing method of high temperature resistant heat insulation sandwich material component | |
| CN106808247B (en) | A kind of machine tooling method of high temperature resistant heat insulation sandwich material component | |
| US20170274577A1 (en) | Composite structures with stiffeners and method of making the same | |
| US9782958B2 (en) | Method and device for manufacturing composite material parts | |
| US6168358B1 (en) | Hybrid lay-up tool | |
| CN108526491B (en) | Machine tool machining method for multi-component blank body of high-temperature-resistant heat-insulation sandwich material | |
| EP1817155B1 (en) | Flexible mandrel for highly contoured composite stringer and method of producing highly contoured composite stringer | |
| EP1972426B1 (en) | Method and tools for producing ring frames from a composite material | |
| JP2010510111A (en) | Apparatus and method for forming a hat-reinforced composite part using a thermal expansion tooling call | |
| CN111572053B (en) | Processing method of composite material test sample strip | |
| CN108274767B (en) | Sewing mold and method for strip-shaped composite material preformed body | |
| CN108527677B (en) | numerical control machining method for multi-component blank body of high-temperature-resistant heat-insulation interlayer material | |
| CN112067400A (en) | Device and method for preparing tensile and compressive sample of three-dimensional textile composite material | |
| CN112267917A (en) | Fiber preform and ceramic matrix composite turbine outer ring | |
| CN211467534U (en) | Integrated positioning device for composite material reinforcement structure | |
| CN111716761A (en) | Special-shaped curved surface aramid fiber paper honeycomb simple pre-setting die and manufacturing method thereof | |
| CN111039687A (en) | Damage-free hole making method for continuous fiber reinforced ceramic matrix composite | |
| JP5610881B2 (en) | Composite material mold and manufacturing method thereof | |
| EP3390020B1 (en) | Impregnated veils | |
| KR102274173B1 (en) | Co curing method of composite material through reinforcement and its composite material | |
| CN101979229A (en) | Method for flexibly clamping fragile composite ceramic material | |
| US20130292861A1 (en) | Composite material part manufacturing process using removable and retainable material | |
| CN113953772A (en) | Machining method for casting special-shaped mounting edge of cone ring block | |
| WO2016100081A1 (en) | Composite laminate tooling and method of forming a composite part using the tooling | |
| CN214533085U (en) | Aeroengine spoiler |
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 |