CN108527677B - numerical control machining method for multi-component blank body of high-temperature-resistant heat-insulation interlayer material - Google Patents

numerical control machining method for multi-component blank body of high-temperature-resistant heat-insulation interlayer material Download PDF

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Publication number
CN108527677B
CN108527677B CN201710121128.7A CN201710121128A CN108527677B CN 108527677 B CN108527677 B CN 108527677B CN 201710121128 A CN201710121128 A CN 201710121128A CN 108527677 B CN108527677 B CN 108527677B
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blank
component
positioning
sandwich
processing
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CN108527677A (en
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宋寒
苏力军
李文静
刘云龙
曹杰
李晶
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Aerospace Research Institute of Special Materials and Processing Technology
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Aerospace Research Institute of Special Materials and Processing Technology
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    • BPERFORMING OPERATIONS; TRANSPORTING
    • B28WORKING CEMENT, CLAY, OR STONE
    • B28DWORKING STONE OR STONE-LIKE MATERIALS
    • B28D1/00Working stone or stone-like materials, e.g. brick, concrete or glass, not provided for elsewhere; Machines, devices, tools therefor
    • B28D1/22Working stone or stone-like materials, e.g. brick, concrete or glass, not provided for elsewhere; Machines, devices, tools therefor by cutting, e.g. incising
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B28WORKING CEMENT, CLAY, OR STONE
    • B28DWORKING STONE OR STONE-LIKE MATERIALS
    • B28D7/00Accessories specially adapted for use with machines or devices of the preceding groups
    • B28D7/04Accessories specially adapted for use with machines or devices of the preceding groups for supporting or holding work or conveying or discharging work
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B28WORKING CEMENT, CLAY, OR STONE
    • B28DWORKING STONE OR STONE-LIKE MATERIALS
    • B28D7/00Accessories specially adapted for use with machines or devices of the preceding groups
    • B28D7/04Accessories specially adapted for use with machines or devices of the preceding groups for supporting or holding work or conveying or discharging work
    • B28D7/046Accessories specially adapted for use with machines or devices of the preceding groups for supporting or holding work or conveying or discharging work the supporting or holding device being of the vacuum type
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16LPIPES; JOINTS OR FITTINGS FOR PIPES; SUPPORTS FOR PIPES, CABLES OR PROTECTIVE TUBING; MEANS FOR THERMAL INSULATION IN GENERAL
    • F16L59/00Thermal insulation in general
    • F16L59/02Shape or form of insulating materials, with or without coverings integral with the insulating materials
    • F16L59/029Shape or form of insulating materials, with or without coverings integral with the insulating materials layered

Abstract

The invention provides a numerical control processing method of a multi-component blank body of a high-temperature-resistant heat-insulating interlayer 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-cut processed member into a plurality of the above-mentioned multilayer members by a dividing process; wherein the green body of component material has a heterogeneous layer structure. The method is quick, and can greatly improve the processing precision, the processing efficiency and the quality stability of the component.

Description

Numerical control machining method for multi-component blank body of high-temperature-resistant heat-insulation interlayer material
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 numerical control processing method of a multi-component blank body of a high-temperature-resistant heat-insulating sandwich material 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 the multilayer members by a dividing process;
Wherein the component material blank has a heterogeneous layer structure and comprises a plurality of sandwich components, and the edge cutting process and/or the segmentation process is performed by means of a numerical control process.
2. The method of claim 1, wherein the heterostructure is a heterostructure having at least 3 layers; more preferably, the heterostructure is composed 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.
3. The method according to claim 1 or 2, wherein the error of the edge cutting process is not more than 0.2%.
4. According to the method of any one of the technical schemes 1 to 3, the processing tool is a conformal processing tool; more preferably, the fixation is achieved by vacuum suction.
5. The method according to any one of claims 1 to 4, wherein: the positioning features comprise profile positioning features and/or positioning datum features which are positioned on the machining tool and matched and attached with the interlayer material members; and/or a positioning member positioned on the component material blank and aligned with the positioning datum feature; preferably, the positioning member comprises a ceramic post having a high temperature resistance not lower than the 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.
6. The method according to any of claims 1-5, wherein the sandwich material member has a flat surface and/or a non-flat profiled surface.
7. The method according to any one of claims 1 to 6, 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 a strain performance > 2000 mu epsilon; more preferably, the sandwich material element is used for forming a thermal protection structure outside the cabin of the hypersonic aircraft by splicing.
8. the method according to any one of claims 1 to 7, wherein an error of the dividing process is not more than 0.2%.
9. According to the method of any one of claims 1 to 8, the numerical control machining is performed by a form-following mold and a three-dimensional theoretical model.
10. the method according to any of claims 1 to 9, wherein the outer two layers and at least one inner core layer of the heterostructure have hardness heterogeneity and/or brittleness heterogeneity; preferably, the heterostructure is a three-layer sandwich heterostructure having an upper layer, a core layer and a lower layer.
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 invention uses a numerical control machine tool to process, uses the mold surface attaching and positioning features and/or positioning reference features (such as positioning surfaces, positioning holes, positioning pins, positioning nails or positioning columns), mold following tires and three-dimensional theoretical models to process, uses a clamp and/or vacuum negative pressure to adsorb and fix, and processes through a processing tool to remove the redundant materials, thereby achieving the high precision with the error not more than 0.2%.
(3) The method has high processing efficiency, can greatly shorten the preparation period of the component and save time and cost. The numerical control machining is high in automation degree, time is saved, precision is high, rejection rate is low, waste can be reduced, and 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 schematic representation of machining a component material blank using a form following tooling.
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: 11: machining a tool along with the shape; 12: a shape following adjusting nut; 13: a green body; 14: a member; 15: a positioning member; 16: positioning the pile; 17: a profile locating feature.
Detailed Description
The invention provides a numerical control processing method of a multi-component blank of a high-temperature-resistant heat-insulating interlayer material, and the invention is further explained by combining 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 mentioned above, the invention provides a numerical control processing method of a multi-component blank 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 the multilayer members by a dividing process;
Wherein the component material blank has a heterogeneous layer structure and comprises a plurality of sandwich components, and the edge cutting process and/or the segmentation process is performed by means of a numerical control process.
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 a strain performance > 2000 mu epsilon.
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 conformal processing tool
the shape following machining tool has a profile matched and attached with a related component, and can only comprise a profile on one side; 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 tool locating feature that itself includes to locate a tool, which may be, for example, a datum profile, such as any one of the sharp corners in figure 1 that includes three mutually perpendicular faces.
The form following tooling may have various positioning features for positioning, such as point positioning features (e.g., spuds), line positioning features (e.g., form following tooling edges), or profile positioning features (e.g., perimeter mating profile positioning features) to improve positioning accuracy.
The shape following processing tool can comprise a clamp for fixing a green body or a component, and can also alternatively or further comprise a vacuum negative pressure device, and for example, because the tool profile is tightly attached to the component profile, vacuum negative pressure can be provided by the negative pressure providing device, so that the green body or the component to be processed is fixed or further fixed by vacuum negative pressure adsorption.
Mode of processing
The invention can adopt a numerical control machine tool to process in a numerical control processing mode, for example, the edge cutting processing or the dividing processing can be carried out in the numerical control processing mode, thereby improving the automation degree and the consistency of the component specification. In some embodiments, the numerical control machining mode is performed through 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 alignment are carried out on a numerical control machine tool by utilizing a positioning reference surface contained in the mold, 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 mold). In the case where the cost is allowable and the number of machining is high and particularly high precision is required, the numerical control machining method is preferably adopted. By adopting the method of the invention, the precision error of the edge cutting processing or the dividing processing can reach not more than 0.2 percent.
In some particularly preferred embodiments, the positioning features, especially the profile positioning features (large-area alignment and protection of the surface of the blank from damage during machining) on the machining tool and the positioning elements on the blank can be used for positioning, and the fixture and vacuum negative pressure adsorption are used for fixing, so that the machining precision can be remarkably improved. 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 schematic representation of machining a component material blank using a form following tooling. As shown in fig. 1, a blank 13 is placed on a conformal machining tool 11, is positioned by means of a positioning piece 15, a positioning pile 16 and a profile positioning feature 17, is conformal-adjusted and fixed by a conformal adjusting nut 12, and is then subjected to edge cutting machining by a cutter to obtain a component 14. In some embodiments, further fixation and cutting or separating operations may optionally be performed using a vacuum negative pressure device (not shown).
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 using a numerical control machine tool in a numerical control processing mode, wherein each layer of material is shown in a graph 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 (silicon dioxide); the middle core layer is obtained by compounding a flexible high-temperature-resistant fiber preform and an aerogel sol precursor (silicon dioxide). As shown in fig. 1, a component material blank including 4 sandwich material components is firstly placed in a shape following processing tool; then positioning the component material blank by utilizing the positioning characteristics; adjusting a conformal adjusting nut, and 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 and temperature resistance are shown in table 1 below. The photograph of the cut surface of the cutting process is shown in FIG. 3.
example 2
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 using a numerical control machine tool in a numerical control processing mode, wherein each layer of material is shown in a graph 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 firstly placed in a shape following processing tool; then positioning the component material blank by utilizing the positioning characteristics; adjusting a conformal adjusting nut, and fixing the positioned component material blank; the edge-cut processing is performed on the member material blank to obtain an edge-cut processed member whose edge is subjected to the cutting processing, and then the edge-cut processed member is divided into four finally-obtained members to thereby divide the edge-cut processed member whose edge is subjected to the cutting processing 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.
Comparative example 1
The green body of the member material used in example 2 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 blank material and machining accuracy errors in examples
"-" indicates no measurement.

Claims (6)

1. A numerical control processing method of a multi-component green body of a high-temperature-resistant heat-insulation sandwich material is characterized in that a plurality of sandwich material components are prepared from a single green body material and are used for forming a heat protection structure outside a cabin body of an hypersonic aircraft through splicing, and the numerical control processing method comprises the following steps:
(1) Placing a single blank material serving as a component material blank in a processing tool, wherein the processing tool is a shape following processing tool serving as a shape following mould;
(2) Positioning the component material blank by utilizing the positioning characteristics, so that the component material blank is attached and fixed on the shape following processing tool;
(3) regarding the positioned component material blank and the conformal machining tool as a whole, positioning and aligning on a numerical control machine tool by utilizing a positioning datum plane contained in the conformal machining tool, determining an original point of coordinates, and fixing the whole to match the original point of coordinates with coordinates of a three-dimensional theoretical model representing a state after the component material blank and the conformal machining tool are attached;
(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 sandwich material members by a dividing process;
Wherein a single blank material as the member material blank has a heterogeneous layer structure and comprises a plurality of sandwich material members, and the edge cutting process and the dividing process are performed by means of a numerical control process; the heterogeneous layer structure is a heterogeneous layer structure with 3 layers, the heterogeneous layer structure is composed of an upper plate layer, a core layer and a lower plate layer, the core layer is made of a semi-flexible material, and the upper plate layer material and/or the lower plate layer material are/is a brittle material;
The positioning features comprise profile positioning features and/or positioning reference features which are positioned on the conformal machining tool and matched and attached with the interlayer material member; and/or a positioning member positioned on the component material blank and aligned with the positioning datum feature;
The locating piece comprises a ceramic column with high temperature resistance not lower than the preparation temperature of the blank body, and the profile locating feature comprises a peripheral matching profile locating feature matched and attached with the interlayer material member.
2. The method of claim 1, wherein the margin cut process has an error of no more than 0.2%.
3. the method of claim 1, wherein the fixing is achieved by vacuum suction.
4. A method according to any one of claims 1 to 3, characterised in that the sandwich material element has a flat surface and/or a non-flat profiled surface.
5. A method according to any one of claims 1 to 3, wherein the sandwich material member has high temperature resistance, thermal insulation and load-bearing properties;
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 a strain performance > 2000 mu epsilon.
6. the method of any one of claims 1 to 3, wherein the error of the segmentation process is not more than 0.2%.
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