CN106808247A - A kind of machine tooling method of high temperature resistant heat insulation sandwich material component - Google Patents

A kind of machine tooling method of high temperature resistant heat insulation sandwich material component Download PDF

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Publication number
CN106808247A
CN106808247A CN201710121671.7A CN201710121671A CN106808247A CN 106808247 A CN106808247 A CN 106808247A CN 201710121671 A CN201710121671 A CN 201710121671A CN 106808247 A CN106808247 A CN 106808247A
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China
Prior art keywords
sandwich
component
base substrate
processing
construction
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CN106808247B (en
Inventor
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
    • B23MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23QDETAILS, COMPONENTS, OR ACCESSORIES FOR MACHINE TOOLS, e.g. ARRANGEMENTS FOR COPYING OR CONTROLLING; MACHINE TOOLS IN GENERAL CHARACTERISED BY THE CONSTRUCTION OF PARTICULAR DETAILS OR COMPONENTS; COMBINATIONS OR ASSOCIATIONS OF METAL-WORKING MACHINES, NOT DIRECTED TO A PARTICULAR RESULT
    • B23Q3/00Devices holding, supporting, or positioning work or tools, of a kind normally removable from the machine
    • B23Q3/02Devices holding, supporting, or positioning work or tools, of a kind normally removable from the machine for mounting on a work-table, tool-slide, or analogous part
    • B23Q3/06Work-clamping means
    • B23Q3/062Work-clamping means adapted for holding workpieces having a special form or being made from a special material

Abstract

The invention provides a kind of machine tooling method of high temperature resistant heat insulation sandwich material component, methods described comprises the following steps:(1) construction material base substrate is placed in processing tool;(2) construction material base substrate is positioned using location feature;(3) the construction material base substrate having good positioning is fixed;(4) edge cuts processing is carried out to construction material base substrate, obtains edge cuts tooling member;Wherein, the construction material base substrate has heterogeneous Rotating fields, and edge cuts processing is carried out by machine tooling mode.The inventive method is simple, easy to operate, environmental pollution is small, can increase substantially component machining accuracy and processing efficiency, is mainly used in the fields such as aerospace industries, civilian industry.

Description

A kind of machine tooling method of high temperature resistant heat insulation sandwich material component
Technical field
The present invention relates to heat-barrier material technical field, specifically, the present invention relates to a kind of high temperature resistant heat insulation sandwich material The processing method of component.
Background technology
When long in atmosphere during high-performance cruise, aircraft will bear harsh air and heat to hypersonic aircraft Load is acted on.In order to ensure that aircraft contour structures are complete, internal component normal work is, it is necessary to have temperature-resistance thermal-insulation concurrently and hold The thermal protection system of function is carried to protect aircraft to avoid burning and overheating in Aerodynamic Heating environment.
Thermal protection system has various functions such as heatproof, heat-insulated and carrying concurrently due to needing, therefore general all using with folder The high temperature resistant heat insulation component of Rotating fields, i.e. high temperature resistant heat insulation sandwich material component.At present, high temperature resistant heat insulation sandwich material component It is standby technically that research is concentrated mainly on each layer integration system of the material and in sandwich in itself.
For example, CN201320526457.7 discloses a kind of high temperature resistant integrative rigidity heat insulating component, the high temperature resistant one Bodyization rigidity heat insulating component includes:Rigid fiber thermal insulation layer;Infiltrate into the aerogel infiltration layer in the rigid fiber thermal insulation layer; Fabric panel enhancement layer at least side of the rigid fiber thermal insulation layer, wherein will be described by staples line Rigid fiber thermal insulation layer and the fabric panel enhancement layer are sewed together, but the patent does not disclose last side Edge cutting process method.
However, high temperature resistant heat insulation sandwich material component is typically assemblied in outside aircraft nacelle, needing when in use will be more Individual component is stitched together, therefore is very high for the requirement of the interior outer mold surface and surrounding contour accuracy of single component.Separately On the one hand, component is directed not only to the preparation section of each layer due to being made up of interlayer, during manufacture, further relates to the work of each layer integration Sequence, the performance or appearance profile of the marginal portion of the base substrate obtained after integration cannot often meet use requirement, therefore need Green body edge is for further processing.
As described above, current research is concentrated mainly in layers of material performance and by the technology of each layer integration On, seldom study the process technology of the appearance profile precision for improving high temperature resistant heat insulation sandwich.If using existing Processing mode, such as lathe or milling machine mode, have that positioning precision is low, and automaticity is not high, process rear part rim condition Not good, progress prepared by influence component production, or even part has the component of specific shape the problems such as cannot process.
Hence it is highly desirable to a kind of profile and precision for ensureing and improving high temperature resistant heat insulation sandwich material component, carry The processing method of processing efficiency high.How the processing method feature or difficult point of this sandwich material component are using high-precision Positioning datum ensureing machining accuracy, and how to ensure to process sandwich material structure that heterogeneity material becomes one with Ensure that the rim condition of its sandwich material component meets use requirement.
The content of the invention
In order to solve one or more above mentioned problems, the invention provides a kind of sandwich in particular, for example high temperature resistant every The processing method of hot material sandwich material component.
Specifically, the present invention is realized by following technical solution:
1st, a kind of machine tooling method of high temperature resistant heat insulation sandwich material component, methods described comprises the following steps:
(1) construction material base substrate is placed in processing tool;
(2) construction material base substrate is positioned using location feature;
(3) the construction material base substrate having good positioning is fixed;
(4) edge cuts processing is carried out to construction material base substrate, obtains edge cuts tooling member;
Wherein, the construction material base substrate has heterogeneous Rotating fields, and edge cuts processing passes through machine tooling Mode is carried out.
2nd, the method according to technical scheme 1, the edge cuts manufacturing tolerance is no more than 0.3%.
3rd, the method according to technical scheme 1 or 2, the processing tool is clipping processing tool, and described solid It is fixed to be realized by fixture;Preferably, the location feature include on the processing tool with sandwich material The type face location feature and/or positioning datum feature of Components Matching laminating;And/or on construction material base substrate with positioning base The keeper of quasi- feature locations alignment;It is further preferred that the keeper is not less than body preparation temperature including heat-resisting quantity Ceramics pole;And/or type face location feature includes having the periphery fitting-type face positioning fitted with sandwich material Components Matching Feature.
4th, the method according to any one of technical scheme 1 to 3, the sandwich material component have flat surfaces and/ Or the sandwich material component has non-flat forms special-shaped surfaces.
5th, the method according to any one of technical scheme 1 to 4, the sandwich material component have resistance to elevated temperatures, Heat-proof quality and load-carrying properties;Preferably, the use temperature upper limit of the sandwich material component is 1000~1200 DEG C;Room temperature Thermal conductivity factor≤0.05W/mK;Compression strength > 1MPa;And/or the μ ε of strain property > 2000;It is further preferred that the interlayer Material members are used for the thermal protection structure by being spliced to form outside the nacelle of hypersonic aircraft.
6th, the method according to any one of technical scheme 1 to 5, the edge cuts tooling member includes multiple described Sandwich material component, and methods described is after step (4), and methods described also includes step (5):By division processing by institute State edge cuts tooling member and further cut into multiple sandwich material components;Preferably, the mistake of the division processing Difference is no more than 0.3%.
7th, the method according to any one of technical scheme 1 to 6, the edge cuts tooling member only includes an institute State sandwich material component.
8th, the method according to any one of technical scheme 1 to 7, the lathe is lathe or milling machine.
9th, the method according to any one of technical scheme 1 to 8, the heterogeneous Rotating fields are different with least 3 layers Matter Rotating fields;Preferably, the outer two layers in the heterogeneous Rotating fields have hardness heterogeneous with least one inner core layers And/or fragility is heterogeneous.
10th, the method according to any one of technical scheme 1 to 9, the heterogeneous Rotating fields be with upper strata, sandwich layer and The heterogeneous Rotating fields of three-layer sandwich of lower floor;It is further preferred that the heterogeneous Rotating fields are by flaggy above, sandwich layer and following flaggy structure Into, and relative to panel layer and sandwich layer each other for, core material be semi-flexible material, above cover sheet materials and/or below Cover sheet materials are fragile material.
The inventive method has the following advantages that:
(1) the interior outer mold surface and surrounding of the sandwich such as high temperature resistant heat insulation sandwich material component that this method processing is obtained Contour accuracy is higher, and reducing component cannot meet the loss that use requirement is caused.Especially in some embodiments, the present invention Using type face location feature and positioning datum feature, such as periphery fitting-type face location feature and/or positioning datum feature are as positioned Face, location hole, alignment pin, locating pin or locating dowel, and/or it is introduced into the keeper that change will not be produced in material preparation process Such as high temperature resistant ceramic of compact post, it is ensured that the precision of positioning.
(2) in some embodiments, the present invention is (such as fixed using type face laminating location feature and/or positioning datum feature Plane, location hole, alignment pin, locating pin or locating dowel), processed with pattern tire and three-dimensional DEM, fixed using fixture, lead to Cross clipping processing tool for example up and down clipping processing tool be processed, remove redundance material, can reach error ≯ 0.4% high accuracy even ≯ 0.3%.
(3) this method processing efficiency is higher, and component manufacturing cycle can be greatly shortened, and saves time cost.It is clipping Processing tool blessing fixation is easy to operate, therefore efficiency high, saves the time, and high precision, percent defective are low, can reduce wave Take, it is cost-effective.
(4) this method is simple, easy to operate, environmental pollution is small;
(5) this method is processed to the component of variously-shaped specification, such as planar plate members or special-shaped component, especially It is adapted to the complicated special-shaped component in various type faces, therefore is with a wide range of applications in the environment of aerospace industry.
Brief description of the drawings
Fig. 1 shows the diagram that blank of material component is processed using clipping processing tool up and down.
Fig. 2 shows that single blank of material includes the diagram of multiple (being 4 in figure) sandwich material components.
The photo of the tangent plane of the material that Fig. 3 is cut by embodiment 1.
The photo of the tangent plane of the material that Fig. 4 is cut by embodiment 2.
Fig. 5 is the photo of the cut surface of cutting processing used in the prior art.
In figure:13:Base substrate;14:Upper holder;15 times holders;16:Upper and lower clipping processing tool.
Specific embodiment
The invention provides a kind of machine tooling method of high temperature resistant heat insulation sandwich material component, with reference to embodiment pair The present invention is described further.These implementation methods are to be illustrated with regard to the preferred embodiment of the present invention, the present invention Protection domain be not read as pertaining only to these implementation methods.
As described above, the invention provides a kind of machine tooling method of high temperature resistant heat insulation sandwich material component, the side Method comprises the following steps:
(1) construction material base substrate is placed in processing tool;
(2) construction material base substrate is positioned using location feature;
(3) the construction material base substrate having good positioning is fixed;
(4) edge cuts processing is carried out to construction material base substrate, obtains edge cuts tooling member;
Wherein, the construction material base substrate has heterogeneous Rotating fields, and edge cuts processing passes through machine tooling Mode is carried out.
Heterogeneous Rotating fields
In some embodiments, the heterogeneous Rotating fields are, with least 2 layers of heterogeneous Rotating fields, more preferably have At least 3 layers of heterogeneous Rotating fields, for example, can be the heterogeneous Rotating fields of 3 to 5 layers (such as 3 layers, 4 layers or 5 layers), or can have There are the heterogeneous Rotating fields of more interlayer.
In the heterogeneous Rotating fields, outer two layers preferably have hardness heterogeneity (hardness with least one inner core layers It is different).In other implementation methods, outer two layers and at least one inner core layers preferably enbrittle heterogeneous (fragility Or toughness is different);In preferred some implementation methods, outer two layers have hardness different with least one inner core layers Matter and fragility are heterogeneous.The hardness and/or fragility of outer two layers can be the same or different.
Some preferred embodiment in, the heterogeneous Rotating fields have 3 layers.For example, the heterogeneous Rotating fields are tool There are the heterogeneous Rotating fields of three-layer sandwich of upper strata, sandwich layer and lower floor.
In some implementation methods, the heterogeneous Rotating fields are made up of flaggy above, sandwich layer and following flaggy, and relative to Panel layer and sandwich layer each other for, core material is semi-flexible material, above cover sheet materials and/or following cover sheet materials be fragility Material.It is further preferred that for sandwich layer, above cover sheet materials and following cover sheet materials be fragile material.But, on The material of panel layer and following flaggy can be the same or different.
In one more specifically implementation method, the sandwich material component is typical three-ply sandwich structure component, is used Thermal protection outside the nacelle of superelevation velocity of sound aircraft.Flaggy and following flaggy are by high temperature resistant above the three-ply sandwich structure Ceramic fibre is constituted, and is usually obtained by the fiber preform and high temperature resistant precursor sol bluk recombination of three-dimensional braided structure, rigidity It is larger, with preferable high temperature resistant and anti-high velocity air performance of flushing;Middle sandwich layer is high temperature resistant aeroge, usually by soft Property high-temperature fibre precast body is obtained with aeroge precursor sol bluk recombination, with certain flexible and preferable heat-proof quality. Base substrate with this structure is larger due to the performance of marginal position and the performance difference of center section, it is difficult to add with settling at one go To prepare, and each layer is all still flexible comprising reinforcing fiber and has notable difference, be especially stranded when edge cuts are processed It is difficult.
Component
In some embodiments, the sandwich material component has flat surfaces.It is described in other implementation methods Sandwich material component has non-flat forms special-shaped surfaces.
Some preferred embodiment in, the sandwich material component has resistance to elevated temperatures, heat-proof quality and/or holds Performance is carried, preferably with resistance to elevated temperatures, heat-proof quality and load-carrying properties.In some embodiments, the sandwich material structure The use temperature upper limit of part is 1000~1200 DEG C;Room temperature thermal conductivity factor≤0.05W/mK;Compression strength > 1MPa;And/or The μ ε of strain property > 2000.
In some preferred implementation methods, the sandwich material component is used to be flown by being spliced to form hypersonic Thermal protection structure outside the nacelle of device.
As it was previously stated, hypersonic aircraft needs to have the thermal protection structure of temperature-resistance thermal-insulation and bearing function concurrently to avoid Burn and overheat in Aerodynamic Heating environment, such structure (hereinafter referred high temperature resistant heat insulation sandwich) generally has at least three The structure of layer, described three layers generally comprise outer two layers and at least one inner core layers.Sandwich layer it is general by with heat-resisting quantity and For example semiflexible material of heat-insulated relative flexibility is made.The material of outer two layers can be the same or different, generally by having The material for having fragility higher and hardness is made to provide bearing function.For example high temperature resistant heat insulation sandwich can have similar three The three-decker of Mingzhi's formula.
The preparation section of each layer is directed not only to due to being sandwich, during manufacture, is further related to the operation of each layer integration. Because sandwich has layers of material, and property is inhomogenous, therefore bright with homogeneous material component in preparation, processing Aobvious difference, needs to consider the problem of deformation matching in terms of preparation, and this is influential on the final type face precision of product.It is this Sandwich is mainly core material in processing and the difference of upper and lower panel material property is larger, and core material is semi-flexible material Material, panel material is fragile material, and when processing is substantially disposable processing simultaneously.Therefore, this sandwich is in one The performance or appearance profile of the marginal portion of the base substrate obtained after change cannot often meet use requirement, it is necessary to be carried out to edge Further processing.If using traditional processing mode, such as lathe, milling machine mode, have that positioning precision is low and processing after structure The problem of part rim condition not good (as shown in Figure 5).On the other hand, for being assemblied in outside the nacelle of superelevation velocity of sound aircraft This component needs to be stitched together multiple components when in use, thus interior outer mold surface for single interlayer heat insulating component and The requirement of surrounding contour accuracy is very high.Therefore, processing for such component is, it is necessary to accurately be processed. Because the heterogeneity of each layer and because the high-performance that the type face required by splicing and the high accuracy of edge contour and purposes are determined will Ask, so the machining accuracy and difficulty of this kind of component are increased significantly.
Some preferred embodiment in, the base substrate has keeper.It is high temperature resistant in the sandwich material component In the case of insulating sandwich structure, the keeper can for example be not less than the ceramics pole of body preparation temperature for heat-resisting quantity, Such as high temperature resistant ceramic of compact post, it is used to be accurately positioned on processing tool, so that it is guaranteed that the accuracy of processing.
In some embodiments, the edge cuts tooling member includes one or more described sandwich material structure Part, i.e., be many component base substrates for obtaining the base substrate of edge cuts tooling member by edge cuts processing.For example, the edge Cutting processing component can have at least 2, at least 3 or at least 4 sandwich material components.For example can have 2,3,4, 5th, 6,7,8,9,10,15 or 20 or even more sandwich material components.
In some embodiments, the edge cuts tooling member is the sandwich material component, that is to say, that passed through The edge cuts tooling member obtained after edge cuts processing is exactly the sandwich material component for wanting to obtain, i.e., described side Edge cutting processing component only includes a sandwich material component.
In some embodiments, the edge cuts tooling member, as described above, including multiple sandwich material structures Part, and methods described is after step (4), and methods described also includes step (5):By division processing by the edge cuts Tooling member further cuts multiple above-mentioned sandwich material components.
Processing tool
One skilled in the art that, frock is exactly the abbreviation of technological equipment, and processing tool is exactly for processing Technological equipment.In the present invention, processing tool is mainly used in construction material base substrate to be processed or by edge cuts The edge cuts tooling member of processing is positioned, fixed and cut or split.In some embodiments, the processing work Dress can be clipping processing tool.Clipping processing tool for example can be clipping, front and rear clipping up and down or left and right Clipping processing tool.If using clipping processing work, preferably using upper and lower clipping processing tool.
It is understood to one skilled in the art that clipping processing dress frock can have the type fitted with associated components matching Face, can only include side type face;Positioning datum feature for determining component relative position, such as locating surface, location hole, positioning Pin, locating dowel, guide pile or locating pin etc.;And its own machining tool that can be positioned to machining tool for including is determined Position feature, the machining tool location feature for example can on the basis of type face, for example any one be mutually perpendicular to face comprising three Wedge angle.
In addition, the type face that clipping processing tool can match laminating including type face relative with least two of component is determined Position feature;Positioning datum feature for determining component relative position;And instrument for upper and lower clamping tooling to be fixed or Frock.
Clipping processing tool can have the various location features for positioning, and such as point location feature (is for example positioned Stake), line location feature or type face location feature (such as periphery fitting-type face location feature), to improve the accuracy of positioning. In addition, clipping processing tool can also include the fixture for fixing base substrate or component.
Processing mode
The present invention can be processed using lathe by extra bed processing mode, such as described edge cuts are processed or divided Cutting processing can be carried out by machine tooling mode.In some embodiments, the machine tooling mode passes through form following mould Tire and three-dimensional DEM are carried out.Specifically, it is possible, firstly, to the positioning datum and type that are matched using component and form following mould tire Face conforms accurately to component to be fixed on mould tire, now the two can be considered as into one;Then mould tire itself is recycled to include Positioning reference plane, positioning centering is carried out on lathe, be typically to determine the origin of coordinates, this origin of coordinates and three-dimensional DEM After the coordinate of (component fitted with mould tire after state) matches, it is possible to be processed.
In some embodiments, the lathe is manually operated lathe such as lathe or milling machine, it is possible to use such Lathe carries out edge cuts processing.Use the manually operated processing can be with simple and easy to do, processing cost is low, is particularly suitable for processing same The less situation of the amount of specification number of components.Using the method for the present invention, by machine tooling mode, carried out for single member base substrate Edge cuts are processed, and trueness error can reach no more than 0.3%;In the case of many component base substrates, edge cuts processing or The trueness error of division processing can reach no more than 0.4%.
In some particularly preferred embodiments, especially type face positions can to use the location feature on processing tool Keeper in feature (large area is aligned and protects billet surface not to be damaged in process) and base substrate is determined Position, and be fixed by fixture, machining accuracy can be significantly increased.Then, in some embodiments, the edge The error of cutting processing and/or division processing is no more than 0.4%, such as no more than 0.4,0.3,0.2 or 0.1%, preferably not More than 0.05%, so as to fully meet the resistance to height of the thermal protection structure as the outer cabin for being spliced to form superelevation velocity of sound aircraft The high request of warm insulating sandwich structure.
The present invention is further detailed below in conjunction with accompanying drawing.
Fig. 1 shows the diagram that blank of material component is processed using clipping processing tool up and down.Base substrate 13 is clamped in Between the upper holder 14 and lower holder 15 of upper and lower clipping processing tool 16, lower surface and the base substrate 13 of upper holder 14 Upper surface is fitted, and the upper surface of lower holder 15 is fitted with the lower surface of base substrate 13, and edge cuts processing is then carried out again. Upper holder 14 and/or lower holder 15 have the type face of matching of being fitted with sandwich material component and the type face can cover folder Most or all surfaces of layer material component, so that reduce in process or prevent the damage to component surface, It is very important that this needs the high temperature resistant heat insulation sandwich for ultrahigh frequency aircraft of protection meticulously for surface.
Fig. 2 shows that single blank of material includes the diagram of multiple (being 4 in figure) sandwich material components.As shown in Fig. 2 Single base substrate 23 includes 4 (can be fewer or greater than 4) components 24, wherein 4 shape and size of component can be with identical Or it is different, it is preferred that at least two at least one justified margins of component, can so improve the efficiency of edge processing. And, the main advantage of single body preparation multiple component is the raising of production efficiency, can significantly save body preparation Time, once prepared additionally, due to base substrate, can to a certain extent improve homogeneity (that is, the product quality of component performance Stability).
Embodiment
The present invention is further detailed by embodiment hereafter, but these embodiments are only limited the use of in explanation mesh , protection scope of the present invention is not limited to these embodiments.
Embodiment 1
By manual milling machine processing mode to the single member material with flaggy above, following flaggy and sandwich layer this three-decker Material is processed, layers of material as shown in table 2, wherein above flaggy and following flaggy by three-dimensional braided structure fiber preform It is compound with high temperature resistant sol precursor (silica) to obtain;Middle sandwich layer is by flexible high-temperature resistant fiber preform and aeroge Sol precursor (silica) is compound to be obtained.As shown in figure 1, a construction material base for sandwich material component will be included first Body is placed in upper and lower clipping processing tool;Then construction material base substrate is positioned using location feature;By the structure having good positioning Part body of material is fixed;Edge cuts processing is carried out to construction material base substrate, so as to obtain final sandwich material component (referring to Fig. 1).Machining accuracy error, temperature tolerance and compliance are referring to table 2 below.The tangent plane photo of cutting processing is referring to Fig. 3.
Embodiment 2
By manual milling machine processing mode to many component materials with flaggy above, following flaggy and sandwich layer this three-decker Material (including 4 sandwiches) is processed, and layers of material is as shown in table 2, wherein flaggy and following flaggy are compiled by three-dimensional above Knit that the fiber preform of structure is compound with high temperature resistant sol precursor (aluminum oxide) to be obtained;Middle sandwich layer is fine by flexible high-temperature resistant Dimension precast body is compound with aeroge sol precursor (aluminum oxide) to be obtained.As shown in figure 1, first will be including 4 sandwich material structures The construction material base substrate of part is placed in upper and lower clipping processing tool;Then construction material base substrate is determined using location feature Position;The construction material base substrate having good positioning is fixed;Edge cuts processing is carried out to construction material base substrate, is passed through so as to obtain edge The edge cuts tooling member of cutting processing, is then divided into four final structures to be obtained by the edge cuts tooling member Part (referring to Fig. 1 and 2).Machining accuracy error, temperature tolerance and compliance are referring to table 2 below.The tangent plane photo of cutting processing is referring to figure 4。
Embodiment 3-4
Carried out according to content shown in following table, machining accuracy error is referring to table 1.
Embodiment Material The number of components (individual) Processing mode Processing mode
Embodiment 3 With embodiment 3 4 With embodiment 2 Manual milling machine
Embodiment 4 With embodiment 3 1 With embodiment 1 Manual milling machine
Comparative example 1
The construction material base substrate used with embodiment 1 using conventional cutting processing mode pair is processed, specifically, According to the size of the sandwich to be obtained, the edge contour of the component to be obtained is measured from base substrate and draws, then Cutting processing is carried out along the contour line for being drawn by manual milling machine.Machining accuracy error is referring to table 2 below.
Comparative example 2
Comparative example 2 is used and the identical of comparative example 1 routine cutting processing mode, pair phase isomorphism used with embodiment 2 Part body of material is processed.Machining accuracy error, temperature tolerance and compliance are referring to table 2 below.
Blank of material and machining accuracy error, temperature tolerance and compliance in each embodiment of table 2
"-" represented and do not measure.

Claims (10)

1. a kind of machine tooling method of high temperature resistant heat insulation sandwich material component, it is characterised in that methods described includes following step Suddenly:
(1) construction material base substrate is placed in processing tool;
(2) construction material base substrate is positioned using location feature;
(3) the construction material base substrate having good positioning is fixed;
(4) edge cuts processing is carried out to construction material base substrate, obtains edge cuts tooling member;
Wherein, the construction material base substrate has heterogeneous Rotating fields, and edge cuts processing by machine tooling mode Carry out.
2. method according to claim 1, it is characterised in that the edge cuts manufacturing tolerance is no more than 0.3%.
3. method according to claim 1, it is characterised in that:
The processing tool is clipping processing tool, and the fixation realized by fixture;
Preferably, the location feature include on the processing tool with being fitted with sandwich material Components Matching Type face location feature and/or positioning datum feature;And/or being aligned with positioning datum feature locations on construction material base substrate Keeper;
It is further preferred that the keeper is not less than the ceramics pole of body preparation temperature including heat-resisting quantity;And/or the type face Location feature includes thering is the periphery fitting-type face location feature fitted with sandwich material Components Matching.
4. method according to claim 1, it is characterised in that the sandwich material component has flat surfaces and/or institute Stating sandwich material component has non-flat forms special-shaped surfaces.
5. method according to any one of claim 1 to 4, it is characterised in that:
The sandwich material component has resistance to elevated temperatures, heat-proof quality and load-carrying properties;
Preferably, the use temperature upper limit of the sandwich material component is 1000~1200 DEG C;Room temperature thermal conductivity factor≤ 0.05W/m·K;Compression strength > 1MPa;And/or the μ ε of strain property > 2000;
It is further preferred that the sandwich material component is used to prevent by being spliced to form the heat outside the nacelle of hypersonic aircraft Protection structure.
6. method according to any one of claim 1 to 4, it is characterised in that:
The edge cuts tooling member includes multiple sandwich material components, and methods described is after step (4), institute Stating method also includes step (5):The edge cuts tooling member is further cut into by multiple folders by division processing Layer material component;
Preferably, the error of the division processing is no more than 0.3%.
7. method according to any one of claim 1 to 4, it is characterised in that the edge cuts tooling member is only wrapped Include a sandwich material component.
8. method according to any one of claim 1 to 4, it is characterised in that the lathe is lathe or milling machine.
9. method according to any one of claim 1 to 4, it is characterised in that:
The heterogeneous Rotating fields are with least 3 layers of heterogeneous Rotating fields;
Preferably, the outer two layers in the heterogeneous Rotating fields and at least one inner core layers have hardness heterogeneous and/or Fragility is heterogeneous.
10. method according to any one of claim 1 to 4, it is characterised in that:
The heterogeneous Rotating fields are the heterogeneous Rotating fields of three-layer sandwich with upper strata, sandwich layer and lower floor;
It is further preferred that the heterogeneous Rotating fields are made up of flaggy above, sandwich layer and following flaggy, and relative to panel layer and Sandwich layer each other for, core material is semi-flexible material, above cover sheet materials and/or following cover sheet materials be fragile material.
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Cited By (3)

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CN110355814A (en) * 2019-06-19 2019-10-22 西安理工大学 A kind of inexpensive micro-processing method for ultralight frangible aeroge
CN110587231A (en) * 2019-09-06 2019-12-20 北京星航机电装备有限公司 Method for processing composite cabin body made of thermal protection material and metal material
CN110744110A (en) * 2019-11-07 2020-02-04 北京星航机电装备有限公司 Low-damage processing method of inorganic phenolic aerogel

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102390004A (en) * 2011-07-20 2012-03-28 沈阳飞机工业(集团)有限公司 Method for processing laser cutting combined tool with mathematical model
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
WO2015016730A3 (en) * 2013-08-02 2015-04-09 Active Aerogels, Unipessoal, Lda. Method for production of flexible panels of hydrophobic aerogel reinforced with fibre felts
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
CN105442782A (en) * 2015-08-26 2016-03-30 马玉新 Integrated plate
CN105464316A (en) * 2015-08-26 2016-04-06 马玉新 Making method of integrated board

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102390004A (en) * 2011-07-20 2012-03-28 沈阳飞机工业(集团)有限公司 Method for processing laser cutting combined tool with mathematical model
WO2015016730A3 (en) * 2013-08-02 2015-04-09 Active Aerogels, Unipessoal, Lda. Method for production of flexible panels of hydrophobic aerogel reinforced with fibre felts
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
CN105442782A (en) * 2015-08-26 2016-03-30 马玉新 Integrated plate
CN105464316A (en) * 2015-08-26 2016-04-06 马玉新 Making method of integrated board

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
融亦鸣: "《计算机辅助夹具设计》", 28 February 2002 *

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110355814A (en) * 2019-06-19 2019-10-22 西安理工大学 A kind of inexpensive micro-processing method for ultralight frangible aeroge
CN110587231A (en) * 2019-09-06 2019-12-20 北京星航机电装备有限公司 Method for processing composite cabin body made of thermal protection material and metal material
CN110744110A (en) * 2019-11-07 2020-02-04 北京星航机电装备有限公司 Low-damage processing method of inorganic phenolic aerogel

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