CN110587231A - Method for processing composite cabin body made of thermal protection material and metal material - Google Patents
Method for processing composite cabin body made of thermal protection material and metal material Download PDFInfo
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- CN110587231A CN110587231A CN201910841768.4A CN201910841768A CN110587231A CN 110587231 A CN110587231 A CN 110587231A CN 201910841768 A CN201910841768 A CN 201910841768A CN 110587231 A CN110587231 A CN 110587231A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
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Abstract
The invention belongs to the technical field of cabin body processing, and particularly relates to a method for processing a thermal protection material and metal material composite cabin body. In the characteristic processing step on the cabin body, the invention provides feasible processing parameters and standard operation flows, identifies and controls risk points in the cabin body, can effectively protect a thermal protection layer when processing the metal cabin body, and has guiding significance for improving the processing quality and efficiency of the composite cabin body.
Description
Technical Field
The invention belongs to the technical field of cabin body processing, and particularly relates to a method for processing a thermal protection material and metal material composite cabin body.
Background
In order to improve the high temperature resistance of the metal cabin, an IPA thermal protection layer is adhered to the surface of the metal cabin to form a composite cabin; because the difference between the processing characteristics of the thermal protection layer material and the metal material is large, a targeted processing method is required to be adopted to ensure the performance when the composite material cabin is integrally processed.
Disclosure of Invention
Technical problem to be solved
The invention provides a method for processing a composite cabin body made of a thermal protection material and a metal material, and aims to solve the technical problem of how to protect the thermal protection layer when a metal cabin body is processed.
(II) technical scheme
In order to solve the technical problem, the invention provides a method for processing a composite cabin body made of a thermal protection material and a metal material, which comprises the following steps:
s1, inspecting and protecting the surface of the cabin;
s2, cabin body clamping is carried out by using a tool;
s3, performing characteristic processing on the cabin body, wherein cutting fluid and cooling fluid are not used during characteristic processing, an air gun is not used, and a dust collector is adopted to synchronously absorb dust cuttings on the surfaces of the parts; checking whether the cut surface of the thermal protection layer has layering debonding after each layer of milling feed is finished, cleaning burrs of the cut surface of the thermal protection layer, and absorbing and removing powder and metal cuttings of the thermal protection layer; after each layer of drilling machining, checking and cleaning redundant materials on the surface of the drill bit, avoiding scratching the thermal protection layer material by next cutting, and absorbing and removing metal cuttings in the hole;
s4, repairing by a fitter, namely repairing the edge processed by the thermal protection layer in the installation butt joint area of the cabin body, and ensuring that the thermal protection layer does not protrude out of the end face of the metal cabin body by taking the end face of the metal cabin body as a reference and the gap is not more than 0.2 mm.
Further, in step S2, a conformal tool is used for aligning and clamping, and during clamping, the tightening force is adjusted by measuring the gap between the tool and the cabin, so that the surface of the thermal protection layer cannot be squeezed; and measuring the appearance of the cabin body, and controlling the deformation within 0.1 mm.
Further, in step S3, during the surface processing, the thermal protection layer is removed until the thermal protection layer is flush with the outer surface of the metal capsule, and the surface processing is performed by rough processing, semi-finishing and finish processing:
rough machining: adopting a coating hard alloy cutter with phi 10mm or phi 12mm, wherein the rotating speed of a main shaft is 600-;
semi-finishing: adopting a diamond cutter with phi 10mm or phi 12mm, wherein the rotating speed of a main shaft is 3000-;
finish machining: adopting a diamond cutter with phi 10mm or phi 12mm, wherein the rotating speed of a main shaft is 3000-;
firstly, when the allowance of the bottom surface is 0.5mm, measuring the height difference of residual materials around the bottom surface, then processing the bottom surface to be level with the highest point of the metal cabin body according to the depth of each layer of the bottom surface being 0.2mm, and removing the residual materials by a bench worker.
Further, the surface features are end faces and hems.
Further, in step S3, the heat shield and the metal are cut together to the same plane during the cross-sectional machining, and the machining is performed by using rough machining, semi-finish machining, and finish machining:
rough machining: adopting a coated hard alloy cutter with phi 10mm or phi 12mm, wherein the rotating speed of a main shaft is 600-;
semi-finishing: when the thermal protection layer is processed, a diamond cutter with phi 10mm or phi 12mm is adopted, the rotating speed of a main shaft is 3000-; when a metal layer with the thickness of less than 5mm is processed, a diamond cutter with the thickness of phi 10mm or phi 12mm can be continuously adopted, the rotating speed of a main shaft is 1500-2000r/min, the feeding speed is 500-700mm/min, the cutting width is 4-8mm, and the cutting depth is 1-3 mm; when a metal layer with the thickness of more than 5mm is processed, a coating hard alloy cutter with the thickness of phi 10mm or phi 12mm is replaced, the rotating speed of a main shaft is 800-;
finish machining: when the thermal protection layer is processed, a diamond cutter with phi 10mm or phi 12mm is adopted, the rotating speed of a main shaft is 3000-; when the metal layer with the thickness of less than 5mm is processed, a diamond cutter with the thickness of phi 10mm or phi 12mm can be continuously adopted, the rotating speed of the main shaft is 1500-2000r/min, the feeding speed is 500-700mm/min, the cutting width is 4-8mm, and the cutting depth is 0.4-1 mm; when a metal layer with the thickness of more than 5mm is processed, the metal layer is replaced by a coating hard alloy cutter with the thickness of phi 10mm or phi 12mm, the rotating speed of a main shaft is 800-;
first using a diamond tool to cut completely into the metal layer, and then selecting the machining tool and parameters according to the thickness of the material.
Further, the profile features a window, a depression, and a flap.
Further, in step S3, when the hole is machined, the heat shield and the metal are cut together to the same plane, and rough machining and finish machining are performed:
rough machining: adopting a coated hard alloy cutter with phi 10mm or phi 12mm, wherein the rotating speed of a main shaft is 600-;
finish machining: when the thermal protection layer is processed, a diamond cutter with phi 10mm or phi 12mm is adopted, the rotating speed of a main shaft is 3000-; when the metal layer with the thickness of less than 5mm is processed, a diamond cutter with the thickness of phi 10mm or phi 12mm can be continuously adopted, the rotating speed of the main shaft is 1500-2000r/min, the feeding speed is 500-700mm/min, the cutting width is 4-8mm, and the cutting depth is 0.4-1 mm; when a metal layer with the thickness of more than 5mm is processed, the metal layer is replaced by a coating hard alloy cutter with the thickness of phi 10mm or phi 12mm, the rotating speed of a main shaft is 800-;
firstly, processing the diameter to a single side with the allowance of 2mm, observing the position relation with a hole on a metal substrate, determining that the two are coaxial, and then processing the two to the size by adopting a radius compensation mode; the hole which is too small in size and cannot be milled is drilled by adopting an alloy drill, and the depth of each time is not more than 0.5 mm.
Further, step S5 is executed after step S4, whether the size and the form and the position meet the requirements or not is checked, whether the surface of the part has excess and is scratched by collision or not, the material of the thermal protection layer does not have layering and debonding, the thermal protection layer does not protrude out of the end face of the metal cabin body is checked, and the turnover protection state of the part is checked during final delivery.
(III) advantageous effects
The method for processing the composite cabin body of the thermal protection material and the metal material comprises the steps of inspecting and protecting the surface of the cabin body, clamping the cabin body by using a tool, performing characteristic processing on the cabin body and repairing and matching by a fitter. In the characteristic processing step on the cabin body, the invention provides feasible processing parameters and standard operation flows, identifies and controls risk points in the cabin body, can effectively protect a thermal protection layer when processing the metal cabin body, and has guiding significance for improving the processing quality and efficiency of the composite cabin body.
Drawings
FIG. 1 is a flow chart of a method for processing a composite cabin according to an embodiment of the present invention;
fig. 2 is a schematic view of the processing characteristics of the composite cabin according to the embodiment of the invention.
Detailed Description
In order to make the objects, contents and advantages of the present invention clearer, the following detailed description of the embodiments of the present invention will be made in conjunction with the accompanying drawings and examples.
The embodiment provides a method for processing a composite cabin body made of a thermal protection material and a metal material, and the main flow of the method is shown in fig. 1. The method specifically comprises the following steps:
(1) turnover protection:
the cabin body surface is required to be inspected and protected before the parts are machined, and the method comprises the following steps:
opening the peripheral lock catch of the cabin packaging box, and taking down a packaging box cover plate;
secondly, the bag belt and the cabin body are isolated and protected by a foam layer, and the cabin body is lifted out of the packing box and is arranged on a wood supporting seat;
checking the appearance of the cabin body, wherein the surface is required to have no collision and scratch defects, and the thermal protection layer material is required to have no delamination and debonding;
fourthly, marking and transferring marks on the metal surface are finished, and the thermal protection layer cannot be stained;
and fifthly, wrapping the outer molded surface of the part by using a protective film.
(2) Aligning and clamping: use special frock to carry out cabin body clamping, include:
firstly, aligning and clamping by using a conformal tool, and measuring the clearance between the tool and a cabin body during clamping to adjust the tightening force so as not to extrude the surface of a hot protective layer;
secondly, measuring the appearance of the cabin body and controlling the deformation within 0.1 mm.
(3) Performing characteristic processing on the cabin body: the cabin body processing comprises three typical characteristics, namely a surface 5, a section 3 and a hole 4 (shown in figure 2), and different processing methods are adopted for the three typical characteristics, wherein the processing methods comprise the following steps:
cutting fluid and cooling fluid are strictly forbidden during feature processing, an air gun is strictly forbidden, and a dust collector is adopted to synchronously absorb and remove dust and cuttings on the surfaces of parts;
trial cutting is needed before formal processing, and the method is used for determining a processing position besides confirming the correctness of a program so as to remove the package of the processing position;
surface processing: removing the allowance of the thermal protection layer 2 until the allowance is flush with the outer surface of the metal cabin body 1, wherein the typical characteristics are end surface and edge covering, and the rough machining, the semi-finish machining and the finish machining are adopted:
rough machining (balance 4-6 mm): adopting a coating hard alloy cutter with phi 10mm or phi 12mm, wherein the rotating speed of a main shaft is 600-;
semi-finishing (balance 1-3 mm): adopting a diamond cutter with phi 10mm or phi 12mm, wherein the rotating speed of a main shaft is 3000-;
finish machining: adopting a diamond cutter with phi 10mm or phi 12mm, wherein the rotating speed of a main shaft is 3000-;
firstly, when the allowance of the bottom surface is 0.5mm, measuring the height difference of residual materials around the bottom surface, then processing the bottom surface to be flat with the depth of each layer being 0.2mm until the bottom surface is connected with the highest point of the metal cabin body, and removing the residual materials by a bench worker;
fourthly, processing the cross section: the thermal protection layer 2 is cut to the same plane together with the metal, typically characterized by windows, undercuts and flaps, using rough machining-semi-finish machining:
rough machining (balance 4-6 mm): adopting a coated hard alloy cutter with phi 10mm or phi 12mm, wherein the rotating speed of a main shaft is 600-;
semi-finishing (balance 1-3 mm): when the thermal protection layer is processed, a diamond cutter with phi 10mm or phi 12mm is adopted, the rotating speed of a main shaft is 3000-; when a metal layer with the thickness of less than 5mm is processed, a diamond cutter with the thickness of phi 10mm or phi 12mm can be continuously adopted, the rotating speed of a main shaft is 1500-2000r/min, the feeding speed is 500-700mm/min, the cutting width is 4-8mm, and the cutting depth is 1-3 mm; when a metal layer with the thickness of more than 5mm is processed, a coating hard alloy cutter with the thickness of phi 10mm or phi 12mm is replaced, the rotating speed of a main shaft is 800-;
finish machining: when the thermal protection layer is processed, a diamond cutter with phi 10mm or phi 12mm is adopted, the rotating speed of a main shaft is 3000-; when the metal layer with the thickness of less than 5mm is processed, a diamond cutter with the thickness of phi 10mm or phi 12mm can be continuously adopted, the rotating speed of the main shaft is 1500-2000r/min, the feeding speed is 500-700mm/min, the cutting width is 4-8mm, and the cutting depth is 0.4-1 mm; when a metal layer with the thickness of more than 5mm is processed, the metal layer is replaced by a coating hard alloy cutter with the thickness of phi 10mm or phi 12mm, the rotating speed of a main shaft is 800-;
firstly, using a diamond cutter to process the metal layer until the metal layer is completely cut in, and then selecting a processing cutter and parameters according to the thickness of the material;
hole machining: by rough-finish machining
The hole machining is recommended to be milling, the cutter and parameters are consistent with the cross section machining, the diameter is machined to be 2mm of the single-side allowance, the position relation between the hole and the metal substrate is observed, the hole and the metal substrate are coaxial, and then the hole is machined to be the size in a radius compensation mode; drilling holes which are too small in size and cannot be milled, and adopting an alloy drill bit, wherein the depth of each time is not more than 0.5 mm;
sixthly, layered processing: checking whether the cut surface of the thermal protection layer has layering debonding after each layer of milling feed is finished, cleaning burrs of the cut surface of the thermal protection layer, and absorbing and removing powder and metal cuttings of the thermal protection layer; after each layer of drilling machining, checking and cleaning redundant materials on the surface of the drill bit, avoiding scratching the thermal protection layer material by next cutting, and absorbing and removing metal cuttings in the hole;
seventhly, repairing and matching by a fitter, repairing and matching the processed edge of the thermal protection layer in the installation butt joint area of the cabin body by using a scalpel, and ensuring that the thermal protection layer does not protrude out of the end surface of the metal cabin body by taking the end surface of the metal cabin body as a reference, wherein the gap is not more than 0.2 mm; note that sanding with abrasive belt or sand paper is prohibited.
(4) And (4) checking: checking whether the size and the shape and the position meet the requirements, checking whether the surface of the part has excess materials, collision and scratch, no layering and debonding of the thermal protection layer material, no protrusion of the thermal protection layer out of the end face of the metal cabin body, and checking the turnover protection state of the part during final delivery.
The above description is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, several modifications and variations can be made without departing from the technical principle of the present invention, and these modifications and variations should also be regarded as the protection scope of the present invention.
Claims (8)
1. A method for processing a composite cabin body made of a thermal protection material and a metal material is characterized by comprising the following steps:
s1, inspecting and protecting the surface of the cabin;
s2, cabin body clamping is carried out by using a tool;
s3, performing characteristic processing on the cabin body, wherein cutting fluid and cooling fluid are not used during characteristic processing, an air gun is not used, and a dust collector is adopted to synchronously absorb dust cuttings on the surfaces of the parts; checking whether the cut surface of the thermal protection layer has layering debonding after each layer of milling feed is finished, cleaning burrs of the cut surface of the thermal protection layer, and absorbing and removing powder and metal cuttings of the thermal protection layer; after each layer of drilling machining, checking and cleaning redundant materials on the surface of the drill bit, avoiding scratching the thermal protection layer material by next cutting, and absorbing and removing metal cuttings in the hole;
s4, repairing by a fitter, namely repairing the edge processed by the thermal protection layer in the installation butt joint area of the cabin body, and ensuring that the thermal protection layer does not protrude out of the end face of the metal cabin body by taking the end face of the metal cabin body as a reference and the gap is not more than 0.2 mm.
2. The processing method according to claim 1, wherein in step S2, a conformal tool is used for aligning and clamping, and during clamping, the gap between the measuring tool and the cabin is measured to adjust the tightening force so as not to press the surface of the thermal protection layer; and measuring the appearance of the cabin body, and controlling the deformation within 0.1 mm.
3. The method of claim 1, wherein in step S3, the surface processing is performed by removing the thermal protection layer until the thermal protection layer is flush with the outer surface of the metal capsule, and performing the rough machining, semi-finishing and finishing by:
rough machining: adopting a coating hard alloy cutter with phi 10mm or phi 12mm, wherein the rotating speed of a main shaft is 600-;
semi-finishing: adopting a diamond cutter with phi 10mm or phi 12mm, wherein the rotating speed of a main shaft is 3000-;
finish machining: adopting a diamond cutter with phi 10mm or phi 12mm, wherein the rotating speed of a main shaft is 3000-;
firstly, when the allowance of the bottom surface is 0.5mm, measuring the height difference of residual materials around the bottom surface, then processing the bottom surface to be level with the highest point of the metal cabin body according to the depth of each layer of the bottom surface being 0.2mm, and removing the residual materials by a bench worker.
4. The process of claim 3 wherein the surface features are end faces and hems.
5. The processing method according to claim 1, wherein in the step S3, when the cross-sectional processing is performed, the heat shielding layer and the metal are cut to the same plane together, and the processing is performed by using rough processing-semi-finishing:
rough machining: adopting a coated hard alloy cutter with phi 10mm or phi 12mm, wherein the rotating speed of a main shaft is 600-;
semi-finishing: when the thermal protection layer is processed, a diamond cutter with phi 10mm or phi 12mm is adopted, the rotating speed of a main shaft is 3000-; when a metal layer with the thickness of less than 5mm is processed, a diamond cutter with the thickness of phi 10mm or phi 12mm can be continuously adopted, the rotating speed of a main shaft is 1500-2000r/min, the feeding speed is 500-700mm/min, the cutting width is 4-8mm, and the cutting depth is 1-3 mm; when a metal layer with the thickness of more than 5mm is processed, a coating hard alloy cutter with the thickness of phi 10mm or phi 12mm is replaced, the rotating speed of a main shaft is 800-;
finish machining: when the thermal protection layer is processed, a diamond cutter with phi 10mm or phi 12mm is adopted, the rotating speed of a main shaft is 3000-; when the metal layer with the thickness of less than 5mm is processed, a diamond cutter with the thickness of phi 10mm or phi 12mm can be continuously adopted, the rotating speed of the main shaft is 1500-2000r/min, the feeding speed is 500-700mm/min, the cutting width is 4-8mm, and the cutting depth is 0.4-1 mm; when a metal layer with the thickness of more than 5mm is processed, the metal layer is replaced by a coating hard alloy cutter with the thickness of phi 10mm or phi 12mm, the rotating speed of a main shaft is 800-;
first using a diamond tool to cut completely into the metal layer, and then selecting the machining tool and parameters according to the thickness of the material.
6. The process of claim 5 wherein the cross-sectional features are windows, depressions and flaps.
7. The method of claim 1, wherein in the step S3, the hole is processed by cutting the thermal shield and the metal together to the same plane, and performing the rough machining-finishing by:
rough machining: adopting a coated hard alloy cutter with phi 10mm or phi 12mm, wherein the rotating speed of a main shaft is 600-;
finish machining: when the thermal protection layer is processed, a diamond cutter with phi 10mm or phi 12mm is adopted, the rotating speed of a main shaft is 3000-; when the metal layer with the thickness of less than 5mm is processed, a diamond cutter with the thickness of phi 10mm or phi 12mm can be continuously adopted, the rotating speed of the main shaft is 1500-2000r/min, the feeding speed is 500-700mm/min, the cutting width is 4-8mm, and the cutting depth is 0.4-1 mm; when a metal layer with the thickness of more than 5mm is processed, the metal layer is replaced by a coating hard alloy cutter with the thickness of phi 10mm or phi 12mm, the rotating speed of a main shaft is 800-;
firstly, processing the diameter to a single side with the allowance of 2mm, observing the position relation with a hole on a metal substrate, determining that the two are coaxial, and then processing the two to the size by adopting a radius compensation mode; the hole which is too small in size and cannot be milled is drilled by adopting an alloy drill, and the depth of each time is not more than 0.5 mm.
8. The machining method according to claim 1, wherein step S5 is executed after step S4 to check whether the dimensions and the form and position meet the requirements, whether the surfaces of the parts have excess and are scratched or not, the materials of the thermal protection layers do not have delamination and debonding, the thermal protection layers do not protrude out of the end faces of the metal cabin, and the turnover protection state of the parts is checked during final delivery.
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| CN201910841768.4A CN110587231B (en) | 2019-09-06 | 2019-09-06 | Method for processing composite cabin body made of thermal protection material and metal material |
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Cited By (3)
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| CN111300537A (en) * | 2019-12-30 | 2020-06-19 | 北京航星机器制造有限公司 | Processing method of inorganic phenolic aerogel thermal protection layer |
| CN114211206A (en) * | 2021-12-22 | 2022-03-22 | 北京星航机电装备有限公司 | Method for processing multi-cavity casting cabin body of revolving body |
| CN114393424A (en) * | 2022-02-25 | 2022-04-26 | 北京星航机电装备有限公司 | Clamping and aligning method for cabin body after heat application protection |
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| CN114393424B (en) * | 2022-02-25 | 2022-12-30 | 北京星航机电装备有限公司 | Clamping and aligning method for cabin body after heat application protection |
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