CN114951735A - Machining method of composite cabin section - Google Patents
Machining method of composite cabin section Download PDFInfo
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- CN114951735A CN114951735A CN202210669569.1A CN202210669569A CN114951735A CN 114951735 A CN114951735 A CN 114951735A CN 202210669569 A CN202210669569 A CN 202210669569A CN 114951735 A CN114951735 A CN 114951735A
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- proof layer
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23B—TURNING; BORING
- B23B35/00—Methods for boring or drilling, or for working essentially requiring the use of boring or drilling machines; Use of auxiliary equipment in connection with such methods
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
- B29C65/48—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C66/00—General aspects of processes or apparatus for joining preformed parts
- B29C66/01—General aspects dealing with the joint area or with the area to be joined
- B29C66/03—After-treatments in the joint area
- B29C66/032—Mechanical after-treatments
- B29C66/0326—Cutting, e.g. by using waterjets, or perforating
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C66/00—General aspects of processes or apparatus for joining preformed parts
- B29C66/50—General aspects of joining tubular articles; General aspects of joining long products, i.e. bars or profiled elements; General aspects of joining single elements to tubular articles, hollow articles or bars; General aspects of joining several hollow-preforms to form hollow or tubular articles
- B29C66/51—Joining tubular articles, profiled elements or bars; Joining single elements to tubular articles, hollow articles or bars; Joining several hollow-preforms to form hollow or tubular articles
- B29C66/52—Joining tubular articles, bars or profiled elements
- B29C66/522—Joining tubular articles
- B29C66/5221—Joining tubular articles for forming coaxial connections, i.e. the tubular articles to be joined forming a zero angle relative to each other
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/52—Protection, safety or emergency devices; Survival aids
- B64G1/58—Thermal protection, e.g. heat shields
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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Abstract
The invention discloses a processing method of a composite cabin section, relates to the technical field of cabin section processing, and solves the technical problems that the processing difficulty is large and the precision and the qualification rate are influenced because the composite cabin section is easy to deform in the related technology, and comprises the following steps: processing a first opening on the metal shell, and plugging the first opening; sleeving the non-metal heat-proof layer outside the metal shell to form a composite cabin section raw material; curing the composite cabin raw material; processing the shape of the non-metal heat-proof layer; processing a second opening on the nonmetal heat-proof layer; and cleaning the filler in the first opening. The stress generated in the machining process of the metal cabin section is released by pre-drilling the hole on the metal shell, so that the adverse condition that the metal shell is deformed in the subsequent machining process of the raw material of the composite cabin section is improved; after the raw materials of the composite cabin section are sleeved and formed, the appearance and the hole of the non-metal heat-proof layer are processed, so that the influence of the sleeving on the machining process of the composite cabin section is reduced, the precision of the composite cabin section is improved, and the machining qualified rate is ensured.
Description
Technical Field
The invention relates to the technical field of cabin section processing, in particular to a processing method of a composite cabin section.
Background
The composite cabin section consisting of the metal shell and the nonmetal heat-proof layer is an important part of an aerospace product, the metal shell on the inner layer can provide an installation space for different instruments or equipment, and the nonmetal heat-proof layer on the outer layer is used as a protective layer of an aircraft. However, the diameter of the composite cabin section is usually larger, the skin is thinner, and the rigidity is weaker, so that the cabin section is easy to deform in the machining process, the machining difficulty of the cabin section is increased, the precision of the cabin section is reduced, and the percent of pass of cabin section machining is reduced.
Disclosure of Invention
The application provides a processing method of a composite cabin section, and solves the technical problems that in the related technology, the processing difficulty is high, and the precision and the qualified rate are influenced due to the fact that the composite cabin section is easy to deform in processing.
The application provides a processing method of a composite cabin section, which comprises the following steps: processing a first opening on the metal shell, and filling filler in the first opening to block the first opening; sleeving the non-metal heat-proof layer outside the metal shell to form a composite cabin section raw material; curing the composite cabin raw material; processing the appearance of the non-metal heat-proof layer of the composite cabin section raw material; processing a second opening on the non-metal heat-proof layer of the composite cabin raw material, wherein the second opening is arranged corresponding to the first opening; and cleaning the filler in the first open hole to obtain the composite cabin section.
Optionally, the first opening comprises a first kidney-shaped slot provided at the end of the metal shell and a first opening provided at the body of the metal shell;
the second opening comprises a second kidney-shaped groove arranged at the end part of the non-metal heat-proof layer and a second opening arranged at the body part of the non-metal heat-proof layer;
the second trompil corresponds the setting with first trompil, includes: the first kidney-shaped groove and the second kidney-shaped groove are concentrically arranged, and the first opening and the second opening are concentrically arranged.
Optionally, the first opening further comprises a first lifting hole provided at an end of the metal shell;
the second hole also comprises a second lifting hole arranged at the end part of the non-metal heat-proof layer;
the second trompil corresponds the setting with first trompil, includes: the first lifting hole and the second lifting hole are concentrically arranged.
Optionally, plugging the first opening includes plugging the first kidney-shaped slot, and plugging the first kidney-shaped slot includes:
cleaning the inner wall of a first kidney-shaped groove on the metal shell;
cutting the pressure-sensitive adhesive tape according to the surface area of the first kidney-shaped groove so that the allowance of the periphery of the surface area of the pressure-sensitive adhesive tape is between 10mm and 12 mm;
matching a wooden block cover according to the size of the bottom of the first waist-shaped groove, so that the margin of the periphery of the wooden block cover is between-1 mm and-1.5 mm, and the margin of the height of the wooden block cover and the depth of the first waist-shaped groove is between 0mm and-1 mm;
uniformly coating the pressure-sensitive adhesive tape on the wooden plug cover, and installing the pressure-sensitive adhesive tape and the wooden plug cover into the first kidney-shaped groove;
pressing the exposed part of the pressure-sensitive adhesive tape on the outer surface of the first kidney-shaped groove, and cutting off the redundant pressure-sensitive adhesive tape;
carry out stifled hole to first trompil includes carries out stifled hole to first opening, carries out stifled hole to first opening and includes:
cleaning the inner wall of the first opening on the metal shell;
the metal blocking cover is matched according to the size of the first opening on the metal shell, so that the allowance of the periphery of the metal blocking cover is between-0.3 mm and-0.5 mm, and the height of the metal blocking cover and the allowance of the outer surface of the first opening are between 0mm and-0.3 mm;
the outer surface of the metal cap is covered with a blue separating film and is fitted into the first opening together.
Optionally, plugging the first opening includes plugging a first lifting hole, and plugging the first lifting hole includes:
and sealing the first lifting hole in the metal shell by using a sealing rubber strip so that the height of the sealing rubber strip and the allowance of the surface of the first lifting hole are between 0mm and-1 mm.
Optionally, after the first opening is plugged and before the non-metal heat protection layer is sleeved outside the metal shell, performing end surface protection on the metal shell;
performing end face shielding of the metal shell includes:
and cleaning the end faces of two axial sides of the metal shell, and respectively sticking a layer of medical adhesive tape.
Optionally, sleeving the non-metallic heat protection layer outside the metal shell comprises: the nonmetal heat-proof layer and the metal shell are in trial assembly; after the trial assembly, sleeving the non-metal heat-proof layer with the metal shell;
non-metal heat protection layer and metal casing try on suit, include:
the metal shell is placed upside down;
placing the non-metal heat-proof layer upside down;
the metal shell is placed in an inner hole of the non-metal heat-proof layer;
adjusting the gap between the outer surface of the metal shell and the inner surface of the non-metal heat-proof layer to enable the gap between the outer surface of the metal shell and the inner surface of the non-metal heat-proof layer to be smaller than or equal to a preset gap;
recording the gap value between the outer surface of the metal shell and the inner surface of the non-metal heat-proof layer;
marking the end surface trial sleeve positions of the metal shell and the non-metal heat-proof layer;
taking the metal shell out of the non-metal heat-proof layer;
non-metal heat protection layer and metal casing suit after trying on the suit includes:
configuring curing glue;
coating curing glue on the outer surface of the metal shell and the inner surface of the non-metal heat-proof layer;
aligning the trial sleeving positions of the metal shell and the non-metal heat-proof layer according to the marked end face trial sleeving positions;
sleeving the metal shell into an inner hole of the nonmetal heat-proof layer so that the clearance between the outer surface of the metal shell and the inner surface of the nonmetal heat-proof layer is smaller than or equal to a target clearance;
recording the gap value between the outer surface of the metal shell and the inner surface of the non-metal heat-proof layer;
and cleaning the redundant curing glue solution on the metal shell.
Optionally, sleeving the non-metallic heat shield layer outside the metal shell comprises disposing a curing adhesive between the metal shell and the non-metallic heat shield layer;
curing a composite hold stock comprising:
heating the curing glue to 80 +/-5 ℃, and keeping the temperature for 4 +/-0.1 h;
and cleaning the residual curing adhesive on the end surface of the metal shell and the periphery of the first opening.
Optionally, machining the appearance of the non-metallic heat resistant layer of the composite deck section stock comprises:
roughly machining the appearance of the non-metal heat-proof layer of the composite cabin section raw material, radially machining the non-metal heat-proof layer to a preset size, and axially machining the non-metal heat-proof layer until the non-metal heat-proof layer is connected with the metal shell;
and (3) performing finish machining on the shape of the non-metal heat-proof layer of the composite cabin section raw material, and radially machining the non-metal heat-proof layer to a target size.
Optionally, machining a second opening in the non-metallic heat resistant layer of the composite hold stock comprises: roughly machining a second opening; finish machining the second open pore;
roughing the second opening includes:
roughly machining a second kidney-shaped groove to enable the second kidney-shaped groove to be smaller than the periphery of the first kidney-shaped groove by 5mm allowance, wherein the depth direction of the second kidney-shaped groove is not smaller than the thickness of the nonmetal heat-proof layer;
roughly machining the second opening to enable the second opening to be smaller than the periphery of the first opening by 5mm of allowance, wherein the depth direction of the second opening is not smaller than the thickness of the nonmetal heat-proof layer;
finishing the second bore includes:
finishing the second kidney-shaped groove to enable the second kidney-shaped groove to reach a target size and be flat with the periphery of the first kidney-shaped groove;
the second opening is finish machined to bring the second opening to a target size flush with the first opening perimeter.
Optionally, after the plugging the first opening and before the sleeving the non-metal heat protection layer outside the metal shell, the method further includes:
and a non-metal heat-insulating layer is coated between the metal shell and the non-metal heat-proof layer.
The beneficial effect of this application is as follows: the application provides a processing method of a composite cabin section, which is characterized in that a hole is pre-drilled on a metal shell, so that stress generated in the processing process of the metal cabin section is released, and the metal shell is prevented from deforming in the subsequent processing process of raw materials of the composite cabin section; the shape and the hole of the non-metal heat-proof layer are processed after the raw materials of the composite cabin section are sleeved and formed, and then the filler in the hole of the metal shell is cleaned.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention.
FIG. 1 is a schematic flow chart illustrating the steps of a method of manufacturing a composite deck section according to the present disclosure;
FIG. 2 is a first schematic structural view of a composite deck section corresponding to the method of processing provided herein;
FIG. 3 is a second schematic structural view of a composite deck section corresponding to the method of processing provided herein;
fig. 4 is a third structural schematic diagram of a composite cabin segment corresponding to the processing method provided by the present application.
The attached drawings are marked as follows: 100-metal shell, 111-first kidney-shaped groove, 112-first opening, 113-first lifting hole, 200-nonmetal heat-proof layer, 211-second kidney-shaped groove, 212-second opening, 213-second lifting hole and 300-nonmetal heat-proof layer.
Detailed Description
The embodiment of the application provides a method for processing a composite cabin section, and solves the technical problems that in the related art, the processing difficulty is high, and the precision and the qualified rate are influenced due to the fact that the composite cabin section is easy to deform in processing.
In order to solve the technical problems, the general idea of the embodiment of the present application is as follows:
a method of processing a composite deck section, comprising: processing a first opening on the metal shell, and filling filler in the first opening to block the first opening; sleeving the non-metal heat-proof layer outside the metal shell to form a composite cabin section raw material; curing the composite cabin raw material; processing the appearance of the non-metal heat-proof layer of the composite cabin section raw material; processing a second opening on the non-metal heat-proof layer of the composite cabin raw material, wherein the second opening is arranged corresponding to the first opening; and cleaning the filler in the first open hole to obtain the composite cabin section.
In order to better understand the technical solution, the technical solution will be described in detail with reference to the drawings and the specific embodiments.
Example 1
Referring to fig. 1, the present embodiment discloses a method for processing a composite cabin segment, including: processing a first opening on the metal shell 100, and filling filler in the first opening to block the first opening; sleeving the non-metal heat-proof layer 200 outside the metal shell 100 to form a composite cabin section raw material; curing the composite cabin raw material; processing the appearance of the non-metal heat-proof layer 200 of the composite cabin section raw material; processing a second opening on the non-metal heat-proof layer 200 of the composite cabin raw material, wherein the second opening is arranged corresponding to the first opening; and cleaning the filler in the first open hole to obtain the composite cabin section.
In detail, according to the processing method, the metal shell 100 is pre-perforated before being sleeved, and the corresponding first perforated hole is processed to a preset size, so that the stress generated in the processing process of the metal cabin section is released, and the metal shell 100 is prevented from deforming in the subsequent processing process of the raw material of the composite cabin section.
After the raw materials of the composite cabin section are formed by sleeving, the appearance and the second opening of the non-metal heat-proof layer 200 are processed, so that the influence of sleeving on the machining process of the composite cabin section is reduced. And subsequently cleaning fillers related to the first hole blocking and plugging to obtain the composite cabin section.
In conclusion, by the processing method, the stress generated when the hole is processed on the metal shell 100 is released in advance, and the nonmetal heat-proof layer 200 is processed after sleeving, so that the precision of the composite cabin section is improved, the processing qualification rate of the composite cabin section is ensured, and the reliability of the processing method of the composite cabin section is improved.
It is understood that the metal casing 100 may be an aluminum alloy casing or a titanium alloy casing, and the metal casing 100 is used for providing an installation space for parts or instruments, and plays a role of bearing load; the non-metal heat-proof layer 200 can be made of glass fiber reinforced plastic or a woven body and the like, is used as a protective layer of the aircraft, and has the effects of isolating high temperature generated by friction between the aircraft and the atmosphere in the whole process of the flight of the aircraft and protecting effective load in the aircraft.
Referring to fig. 2, the axial direction of the composite cabin segment in fig. 2 is the left-right direction in the figure, and the shape of the metal casing 100 and the non-metal heat-protection layer 200 may be a combination of a cylindrical shape and a conical shape. Referring to fig. 3, the axial direction of the composite cabin segment of fig. 3 is oriented up and down in the figure, and the shape of the metal casing 100 and the non-metal heat protection layer 200 may be cylindrical.
In some embodiments, referring to fig. 2 and 3, the first opening includes a first kidney-shaped slot 111 disposed at an end of the metal shell 100 and a first opening 112 disposed at a body of the metal shell 100; the second opening hole includes a second kidney-shaped groove 211 provided at an end portion of the non-metallic heat-resistant layer 200 and a second opening 212 provided at a body portion of the non-metallic heat-resistant layer 200. The first and second slots 111 and 211 are mainly used for connecting two adjacent composite cabin sections, and the first and second openings 112 and 212 are used for installing each structural member or equipment in the composite cabin sections.
Combine foretell second trompil and first trompil to correspond the setting, specifically embody: the first kidney groove 111 is concentrically disposed with the second kidney groove 211, and the first opening 112 is concentrically disposed with the second opening 212. The concentric arrangement means that the two holes are arranged on the same central line.
As shown in fig. 2 and 3, the first kidney-shaped grooves 111 are respectively opened at both axial ends, that is, front and rear end portions of the metal shell 100. The first and second slots 111 and 211 may have the same or different shapes.
As shown in fig. 2 and 3, second kidney-shaped grooves 211 are formed at front and rear end portions of the non-metallic heat-shielding layer 200, respectively. The number of the first openings 112 and the second openings 212 may be one or more, even none, and the shapes of the first openings 112 and the second openings 212 may be the same or different.
The first openings are plugged, so that glue liquid in the sleeving process can be prevented from flowing into the first openings, the precision of the first openings on the metal shell 100 is guaranteed, and the flexibility of the processing method of the composite cabin section is improved.
In certain embodiments, plugging the first opening comprises plugging the first kidney slot 111, and plugging the first kidney slot 111 comprises: cleaning the inner wall of the first kidney-shaped groove 111 on the metal shell 100, for example, cleaning with alcohol and airing for not less than 30 min; cutting the pressure-sensitive adhesive tape according to the surface area of the first kidney-shaped groove 111 so that the peripheral allowance of the surface area of the pressure-sensitive adhesive tape is between 10mm and 12 mm; a wooden block cover is prepared according to the size of the bottom of the first kidney-shaped groove 111, so that the margin of the periphery of the wooden block cover is between-1 mm and-1.5 mm, and the margin of the height of the wooden block cover and the depth of the first kidney-shaped groove 111 is between 0mm and-1 mm; uniformly coating the pressure-sensitive adhesive tape on the wooden plug cover, and installing the pressure-sensitive adhesive tape and the wooden plug cover into the first kidney-shaped groove 111; the exposed portion of the pressure sensitive adhesive tape is pressed against the outer surface of the first waist-shaped groove 111, and the excess pressure sensitive adhesive tape is cut off.
It should be noted that the first kidney-shaped slot 111 generally belongs to a blind hole, and the first opening 112 belongs to a through hole. The pressure-sensitive adhesive tape and the first kidney-shaped groove 111 are thus provided with surface area peripheral allowance so that the pressure-sensitive adhesive tape covers not only the groove bottom wall of the first kidney-shaped groove 111 but also the groove side wall of the first kidney-shaped groove 111 after plugging.
With respect to the peripheral margin between 10mm and 12mm, it means that the margin of the pressure sensitive adhesive tape to the side of each face of the spread first kidney groove 111 is between 10mm and 12 mm. The allowance of the wooden block cover and the bottom periphery of the first kidney-shaped groove 111 is between-1 mm and-1.5 mm, which means that the cross section of the wooden block cover is slightly smaller than the groove bottom wall of the first kidney-shaped groove 111, and the allowance of the corresponding sides is between 1mm and 1.5 mm. Regarding the allowance between the height of the wooden block and the depth of the first kidney-shaped groove 111 being 0mm to-1 mm, it means that the height of the wooden block is not greater than the depth of the first kidney-shaped groove 111, and the difference is controlled to be 0 to 1 mm.
In certain embodiments, plugging the first opening comprises plugging the first opening 112, and plugging the first opening 112 comprises: cleaning the inner wall of the first opening 112 on the metal shell 100, for example, cleaning with alcohol and airing for not less than 30 min; the metal blocking cover is matched according to the size of the first opening 112 on the metal shell 100, so that the peripheral allowance of the metal blocking cover is between minus 0.3mm and minus 0.5mm, the cross section of the metal blocking cover is limited to be slightly smaller than the first opening 112, the height of the metal blocking cover and the allowance of the outer surface of the first opening 112 are between 0mm and minus 0.3mm, and the height of the metal blocking cover is limited not to be larger than the depth of the first opening 112; the outer surface of the metal cap is covered with a blue separating film and is fitted into the first opening 112 together.
In some embodiments, the end surface protection of the metal casing 100 is further performed after the first opening is plugged and before the non-metallic heat protection layer 200 is sleeved outside the metal casing 100. Performing end surface protection of the metal case 100 includes: the axial two side end faces of the metal shell 100 are cleaned, for example, cleaned with alcohol, and are air-dried for no less than 30min, and are respectively pasted with a layer of medical adhesive tape.
In some possible embodiments, encasing the non-metallic heat shield 200 outside the metal casing 100 comprises: the non-metal heat-proof layer 200 and the metal shell 100 are in trial assembly; after the trial assembly, the non-metallic heat shield layer 200 is assembled with the metal case 100. The trial sleeve continuously adjusts the relative positions of the metal shell 100 and the non-metal heat-proof layer 200 until the gap between the outer surface of the metal shell 100 and the inner surface of the non-metal heat-proof layer 200 meets the requirement, marks relevant position information and provides help for subsequent trial sleeve. Through trial assembly, the influence of the assembly process on the precision of the composite cabin section is reduced, and the flexibility of the machining method of the composite cabin section is improved.
Specifically, the non-metallic heat shielding layer 200 is assembled with the metal casing 100, and includes: the metal shell 100 is placed upside down and can be optionally placed on a plastic film; the nonmetal heat-proof layer 200 is placed upside down and can be optionally placed on a plastic film; the metal case 100 is placed into the inner hole of the non-metal heat-shielding layer 200; adjusting the gap between the outer surface of the metal shell 100 and the inner surface of the non-metal heat-proof layer 200 to make the gap between the outer surface of the metal shell 100 and the inner surface of the non-metal heat-proof layer 200 less than or equal to a preset gap; recording the gap value between the outer surface of the metal shell 100 and the inner surface of the non-metal heat-proof layer 200; marking the end surface trial sheathing positions of the metal shell 100 and the nonmetal heat-proof layer 200; the metal case 100 is taken out from the non-metallic heat shield layer 200.
Specifically, the fitting of the non-metal heat-proof layer 200 and the metal shell 100 after the trial fitting includes: configuring curing glue; coating the curing adhesive on the outer surface of the metal shell 100 and the inner surface of the non-metal heat-proof layer 200; aligning the trial sleeving positions of the metal shell 100 and the non-metal heat-proof layer 200 according to the marked end face trial sleeving positions; sleeving the metal shell 100 into the inner hole of the nonmetal heat-proof layer 200, so that the clearance between the outer surface of the metal shell 100 and the inner surface of the nonmetal heat-proof layer 200 is less than or equal to the target clearance; recording the gap value between the outer surface of the metal shell 100 and the inner surface of the non-metal heat-proof layer 200; and cleaning the redundant curing glue solution on the metal shell 100. The sleeving method is beneficial to ensuring the precision of the raw materials of the composite cabin.
In certain possible embodiments, encasing the non-metallic heat shield 200 outside the metal casing 100 includes disposing a curing glue between the metal casing 100 and the non-metallic heat shield 200. Curing a composite hold stock comprising: heating the curing glue to 80 +/-5 ℃, and keeping the temperature for 4 +/-0.1 h; and cleaning the residual curing adhesive on the end surface of the metal shell 100 and the periphery of the first opening.
And curing the sleeved metal shell 100 and the non-metal heat-proof layer 200 to enable the non-metal heat-proof layer 200 to be coated on the metal shell 100, so that the reliability of the composite cabin section is improved. In certain embodiments, curing the composite hold stock further comprises: the medical rubberized fabric on the two axial end faces of the metal shell 100 is cleaned.
In some embodiments, the non-metallic heat protection layer 200 of the composite hold stock may be shaped by a combination of rough machining and finish machining, including: roughly machining the shape of the non-metal heat-proof layer 200 of the composite cabin section raw material, radially machining the non-metal heat-proof layer 200 to a preset size, and axially machining the non-metal heat-proof layer to be flat with the metal shell 100; and (3) finishing the appearance of the non-metal heat-proof layer 200 of the composite cabin section raw material, and radially processing the non-metal heat-proof layer 200 to a target size. The preset size is larger than the target size, and the aim is to reserve allowance for fine machining after rough machining, so that the requirement of high-precision machining is met.
In certain possible embodiments, machining a second opening in the non-metallic heat shield layer 200 of the composite hold stock comprises: roughly machining a second opening; after rough machining, the second opening is finish machined. Roughing the second opening includes: roughly machining the second kidney-shaped groove 211 to ensure that the second kidney-shaped groove 211 is reduced by 5mm allowance compared with the periphery of the first kidney-shaped groove 111, and the depth direction is not less than the thickness of the nonmetal heat-proof layer 200; the second opening 212 is roughly processed so that the second opening 212 is reduced by an amount of 5mm from the periphery of the first opening 112 and the depth direction is not less than the thickness of the non-metal heat-shielding layer 200. Finishing the second bore includes: finishing the second kidney-shaped groove 211 to enable the second kidney-shaped groove 211 to reach a target size and be flush with the periphery of the first kidney-shaped groove 111; the second opening 212 is finished such that the second opening 212 is of a target size, flush with the perimeter of the first opening 112.
In certain embodiments, particularly when a wooden cap is used in conjunction with a pressure sensitive adhesive tape to cap the first kidney groove 111, further including depth direction machining to the pressure sensitive adhesive tape with respect to finishing the second kidney groove 211, the first kidney groove 211 is initially cleaned directly during the machining of the second kidney groove 211.
Similarly, when the metal cap is used to cooperate with the blue separation film to block the first opening 112, the finish machining of the second opening 212 further includes depth direction machining to the blue separation film, and the filler of the first opening 112 is preliminarily cleaned.
The method for processing the composite cabin segment of the embodiment comprises the step of cleaning the filler in the first open hole. In some embodiments, cleaning the filler in the first opening includes removing the filler, and deburring the notch of the first kidney-shaped groove 211 of the metal shell 100, and deburring the periphery of the first opening 112 of the metal shell 100.
It is understood that the outer shape of the metal case 100 is matched with the inner shape of the non-metallic heat-shielding layer 200, particularly, the inner surface diameter of the non-metallic heat-shielding layer 200 is larger than the outer surface diameter of the metal case 100. In certain possible embodiments, the method further comprises, before sleeving the metal casing 100 and the non-metallic heat protection layer 200 with a target difference between the diameter of the inner surface of the non-metallic heat protection layer 200 and the diameter of the outer surface of the metal casing 100 to form the composite hold stock: the diameter allowance of the outer surface of the non-metal heat-proof layer 200 is between 4mm and 6mm during rough machining, and then fine machining is carried out to the target size; the height allowance between the nonmetal heat-proof layer 200 and the two end faces of the metal shell 100 is between 20mm and 30 mm.
In some embodiments, after the forming of the non-metallic heat shield layer 200 and before the forming of the second openings of the non-metallic heat shield layer 200, the outer surface of the heat shield layer is also coated with glue to protect the heat shield layer, including the adverse effects on the heat shield layer from the dust environment of the subsequent forming.
Example 2
Referring to fig. 2 and 3, based on the method for processing the composite cabin segment provided in example 1, fig. 2 shows a scheme that the first opening includes a first lifting hole 113, and the second opening includes a second lifting hole 213.
In some embodiments, the first opening further comprises a first lifting hole 113 provided at an end of the metal shell 100; the second opening hole further includes a second lifting hole 213 provided at an end of the non-metallic heat shield layer 200. And the second opening is arranged corresponding to the first opening, and comprises a first lifting hole 113 and a second lifting hole 213 which are arranged concentrically, namely, the center lines are arranged in a superposition way.
The lifting hole is arranged for hoisting the composite cabin section. The axial length of the composite deck section shown in fig. 2 is greater than the axial length of the composite deck section shown in fig. 3, and generally speaking, a lifting hole needs to be arranged when the deck section is longer.
As shown in fig. 2, first lifting holes 113 are provided at front and rear end portions of the metal case 100, and second lifting holes 213 are provided at front and rear end portions of the non-metal heat-protective layer 200; the number may be set to two. The first lifting hole 113 and the second lifting hole 213 may have the same shape or different shapes.
In one description, the metal shell 100 includes an end frame and a skin, the end portion is referred to as the end frame, the body portion is referred to as the skin, that is, the end frame is provided with the first kidney groove 111 and the first lifting hole 113, and the skin is provided with the first opening 112.
In certain embodiments, plugging the first opening comprises plugging the first lifting hole 113. The plugging of the first lifting hole 113 includes: and sealing the first lifting hole 113 on the metal shell 100 by using a sealing rubber strip, so that the height of the sealing rubber strip and the allowance of the surface of the first lifting hole 113 are between 0mm and-1 mm.
Processing a second opening on the non-metal heat-proof layer 200 of the composite cabin section raw material, and further comprising: roughly machining a second lifting hole 213; after rough machining, the second lifting hole 213 is finished.
In one embodiment, roughing the second lifting hole 213 includes: roughly machining the second lifting hole 213 to be 5mm smaller than the bottom hole of the first lifting hole 113, and taking out the filler in the bottom hole of the metal shell 100.
In one embodiment, finishing the second lifting hole 213 comprises: and finishing to the target size of the second lifting hole 213, and enabling the coaxiality of the second lifting hole 213 and the first lifting hole 113 to be less than or equal to 0.1.
In some embodiments, cleaning the filler in the first opening further comprises cleaning the opening burr of the first lifting hole 113 of the metal shell 100.
Example 3
Based on the processing methods provided in embodiments 1 and 2, the present embodiment provides a processing method, referring to fig. 4, after the hole plugging is performed on the first opening, and before the non-metal heat protection layer 200 is sleeved outside the metal shell 100, further including: a non-metallic insulating layer 300 is wrapped between the metal casing 100 and the non-metallic heat shielding layer 200.
In detail, the composite cabin segment comprises a metal casing 100, a non-metal heat-proof layer 200 and a non-metal heat-proof layer 300, wherein the non-metal heat-proof layer 300 is arranged between the metal casing 100 and the non-metal heat-proof layer 200. The non-metallic insulating layer 300 can effectively block heat flow from being transmitted into the metal shell 100, resist ablation of the surface of the metal shell 100 and protect the payload in the aircraft.
The non-metal heat-insulating layer 300 can be aerogel or micro-bead glass fiber reinforced plastic, and the like, and the non-metal heat-insulating layer 300 can be one layer or two or more layers. The shape of the non-metallic insulating layer 300 is matched with that of the non-metallic insulating layer 200, and the openings are correspondingly arranged. Optionally, the openings of the non-metallic insulating layer 300 are machined with the non-metallic heat shield layer 200.
While preferred embodiments of the present invention have been described, additional variations and modifications in those embodiments may occur to those skilled in the art once they learn of the basic inventive concepts. Therefore, it is intended that the appended claims be interpreted as including preferred embodiments and all such alterations and modifications as fall within the scope of the invention.
It will be apparent to those skilled in the art that various changes and modifications may be made in the present invention without departing from the spirit and scope of the invention. Thus, if such modifications and variations of the present invention fall within the scope of the claims of the present invention and their equivalents, the present invention is also intended to include such modifications and variations.
Claims (11)
1. A method of processing a composite deck section, the method comprising:
processing a first opening on a metal shell, and filling filler in the first opening to block the first opening;
sleeving a non-metal heat-proof layer outside the metal shell to form a composite cabin section raw material;
curing the composite cabin material;
processing the appearance of the non-metal heat-proof layer of the composite cabin raw material;
processing a second opening on the non-metal heat-proof layer of the composite cabin raw material, wherein the second opening is arranged corresponding to the first opening;
and cleaning the filler in the first open hole to obtain the composite cabin section.
2. The process of claim 1 wherein said first opening comprises a first kidney slot at an end of said metal shell and a first opening at a body of said metal shell;
the second hole comprises a second kidney-shaped groove arranged at the end part of the non-metal heat-proof layer and a second opening arranged at the body part of the non-metal heat-proof layer;
the second trompil with first trompil corresponds the setting, includes: the first kidney-shaped groove and the second kidney-shaped groove are concentrically arranged, and the first opening and the second opening are concentrically arranged.
3. The process of claim 2 wherein said first opening further comprises a first lifting hole provided at an end of said metal shell;
the second hole also comprises a second lifting hole arranged at the end part of the non-metal heat-proof layer;
the second trompil with first trompil corresponds the setting, includes: the first lifting hole and the second lifting hole are arranged concentrically.
4. The machining method of claim 2, wherein said plugging said first opening comprises plugging said first kidney slot, and wherein said plugging said first kidney slot comprises:
cleaning the inner wall of the first kidney-shaped groove on the metal shell;
cutting the pressure-sensitive adhesive tape according to the surface area of the first kidney-shaped groove so that the allowance of the periphery of the surface area of the pressure-sensitive adhesive tape is between 10mm and 12 mm;
matching a wooden block cover according to the size of the bottom of the first kidney-shaped groove, so that the margin of the periphery of the wooden block cover is between-1 mm and-1.5 mm, and the margin of the height of the wooden block cover and the depth of the first kidney-shaped groove is between 0mm and-1 mm;
uniformly coating the wooden plug cover with the pressure-sensitive adhesive tape, and installing the pressure-sensitive adhesive tape and the wooden plug cover into the first kidney-shaped groove;
pressing the exposed part of the pressure-sensitive adhesive tape on the outer surface of the first kidney-shaped groove, and cutting off the redundant pressure-sensitive adhesive tape;
the pair of plugging the first open hole includes plugging the first opening, the pair of plugging the first opening includes:
cleaning the inner wall of the first opening on the metal shell;
matching a metal blocking cover according to the size of the first opening on the metal shell, so that the allowance of the periphery of the metal blocking cover is between-0.3 mm and-0.5 mm, and the height of the metal blocking cover and the allowance of the outer surface of the first opening are between 0mm and-0.3 mm;
the outer surface of the metal cap is covered with a blue separating film and is installed into the first opening together.
5. The machining method of claim 3, wherein said plugging the first opening includes plugging the first lifting hole, and wherein said plugging the first lifting hole includes:
and sealing the first lifting hole in the metal shell by using a sealing rubber strip so that the height of the sealing rubber strip and the allowance of the surface of the first lifting hole are between 0mm and-1 mm.
6. The process of claim 1, wherein after said plugging said first opening and before said encasing said non-metallic heat shield outside said metal shell, further comprising protecting said metal shell from end surfaces;
the performing end face shielding of the metal shell includes:
and cleaning the end faces of two axial sides of the metal shell, and respectively sticking a layer of medical adhesive tape.
7. The process of claim 1, wherein said encasing said non-metallic heat shield outside said metal casing comprises: the non-metal heat-proof layer is sleeved with the metal shell in a trial mode; after the trial assembly, sleeving the non-metal heat-proof layer with the metal shell;
the non-metal heat protection layer and the metal shell are assembled in a trial mode, and the method comprises the following steps:
the metal shell is placed in an inverted manner;
the nonmetal heat-proof layer is placed upside down;
the metal shell is placed into an inner hole of the non-metal heat-proof layer;
adjusting the gap between the outer surface of the metal shell and the inner surface of the non-metal heat-proof layer to enable the gap between the outer surface of the metal shell and the inner surface of the non-metal heat-proof layer to be smaller than or equal to a preset gap;
recording the gap value between the outer surface of the metal shell and the inner surface of the non-metal heat-proof layer;
marking the end surface trial sleeve positions of the metal shell and the nonmetal heat-proof layer;
taking the metal shell out of the non-metal heat-proof layer;
after the trial assembly, the non-metal heat-proof layer and the metal shell are assembled, comprising:
configuring curing glue;
coating the curing glue on the outer surface of the metal shell and the inner surface of the non-metal heat-proof layer;
aligning the trial sleeving positions of the metal shell and the non-metal heat-proof layer according to the marked trial sleeving position of the end face;
sleeving the metal shell into an inner hole of the non-metal heat-proof layer so that a gap between the outer surface of the metal shell and the inner surface of the non-metal heat-proof layer is smaller than or equal to a target gap;
recording the clearance value between the outer surface of the metal shell and the inner surface of the non-metal heat-proof layer;
and cleaning the redundant curing glue solution on the metal shell.
8. The process of claim 1, wherein encasing said non-metallic heat shield outside said metal casing comprises disposing a curing glue between said metal casing and said non-metallic heat shield;
the curing the composite hold stock comprises:
heating the curing adhesive to 80 +/-5 ℃, and keeping the temperature for 4 +/-0.1 h;
and cleaning the residual curing adhesive on the end surface of the metal shell and the periphery of the first opening.
9. The method of manufacturing of claim 1, wherein said forming of said non-metallic thermal barrier profile of said composite deck section stock comprises:
roughly machining the appearance of the non-metal heat-proof layer of the composite cabin section raw material, radially machining the non-metal heat-proof layer to a preset size, and axially machining the non-metal heat-proof layer until the non-metal heat-proof layer is connected with a metal shell in a flat manner;
and performing finish machining on the shape of the non-metal heat-proof layer of the composite cabin section raw material, and radially machining the non-metal heat-proof layer to a target size.
10. The method of manufacturing of claim 2, wherein said forming a second opening in said non-metallic heat resistant layer of said composite deck section stock comprises: roughly machining the second open hole; finishing the second opening;
said roughing said second opening includes:
roughly machining the second kidney-shaped groove to enable the second kidney-shaped groove to be smaller than the periphery of the first kidney-shaped groove by 5mm of allowance, wherein the depth direction of the second kidney-shaped groove is not smaller than the thickness of the nonmetal heat-proof layer;
roughly machining the second opening to enable the second opening to be smaller than the periphery of the first opening by 5mm of allowance, wherein the depth direction of the second opening is not smaller than the thickness of the nonmetal heat-proof layer;
said finishing said second bore comprises:
finishing the second kidney-shaped groove to enable the second kidney-shaped groove to reach a target size and be flat with the periphery of the first kidney-shaped groove;
finishing the second opening to a target size flush with the first opening perimeter.
11. The process of claim 1, wherein after said plugging said first opening and before said encasing said non-metallic heat shield outside said metal shell, further comprising:
and a non-metal heat insulation layer is coated between the metal shell and the non-metal heat protection layer.
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