CN114951735B

CN114951735B - Processing method of composite cabin section

Info

Publication number: CN114951735B
Application number: CN202210669569.1A
Authority: CN
Inventors: 周海; 李艳梅; 张文鹏
Original assignee: Hubei Sanjiang Aerospace Group Hongyang Electromechanical Co Ltd
Current assignee: Hubei Sanjiang Aerospace Group Hongyang Electromechanical Co Ltd
Priority date: 2022-06-14
Filing date: 2022-06-14
Publication date: 2023-06-16
Anticipated expiration: 2042-06-14
Also published as: CN114951735A

Abstract

The invention discloses a processing method of a composite cabin section, which relates to the technical field of cabin section processing and solves the technical problems of high processing difficulty, influence on accuracy and qualification rate caused by easy deformation of composite cabin section processing in the related technology, and comprises the following steps: processing a first opening on the metal shell, and plugging the first opening; sleeving the nonmetallic heat-proof layer outside the metal shell to form a composite cabin raw material; solidifying the raw materials of the composite cabin section; processing the shape of the nonmetallic heat-proof layer; machining a second opening in the nonmetallic heat-resistant layer; and cleaning the filler in the first opening. The metal shell is pre-perforated, so that the stress generated in the processing process of the metal cabin is released, and the adverse situation that the metal shell is deformed in the subsequent processing process of the composite cabin raw materials is improved; the nonmetallic heat-proof layer is processed after the raw materials of the composite cabin are formed in a sleeved mode, so that the influence of the sleeved mode on the processing process of the composite cabin is reduced, the precision of the composite cabin is improved, and the processing qualification rate is ensured.

Description

Processing method of composite cabin section

Technical Field

The invention relates to the technical field of cabin segment processing, in particular to a processing method of a composite cabin segment.

Background

The composite cabin section consisting of the metal shell and the nonmetallic heat-proof layer is an important part of the aerospace product, the metal shell of the inner layer can provide installation space for different instruments or equipment, and the nonmetallic heat-proof layer of the outer layer is used as a protective layer of the aircraft. However, the diameter of the composite cabin section is generally larger, the skin is thinner, and the rigidity is weaker, so that the cabin section is easy to deform in the processing process, the processing difficulty of the cabin section is increased, the precision of the cabin section is reduced, and the qualification rate of the processing of the cabin section is reduced.

Disclosure of Invention

The application provides a processing method of a composite cabin, which solves the technical problems that in the related art, the composite cabin is easy to deform in processing, so that the processing difficulty is high, and the accuracy and the qualification rate are affected.

The application provides a processing method of a composite cabin section, which comprises the following steps: processing a first open hole on the metal shell, and filling a filler into the first open hole to block the first open hole; sleeving the nonmetallic heat-proof layer outside the metal shell to form a composite cabin raw material; solidifying the raw materials of the composite cabin section; processing the shape of the nonmetallic heat-proof layer of the composite cabin raw material; processing a second opening on the nonmetallic 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 opening to obtain the composite cabin section.

Optionally, the first opening comprises a first kidney-shaped groove arranged at the end part of the metal shell and a first opening arranged at the body part of the metal shell;

the second opening comprises a second kidney-shaped groove arranged at the end part of the nonmetal heat-proof layer and a second opening arranged at the body part of the nonmetal 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 opening further comprises a second lifting hole arranged at the end part of the nonmetallic 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 slot, and plugging the first kidney 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 surface area and the periphery margin of the pressure-sensitive adhesive tape are between 10mm and 12 mm;

the wood blanking cover is matched according to the bottom size of the first kidney-shaped groove, so that the peripheral allowance of the wood blanking cover is between-1 mm and-1.5 mm, and the allowance of the height of the wood blanking cover and the depth of the first kidney-shaped groove is between 0mm and-1 mm;

uniformly coating the pressure-sensitive adhesive tape with a wooden blanking cover, and installing the pressure-sensitive adhesive tape into the first waist-shaped groove together;

pressing the outer surface of the pressure-sensitive adhesive tape on the outer surface of the first kidney-shaped groove, and cutting off redundant pressure-sensitive adhesive tape;

plugging the first opening includes plugging the first opening, and plugging the first opening includes:

cleaning the inner wall of the first opening on the metal shell;

the metal plug is matched according to the first opening size on the metal shell, so that the peripheral allowance of the metal plug is between-0.3 mm and-0.5 mm, and the allowance of the height of the metal plug and the outer surface of the first opening is between 0mm and-0.3 mm;

the outer surface of the metal plug is covered by a blue separation film and is installed into the first opening together.

Optionally, plugging the first opening includes plugging the first lifting hole, and plugging the first lifting hole includes:

and sealing the first lifting hole on the metal shell by using the 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 plugging the first opening and before sleeving the nonmetallic heat-proof layer outside the metal shell, the method further comprises protecting the end face of the metal shell;

performing end face protection of the metal shell includes:

and cleaning the end surfaces of the two axial sides of the metal shell, and respectively attaching a layer of medical adhesive tape.

Optionally, sleeving the nonmetallic heat-resistant layer outside the metal housing includes: the nonmetallic heat-proof layer is in test set with the metallic shell; the nonmetallic heat-proof layer is sleeved with the metal shell after the test sleeve is sleeved;

the nonmetallic heat-proof layer is in test set with the metal casing, includes:

standing the metal shell upside down;

the nonmetallic heat-proof layer is placed upside down;

the metal shell is placed in an inner hole of the nonmetallic heat-proof layer;

adjusting the gap between the outer surface of the metal shell and the inner surface of the nonmetallic heat-proof layer so that the gap between the outer surface of the metal shell and the inner surface of the nonmetallic heat-proof layer is smaller than or equal to a preset gap;

recording the clearance value between the outer surface of the metal shell and the inner surface of the nonmetallic heat-resistant layer;

marking the end surface test sleeve position of the metal shell and the nonmetallic heat-proof layer;

taking the metal shell out of the nonmetallic heat-proof layer;

after the test set, the nonmetallic heat-proof layer is set with the metal shell, which comprises the following steps:

preparing a curing adhesive;

coating the solidified glue on the outer surface of the metal shell and the inner surface of the nonmetallic heat-proof layer;

aligning the test sleeve positions of the metal shell and the nonmetallic heat-proof layer according to the marked end surface test sleeve positions;

sleeving the metal shell into the 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 the target clearance;

and cleaning the redundant solidified glue solution on the metal shell.

Optionally, sleeving the nonmetallic heat-proof layer outside the metal shell comprises setting a curing adhesive between the metal shell and the nonmetallic heat-proof layer;

solidifying the raw materials of the composite cabin section, comprising:

heating the cured adhesive to 80+/-5 ℃, and preserving the temperature for 4+/-0.1 h;

and cleaning the end face of the metal shell and the residual curing adhesive at the periphery of the first opening.

Optionally, processing the profile of the nonmetallic heat-resistant layer of the composite cabin raw material includes:

roughly machining the shape of the nonmetallic heat-proof layer of the composite cabin raw material, radially machining the nonmetallic heat-proof layer to a preset size, and axially machining the nonmetallic heat-proof layer to be connected with the metal shell in a flat manner;

and (3) finishing the shape of the nonmetallic heat-proof layer of the composite cabin raw material, and radially processing the nonmetallic heat-proof layer to a target size.

Optionally, machining a second opening in the nonmetallic heat-resistant layer of the composite cabin raw material, comprising: rough machining a second opening; finishing the second opening;

roughing the second opening comprises:

roughly machining the second kidney-shaped groove to enable the second kidney-shaped groove to be reduced by 5mm compared with the periphery of the first kidney-shaped groove, wherein the depth direction is not smaller than the thickness of the nonmetallic heat-proof layer;

rough machining the second opening to reduce the second opening by 5mm compared with the periphery of the first opening, wherein the depth direction is not less than the thickness of the nonmetallic heat-proof layer;

finishing the second opening includes:

finishing the second kidney-shaped groove to enable the second kidney-shaped groove to reach a target size and be connected with the periphery of the first kidney-shaped groove in a flat manner;

the second opening is finished to the target size to be flush with the periphery of the first opening.

Optionally, after plugging the first hole and before sleeving the nonmetallic heat-proof layer outside the metal shell, the method further comprises:

and a nonmetallic heat insulation layer is coated between the metallic shell and the nonmetallic heat insulation layer.

The beneficial effects of the application are as follows: the application provides a processing method of a composite cabin, which releases stress generated in the processing process of the metal cabin by pre-perforating the metal shell, and avoids deformation of the metal shell caused by the subsequent processing process of the raw materials of the composite cabin; the method reduces the influence of the sleeving on the processing process of the composite cabin, is beneficial to improving the precision of the composite cabin, ensuring the processing qualification rate of the composite cabin and improving the reliability of the processing method of the composite cabin.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are used in the description of the embodiments will be briefly introduced below, and it is obvious that the drawings in the description below are only some embodiments of the present invention.

Fig. 1 is a schematic step flow diagram of a method for processing a composite cabin provided in the present application;

fig. 2 is a first schematic structural diagram of a composite cabin corresponding to the processing method provided in the present application;

fig. 3 is a second schematic structural diagram of a composite cabin corresponding to the processing method provided in the present application;

fig. 4 is a third schematic structural diagram of a composite cabin corresponding to the processing method provided in the present application.

The drawings are marked: 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, 300-nonmetal heat-proof layer.

Detailed Description

The embodiment of the application solves the technical problems that in the related art, the composite cabin is easy to deform in processing, so that the processing difficulty is high, and the accuracy and the qualification rate are affected.

The technical scheme in the embodiment of the application aims to solve the technical problems, and the overall thought is as follows:

a processing method of a composite cabin section comprises the following steps: processing a first open hole on the metal shell, and filling a filler into the first open hole to block the first open hole; sleeving the nonmetallic heat-proof layer outside the metal shell to form a composite cabin raw material; solidifying the raw materials of the composite cabin section; processing the shape of the nonmetallic heat-proof layer of the composite cabin raw material; processing a second opening on the nonmetallic 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 opening to obtain the composite cabin section.

In order to better understand the above technical solutions, the following detailed description will refer to the accompanying drawings and specific embodiments.

Example 1

Referring to fig. 1, the embodiment discloses a method for processing a composite cabin section, which includes: machining a first opening on the metal shell 100, and filling a filler into the first opening to block the first opening; sleeving the nonmetallic heat-proof layer 200 outside the metal shell 100 to form a composite cabin raw material; solidifying the raw materials of the composite cabin section; processing the shape of the nonmetallic heat-proof layer 200 of the composite cabin raw material; processing a second opening on the nonmetallic 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 opening to obtain the composite cabin section.

In detail, the processing method is to pre-open holes on the metal shell 100 before sleeving, and the corresponding first open holes are processed to a preset size, so that the stress generated in the processing process of the metal cabin is released, and the deformation of the metal shell 100 caused by the subsequent processing process of the composite cabin raw materials is avoided.

The shape of the nonmetallic heat-proof layer 200 and the second openings are processed after the raw materials of the composite cabin are formed by sleeving, so that the influence of the sleeving on the processing process of the composite cabin is reduced. And cleaning the filler related to the first hole blocking to obtain the composite cabin.

In summary, by the processing method, the stress generated when the metal shell 100 is perforated is released in advance, and the nonmetallic heat-proof layer 200 is processed after the metal shell is sleeved, so that the precision of the composite cabin is improved, the processing qualification rate of the composite cabin is ensured, and the reliability of the processing method of the composite cabin is improved.

It is to be understood that the metal housing 100 may be an aluminum alloy housing or a titanium alloy housing, etc., and the metal housing 100 is used to provide a mounting space for parts or instruments, etc., and functions to carry a load; the nonmetallic heat-proof layer 200 can be glass fiber reinforced plastic or a woven body, and is used as a protective layer of the aircraft, and the nonmetallic heat-proof layer can isolate high temperature generated by friction between the aircraft and an atmosphere layer in the whole flight process of the aircraft, so as to protect effective load in the aircraft.

Referring to fig. 2, the axial direction of the composite cabin in fig. 2 is directed left and right in the figure, and the shape of the metal housing 100 and the nonmetallic heat-proof layer 200 may be a combination of cylindrical and conical shapes. Referring to fig. 3, the axial direction of the composite deck of fig. 3 is vertically oriented in the figure, and the metal shell 100 and the nonmetallic heat-proof layer 200 may be cylindrical in shape.

In some embodiments, referring to fig. 2 and 3, the first opening includes a first kidney-shaped slot 111 provided at an end of the metal shell 100 and a first opening 112 provided at a body of the metal shell 100; the second opening includes a second kidney slot 211 provided at an end of the non-metallic heat shield layer 200 and a second opening 212 provided at a body of the non-metallic heat shield layer 200. The first kidney-shaped groove 111 and the second kidney-shaped groove 211 are mainly used for connecting two adjacent composite cabin sections, and the first opening 112 and the second opening 212 are used for installing structural components or devices in the composite cabin sections.

The second opening and the first opening are correspondingly arranged in combination, and the concrete steps are as follows: the first kidney-shaped groove 111 is disposed concentrically with the second kidney-shaped groove 211, and the first opening 112 is disposed concentrically 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 grooves 111 are formed at both axial ends of the metal case 100, that is, front and rear ends. The first and

second kidney grooves

111 and 211 may have the same shape or different shapes.

As shown in fig. 2 and 3, the second kidney grooves 211 are respectively opened at the front and rear end portions of the nonmetallic heat-proof layer 200. While the number of the first openings 112 and the second openings 212 may be one or more, or even none, the shapes of the first openings 112 and the second openings 212 may be the same or different.

The above-mentioned plugging of the first openings can prevent glue solution in the sleeving process from flowing into each first opening, and ensure the accuracy of each first opening on the metal shell 100, and improve the flexibility of the processing method of the composite cabin.

In certain embodiments, plugging the first aperture 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 30min; cutting the pressure-sensitive adhesive tape according to the surface area of the first waist-shaped groove 111 so that the surface area of the pressure-sensitive adhesive tape is 10mm to 12mm in the peripheral margin; the wood blanking cover is matched according to the bottom size of the first waist-shaped groove 111, so that the peripheral allowance of the wood blanking cover is between-1 mm and-1.5 mm, and the allowance of the height of the wood blanking cover and the depth of the first waist-shaped groove 111 is between 0mm and-1 mm; uniformly coating the pressure-sensitive adhesive tape with the wooden blanking cover and installing the pressure-sensitive adhesive tape into the first waist-shaped groove 111 together; the pressure-sensitive adhesive tape is partially pressed against the outer surface of the first kidney-shaped groove 111, and the excess pressure-sensitive adhesive tape is cut off.

It should be noted that, the first kidney-shaped groove 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 a surface area peripheral margin 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 hole blocking.

The allowance of the circumference is between 10mm and 12mm, meaning that the allowance of the side of each face of the pressure-sensitive adhesive tape and the spread first kidney-shaped groove 111 is between 10mm and 12 mm. The remaining amount of the bottom circumference of the wooden blanking cover and the first kidney-shaped groove 111 is between-1 mm and-1.5 mm, and the wooden blanking cover is slightly smaller than the groove bottom wall of the first kidney-shaped groove 111 in cross section, and the remaining amount of each corresponding side is between 1mm and 1.5 mm. The allowance between the height of the wooden blanking cover and the depth of the first kidney-shaped groove 111 is between 0mm and-1 mm, which means that the height of the wooden blanking cover is not more than the depth of the first kidney-shaped groove 111, and the difference is controlled between 0 and 1mm.

In certain embodiments, plugging the first aperture 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 30min; the metal plug is prepared according to the size of the first opening 112 on the metal shell 100, so that the peripheral allowance of the metal plug is between-0.3 mm and-0.5 mm, the cross section of the metal plug is limited to be slightly smaller than the first opening 112, the allowance of the height of the metal plug and the outer surface of the first opening 112 is between 0mm and-0.3 mm, and the height of the metal plug is limited to be not greater than the depth of the first opening 112; the outer surface of the metal plug is covered with a blue separator film and fitted into the first opening 112 together.

In some embodiments, the end protection of the metal shell 100 is performed after plugging the first opening and before sleeving the nonmetallic heat-proof layer 200 outside the metal shell 100. Performing end face protection of the metal shell 100 includes: the two axial side end surfaces of the metal shell 100 are cleaned, for example, cleaned by alcohol respectively, and then are dried for at least 30min, and a layer of medical adhesive tape is respectively attached.

In certain embodiments, encasing the nonmetallic heat shield 200 outside the metallic shell 100 comprises: the nonmetallic heat-proof layer 200 is in test fit with the metal shell 100; after the test set, the nonmetallic heat-proof layer 200 is set with the metallic casing 100. The test sleeve is to continuously adjust the relative positions of the metal shell 100 and the nonmetal heat-proof layer 200 until the clearance between the outer surface of the metal shell 100 and the inner surface of the nonmetal heat-proof layer 200 meets the requirement, mark the relevant position information, and provide help for the subsequent test sleeve. By means of trial assembly, the influence of the assembly process on the precision of the composite cabin is reduced, and the flexibility of the processing method of the composite cabin is improved.

Specifically, the non-metallic heat protection layer 200 is fitted with the metal case 100, including: the metal shell 100 is placed upside down, and optionally placed on a plastic film; the nonmetallic heat-proof layer 200 is placed upside down, and optionally placed on a plastic film; the metal shell 100 is placed into the inner bore of the nonmetallic heat shield 200; adjusting the gap between the outer surface of the metal shell 100 and the inner surface of the nonmetallic heat-proof layer 200 so that the gap between the outer surface of the metal shell 100 and the inner surface of the nonmetallic heat-proof layer 200 is 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 nonmetallic heat-proof layer 200; marking the end surface test sleeve position of the metal shell 100 and the nonmetallic heat-proof layer 200; the metal shell 100 is removed from within the nonmetallic heat shield 200.

Specifically, the non-metallic heat protection layer 200 is sleeved with the metal shell 100 after the test set includes: preparing a curing adhesive; coating the curing glue on the outer surface of the metal shell 100 and the inner surface of the nonmetallic heat-proof layer 200; aligning the test sleeve positions of the metal shell 100 and the nonmetallic heat-proof layer 200 according to the marked end surface test sleeve positions; sleeving the metal shell 100 into the inner hole of the nonmetal heat-proof layer 200 so that the gap 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 gap; recording the gap value between the outer surface of the metal shell 100 and the inner surface of the nonmetallic heat-proof layer 200; the metal shell 100 is cleaned of excess cured glue solution. The method is beneficial to ensuring the precision of the raw materials of the composite cabin.

In some embodiments, encasing the non-metallic heat shield 200 outside the metal housing 100 includes disposing a cured glue between the metal housing 100 and the non-metallic heat shield 200. Solidifying the raw materials of the composite cabin section, comprising: heating the cured adhesive to 80+/-5 ℃, and preserving the temperature for 4+/-0.1 h; the end face of the metal shell 100 and the periphery of the first opening are cleaned of residual cured glue.

The metal shell 100 and the nonmetallic heat-proof layer 200 which are sleeved are solidified, so that the nonmetallic heat-proof layer 200 is covered on the metal shell 100, and the reliability of the composite cabin section is improved. In certain embodiments, the cured composite cabin raw material further comprises: medical adhesive tapes on both axial end surfaces of the metal shell 100 are cleaned.

In some embodiments, the shape of the nonmetallic heat-resistant layer 200 of the composite cabin raw material can be formed by adopting a rough machining and finishing mode, and the method specifically comprises the following steps: rough machining the shape of the nonmetallic heat-proof layer 200 of the composite cabin raw material, radially machining the nonmetallic heat-proof layer 200 to a preset size, and axially machining the nonmetallic heat-proof layer to be connected with the metal shell 100 in a flat mode; and (3) finishing the shape of the nonmetallic heat-proof layer 200 of the composite cabin raw material, and radially machining the nonmetallic heat-proof layer 200 to a target size. The preset size is larger than the target size, and the allowance is reserved for finish machining after rough machining, so that the requirement of high-precision machining is met.

In certain embodiments, machining a second opening in the nonmetallic heat-shield 200 of the composite cabin raw material includes: rough machining a second opening; after rough machining, finishing the second opening. Roughing the second opening comprises: the second kidney-shaped groove 211 is rough machined so that the second kidney-shaped groove 211 is reduced by 5mm from the periphery of the first kidney-shaped groove 111, and the depth direction is not less than the thickness of the nonmetallic heat-proof layer 200; the second opening 212 is rough-processed such that the second opening 212 is reduced by 5mm from the periphery of the first opening 112 by a margin, and the depth direction is not less than the thickness of the nonmetallic heat-shielding layer 200. Finishing the second opening includes: finishing the second kidney-shaped groove 211 so that the second kidney-shaped groove 211 is leveled with the circumference of the first kidney-shaped groove 111 to a target size; the second opening 212 is finished so that the second opening 212 is to a target size, level with the perimeter of the first opening 112.

In some embodiments, particularly when the wooden blanking cover is matched with the pressure-sensitive adhesive tape to block the first kidney-shaped groove 111, the process of finishing the second kidney-shaped groove 211 further comprises the depth direction processing to the pressure-sensitive adhesive tape, and the filling material of the first kidney-shaped groove 211 is primarily cleaned in the process of processing the second kidney-shaped groove 211.

Similarly, when the first opening 112 is plugged with a metal plug and a blue separation film, the finishing of the second opening 212 further includes a deep-processing to the blue separation film, and the preliminary cleaning of the filler of the first opening 112 is performed.

The processing method of the composite cabin section of the embodiment comprises the step of cleaning the filler in the first opening. In some embodiments, cleaning the filler within the first opening includes removing the filler and deburring the first kidney slot 211 slot opening of the metal shell 100 and deburring the perimeter of the first opening 112 of the metal shell 100.

It is understood that the outer shape of the metal shell 100 is adapted to the inner shape of the non-metal heat-shielding layer 200, specifically that the diameter of the inner surface of the non-metal heat-shielding layer 200 is larger than the diameter of the outer surface of the metal shell 100. In certain embodiments, the non-metallic heat protection layer 200 has a target difference between the diameter of the inner surface and the diameter of the outer surface of the metal shell 100, and the metal shell 100 is sleeved with the non-metallic heat protection layer 200 to form the composite cabin raw material, further comprising: the diameter allowance of the outer surface of the nonmetallic heat-proof layer 200 is between 4mm and 6mm during rough machining, and then the nonmetallic heat-proof layer is finished to the target size; the height allowance between the nonmetallic heat-proof layer 200 and the two end surfaces of the metal shell 100 is 20mm to 30 mm.

In some embodiments, after the outline of the nonmetallic heat-proof layer 200 is processed, and before the second opening of the nonmetallic heat-proof layer 200 is processed, the outer surface of the heat-proof layer is further coated with glue, which has the effect of protecting the heat-proof layer, including adverse effects on the heat-proof layer for dust environment of subsequent processing.

Example 2

Referring to fig. 2 and 3 in comparison, fig. 2 shows a solution in which the first opening includes a first lifting hole 113 and the second opening includes a second lifting hole 213.

In certain embodiments, the first opening further comprises a first lifting hole 113 provided at an end of the metal shell 100; the second opening further includes a second lifting hole 213 provided at an end of the nonmetallic heat shield 200. And the arrangement of the second opening corresponding to the first opening includes that the first lifting hole 113 and the second lifting hole 213 are concentrically arranged, i.e. the center line is coincident.

The lifting hole is arranged for lifting the composite cabin. The axial length of the composite deck section shown in fig. 2 is longer than that of the composite deck section shown in fig. 3, and generally, lifting holes are required when the deck section is longer.

As shown in fig. 2, the first lifting hole 113 is provided at the front and rear ends of the metal case 100, and the second lifting hole 213 is provided at the front and rear ends of the nonmetallic heat-proof 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 may have different shapes.

In one form, the metal shell 100 comprises an end frame and a skin, the end frame being referred to as the end frame, the body being referred to as the skin, i.e. the end frame is provided with a first kidney slot 111 and a first lifting hole 113, and the skin is provided with a first opening 112.

In some embodiments, plugging the first aperture includes plugging the first lifting aperture 113. Plugging the first lifting hole 113 includes: the first lifting hole 113 on the metal shell 100 is sealed with 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.

Machining a second opening in the nonmetallic heat-resistant layer 200 of the composite cabin raw material, further comprising: roughing the second lifting hole 213; after the rough machining, the second lifting hole 213 is finished.

In one embodiment, roughing the second lifting hole 213 includes: the second lifting hole 213 is rough machined to be 5mm smaller than the bottom hole of the first lifting hole 113, and the filler in the bottom hole of the metal case 100 is taken out.

In one embodiment, finishing the second lifting hole 213 includes: finish machining to the second lifting hole 213 to a target size, and making the coaxiality of the second lifting hole 213 and the first lifting hole 113 less than or equal to 0.1.

In certain embodiments, cleaning the filler within the first opening further comprises cleaning burrs of the aperture 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 plugging the first hole and before sleeving the nonmetallic heat-proof layer 200 outside the metal casing 100, further including: a nonmetallic heat insulating layer 300 is coated between the metallic casing 100 and the nonmetallic heat shielding layer 200.

In detail, the composite deck includes a metal shell 100, a nonmetallic heat-shielding layer 200, and a nonmetallic heat-shielding layer 300, and the nonmetallic heat-shielding layer 300 is disposed between the metal shell 100 and the nonmetallic heat-shielding layer 200. The non-metallic insulating layer 300 is effective to retard heat flow transfer into the metal shell 100, resist ablation of the surface of the metal shell 100, and protect the payload within the aircraft.

The nonmetallic heat insulation layer 300 can be selected from aerogel or bead glass fiber reinforced plastic, etc., and the nonmetallic heat insulation layer 300 can be one layer or two layers or more. The shape of the nonmetallic heat-proof layer 300 is matched with the shape of the nonmetallic heat-proof 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. It is therefore intended that the following claims be interpreted as including the 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 modifications and variations can be made to the present invention without departing from the spirit or scope of the invention. Thus, it is intended that the present invention also include such modifications and alterations insofar as they come within the scope of the appended claims or the equivalents thereof.

Claims

1. A method of machining a composite deck, the method comprising:

processing a first open hole on a metal shell, and filling a filler into the first open hole to block the first open hole;

sleeving a nonmetallic heat-proof layer outside the metal shell to form a composite cabin raw material;

solidifying the composite cabin raw material;

processing the shape of the nonmetallic heat-proof layer of the composite cabin raw material;

processing a second opening on the nonmetallic 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 opening to obtain the composite cabin section, wherein any pair of connecting holes formed by connecting the first opening and the second opening concentrically are used for installing instruments or equipment.

2. The method of processing of claim 1, wherein the first opening comprises a first kidney slot provided at an end of the metal shell and a first opening provided at a body of the metal shell;

the second opening corresponds to the first opening and comprises: 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 method of processing of claim 2, wherein the first opening further comprises a first lifting hole provided at an end of the metal shell;

the second opening corresponds to the first opening and comprises: the first lifting hole and the second lifting hole are concentrically arranged.

4. The method of processing of claim 2, wherein plugging the first opening comprises plugging the first kidney slot, the plugging the first kidney slot comprising:

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 surface area and the peripheral allowance of the pressure-sensitive adhesive tape are between 10mm and 12 mm;

uniformly coating the pressure-sensitive adhesive tape on the wooden blanking cover, and installing the pressure-sensitive adhesive tape in the first waist-shaped groove together;

pressing the outer surface of the first kidney-shaped groove with the pressure-sensitive adhesive tape out of the belt, and cutting off the excess pressure-sensitive adhesive tape;

the plugging of the first opening includes plugging the first opening, and the plugging of the first opening includes:

cleaning the inner wall of the first opening on the metal shell;

the outer surface of the metal blanking cover is covered by a blue separation film and is installed in the first opening together.

5. The method of processing of claim 3, wherein plugging the first opening comprises plugging the first lifting hole, the plugging the first lifting hole comprising:

and sealing the first lifting hole on 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 method of claim 1, wherein said plugging said first opening and said sleeving said nonmetallic heat shield around said metallic housing further comprises protecting an end face of said metallic housing;

the performing the end face protection of the metal shell comprises:

7. The method of processing of claim 1, wherein the encasing the nonmetallic heat shield outside the metallic housing comprises: the nonmetallic heat-proof layer is in fit with the metal shell; after the test set, the nonmetallic heat-proof layer is set with the metal shell;

the nonmetallic heat-proof layer is in fit with the metal shell, and comprises:

the metal shell is placed upside down;

the nonmetallic heat-proof layer is placed upside down;

the metal shell is placed into an inner hole of the nonmetallic heat-proof layer;

recording a gap value between the outer surface of the metal shell and the inner surface of the nonmetallic heat-proof layer;

marking the end face test sleeve positions of the metal shell and the nonmetal heat-proof layer;

removing the metal shell from within the nonmetallic heat shield;

after the test set, the nonmetallic heat-proof layer is set with the metal shell, and the method comprises the following steps:

preparing a curing adhesive;

coating the curing glue on the outer surface of the metal shell and the inner surface of the nonmetallic heat-proof layer;

sleeving the metal shell into the inner hole of the nonmetallic heat-proof layer, so that the gap between the outer surface of the metal shell and the inner surface of the nonmetallic heat-proof layer is smaller than or equal to a target gap;

and cleaning the redundant solidified glue solution on the metal shell.

8. The method of claim 1, wherein the sleeving the nonmetallic heat-resistant layer outside the metallic shell comprises disposing a cured glue between the metallic shell and the nonmetallic heat-resistant layer;

the curing of the composite cabin raw material comprises:

heating the curing adhesive to 80+/-5 ℃, and preserving heat for 4+/-0.1 h;

9. The method of processing of claim 1, wherein said processing the profile of the nonmetallic heat-resistant layer of the composite cabin raw material comprises:

roughly machining the shape of the nonmetallic heat-proof layer of the composite cabin raw material, radially machining the nonmetallic heat-proof layer to a preset size, and axially machining the nonmetallic heat-proof layer to be connected with a metal shell in a flat mode;

and finishing the appearance of the nonmetallic heat-proof layer of the composite cabin raw material, and radially processing the nonmetallic heat-proof layer to a target size.

10. The method of processing of claim 2, wherein said processing a second opening in said nonmetallic heat-shield layer of said composite pod material comprises: roughing the second opening; finishing the second opening;

the roughing the second opening includes:

rough machining the second kidney-shaped groove to enable the second kidney-shaped groove to be reduced by 5mm compared with the periphery of the first kidney-shaped groove, wherein the depth direction is not smaller than the thickness of the nonmetallic heat-proof layer;

rough machining the second opening to enable the second opening to be reduced by 5mm compared with the periphery of the first opening, wherein the depth direction is not smaller than the thickness of the nonmetallic heat-proof layer;

the finishing the second opening includes:

finishing the second kidney-shaped groove to enable the second kidney-shaped groove to be in a target size and be leveled with the periphery of the first kidney-shaped groove;

the second opening is finished to a target size to level with the first opening periphery.

11. The method of claim 1, wherein after plugging the first opening and before sleeving the nonmetallic heat-resistant layer outside the metal shell, further comprising: