Composite material cabin containing inner flow channel and assembly process of composite material cabin

Abstract

The invention relates to the technical field of assembly of composite material parts, in particular to a composite material cabin with an inner runner and an assembly process of the composite material cabin. The cabin body comprises a cabin body main body and an end frame, an installation opening is formed in one end of the cabin body to install the end frame, the end frame comprises a sealing cover and an annular end frame assembling face, the end frame assembling face is perpendicular to the sealing cover, an unsealed annular groove is formed in the inner wall of the cabin body, the cabin body and the end frame are assembled to seal the annular groove, and the sealed annular groove forms an inner flow channel. The coaxiality of an end frame and a cabin body is controlled in the mode that the assembling face of the end frame and the cabin body are coated with sealant in a segmented and combined mode and a tool is positioned, the end frame is axially inserted into the cabin body through a positioning tool, a sealing ring is used for preventing the sealant from flowing into an inner runner groove, and it is guaranteed that assembling is completed through the coaxiality of the end frame and the cabin body. The sealant is uniform in thickness. According to the technology, the maintainability of the composite product with the inner runner is improved, and convenience is brought to molding of the composite product.

Description

Technical Field

[0001] The invention relates to the technical field of composite material parts assembly, and in particular to a composite material cabin body containing an inner flow channel and an assembly process thereof. Background Art

[0002] As aerospace composite products develop towards the trend of structural and functional integration, the internal structure of composite products is becoming more and more complex. The advantage of realizing the internal flow channel by pre-embedded pipelines in the composite skin is that it realizes the structural and functional integration of composite products, which plays an important role in the overall weight reduction optimization and spatial layout optimization of composite products. The disadvantage is that the production process of composite products is complicated, and the products are solidified and formed at one time. Once the internal flow channel is damaged or blocked, subsequent after-sales maintenance cannot be carried out. For expensive composite products, maintainability is one of the important criteria for measuring the design of a composite product, and it is also the design pursuit of the product. In order to improve the maintainability of composite products with internal flow channels and to facilitate the molding of composite products, the internal flow channel part of the composite product is currently split into two composite parts for sealing and assembly. This method has high requirements for the sealing and assembly process, and the sealant is easy to flow into the internal flow channel groove to form excess. Summary of the invention

[0003] In order to consider the maintainability of expensive composite products after sales, the embodiment of the present invention provides a composite cabin with an inner flow channel and its assembly process, in which the annular groove on the inner wall of the cabin body is sealed to form an inner flow channel by means of combined assembly, and a sealing ring is used to prevent the sealant from flowing into the inner flow channel groove. This method not only facilitates the disassembly and maintenance of the composite product in the later stage, but also brings convenience to the molding of composite product parts.

[0004] In a first aspect, an embodiment of the present invention provides a composite cabin, including a cabin body and an end frame;

[0005] A mounting port is provided at one end of the cabin body to install the end frame, and the end frame includes a cover and an annular end frame assembly surface, the end frame assembly surface is vertically arranged on the cover, and an annular groove for placing pipelines is provided on the inner wall of one end of the cabin body close to the mounting port, and sealants are respectively coated on a preset position of the end frame assembly surface and a side of the annular groove away from the mounting port, so that after the end frame assembly surface is fully inserted into the mounting port, two sealants are respectively located on both sides of the annular groove, so that the sealants at both ends and the outer wall of the end frame assembly surface cooperate to seal the annular groove.

[0006] In one possible design, the difference between the inner radius of the inner wall of the hull body and the outer radius of the end frame assembly surface is a preset distance, so that after the end frame is coaxially assembled into the hull body, there is a gap between the end frame assembly surface and the inner diameter of the hull body to provide space for the sealant layer.

[0007] In one possible design, before assembly, the thickness of the two layers of sealant is greater than the preset distance, so that after the end frame is assembled into the cabin body, the two layers of sealant are fully squeezed and fitted with the inner wall of the cabin body on both sides and the outer wall of the end frame assembly surface.

[0008] In a possible design, a sealing ring is provided on one side of the annular groove close to the installation port, and the height of the sealing ring protruding from the cabin body should be greater than the thickness of the applied sealant, so that the sealing ring can block the sealant during the assembly process to prevent the sealant coated on the end frame assembly surface from entering the annular groove during the assembly process.

[0009] In a possible design, after the end frame and the cabin body are assembled, countersunk screws are passed through the end frame assembly surface and the cabin body in sequence to fix the two.

[0010] In a possible design, the countersunk screw is located at two layers of sealant.

[0011] In a possible design, the cover is provided with an operation hole, and the operation hole is used to allow manual labor or a device to enter the interior of the cabin body to install the countersunk screw.

[0012] In a second aspect, an embodiment of the present invention further provides a method for preparing a composite cabin body, which is used to prepare any of the composite cabin bodies described above, and the preparation method comprises:

[0013] Applying an adhesive primer on the end frame assembly surface and the side of the annular groove away from the mounting opening;

[0014] After the bonding primer is dried, applying a sealant on the bonding primer;

[0015] Inserting the end frame into the cabin body through the installation opening;

[0016] Passing the end frame assembly surface and the cabin body through countersunk screws in sequence to fix the two;

[0017] Carry out curing treatment.

[0018] In a possible design, inserting the end frame into the cabin body through the installation opening includes:

[0019] The end frame is inserted into the cabin body through the installation port by using a positioning tool so that the end frame and the cabin body are coaxial; wherein the positioning tool comprises a guide rail, a positioning plate and a positioning ring, the positioning plate is fixed to the end frame by bolts, the positioning ring is sleeved on the outside of the cabin body, the guide rail connects the positioning plate and the positioning ring so that the positioning plate and the positioning ring are coaxial and can slide along the axis.

[0020] In a possible design, the countersunk screws sequentially penetrate the end frame assembly surface and the cabin body to fix the two, including:

[0021] After the end frame reaches the preset position, the countersunk screws are initially tightened;

[0022] When the sealant is in a semi-cured state, tighten the countersunk screws again.

[0023] Compared with the prior art, the present invention has at least the following beneficial effects:

[0024] The technology provided by this application improves the maintainability of composite products with internal flow channels, and also brings convenience to the molding of composite products, and provides a feasible solution for the production of composite products with internal flow channels. Specifically, the cabin body is provided with an annular groove. In order to achieve the purpose of sealing the annular groove space, an end frame assembly surface is provided on the cover. After the end frame assembly surface is inserted into the cabin body, the pre-coated sealant is respectively located on both sides of the annular groove, and the two sections of sealant cooperate with the end frame assembly surface to achieve the sealing of the annular groove. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0026] Figure 1 is a structural schematic diagram of a composite material cabin provided by an embodiment of the present invention;

[0027] Figure 2 is a schematic diagram of an installation structure of a composite material cabin provided by an embodiment of the present invention;

[0028] Figure 3 It is a schematic diagram of the partial structure of a composite material cabin provided in an embodiment of the present invention.

[0029] In the figure:

[0030] 1-cover; 2-end frame assembly surface; 3-cabin body; 4-sealant; 5-annular groove; 6-sealing ring; 7-positioning plate; 8-positioning ring; 9-guide rail; 10-countersunk screw; 11-bolt. DETAILED DESCRIPTION

[0031] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments in the present invention, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the present invention.

[0032] In the description of the embodiments of the present invention, unless otherwise clearly specified and limited, the terms "first" and "second" are used for descriptive purposes only and cannot be understood as indicating or implying relative importance; unless otherwise specified or explained, the term "multiple" refers to two or more; the terms "connected" and "fixed" should be understood in a broad sense, for example, "connected" can be a fixed connection, a detachable connection, an integral connection, or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0033] In the description of this specification, it should be understood that the directional words such as "upper" and "lower" described in the embodiments of the present invention are described at the angles shown in the drawings and should not be understood as limiting the embodiments of the present invention. In addition, in the context, it should also be understood that when it is mentioned that an element is connected to another element "upper" or "lower", it can not only be directly connected to another element "upper" or "lower", but also indirectly connected to another element "upper" or "lower" through an intermediate element.

[0034] like Figures 1 to 3 As shown, an embodiment of the present invention provides a composite cabin, including a cabin body 3 and an end frame;

[0035] An installation port is set at one end of the cabin body 3 to install the end frame. The end frame includes a cover 1 and an annular end frame assembly surface 2. The end frame assembly surface 2 is vertically arranged on the cover 1. An annular groove 5 for placing the pipeline is set on the inner wall of one end of the cabin body 3 close to the installation port. The preset position of the end frame assembly surface 2 and the side of the annular groove 5 away from the installation port are respectively coated with sealants 4. After the end frame assembly surface 2 is fully inserted into the installation port, the two sealants 4 are respectively located on both sides of the annular groove 5, so that the sealants 4 at both ends and the outer wall of the end frame assembly surface 2 cooperate to seal the annular groove 5.

[0036] The technology provided by this application improves the maintainability of composite products with internal flow channels, and also brings convenience to the molding of composite products, and provides a feasible solution for the production of composite products with internal flow channels. Specifically, the cabin body is provided with an annular groove 5. In order to achieve the purpose of sealing the annular groove 5, an end frame assembly surface 2 is provided on the cover 1. After the end frame assembly surface 2 is inserted into the cabin body 3, the pre-coated sealant 4 is respectively located on both sides of the annular groove 5. The two sections of sealant 4 cooperate with the end frame assembly surface 2 to achieve the sealing of the annular groove 5.

[0037] In some embodiments of the present invention, the difference between the inner radius of the inner wall of the cabin body 3 and the outer radius of the end frame assembly surface 2 is a preset distance, so that after the end frame is coaxially assembled into the cabin body 3, there is a gap between the end frame assembly surface 2 and the inner diameter of the cabin body 3 to provide space for the sealant 4 layer.

[0038] In this embodiment, in order to achieve sealing through the sealant 4, the sealant 4 needs to have a certain thickness, so it is necessary to reserve space for the sealant 4 according to demand.

[0039] In some embodiments of the present invention, before assembly, the thickness of the two layers of sealant 4 is greater than a preset distance, so that after the end frame is assembled into the cabin body 3, the two layers of sealant 4 are fully squeezed and fitted with the inner walls of the cabin body 3 on both sides and the outer wall of the end frame assembly surface 2.

[0040] In this embodiment, in order to make the sealant 4 fully contact the walls to be sealed on both sides, the sealant 4 needs to be slightly larger than the preset distance, so that the walls on both sides squeeze the sealant 4, and then fully contact, bond and seal.

[0041] In some embodiments of the present invention, a sealing ring 6 is provided on one side of the annular groove 5 close to the installation port, and the height of the sealing ring 6 protruding from the main body of the cabin should be greater than the thickness of the applied sealant, so that the sealing ring 6 can achieve the function of blocking the sealant during the assembly process to prevent the sealant 4 coated on the end frame assembly surface 2 from entering the annular groove 5 during the assembly process.

[0042] In this embodiment, in order to prevent the sealant 4 from flowing into the annular groove 5, a sealing ring 6 needs to be provided on the insertion side of the annular groove 5. The sealing ring 6 has a sufficient thickness so that extrusion is formed between the sealing ring 6 and the end frame assembly surface 2, thereby achieving the effect of blocking the sealant 4 on the end frame assembly surface 2 during the insertion process.

[0043] In some embodiments of the present invention, after the end frame and the cabin body 3 are assembled, the countersunk screws 10 are passed through the end frame assembly surface 2 and the cabin body 3 in sequence to fix the two.

[0044] In some embodiments of the present invention, the countersunk screws 10 are located at the two layers of sealant 4 .

[0045] In some embodiments of the present invention, the cover 1 is provided with an operation hole, and the operation hole is used to allow manual labor or a device to enter the interior of the cabin body 3 to install the countersunk screw 10 .

[0046] In a second aspect, an embodiment of the present invention further provides assembly process parameters of a composite cabin body with an inner flow channel, and the specific parameters include:

[0047] Apply adhesive primer to the end frame assembly surface 2 and the side of the annular groove 5 away from the installation opening;

[0048] After the bonding primer is dried, a sealant 4 is applied on the bonding primer;

[0049] Insert the end frame into the cabin body 3 through the installation opening;

[0050] The countersunk screws 10 are passed through the end frame assembly surface 2 and the cabin body 3 in sequence to fix the two;

[0051] Carry out curing treatment.

[0052] In some embodiments of the present invention, inserting the end frame into the cabin body 3 through the installation opening includes:

[0053] The end frame is inserted into the cabin body 3 from the installation port by using the positioning tool so that the end frame and the cabin body 3 are coaxial; wherein the positioning tool comprises a guide rail 9, a positioning plate 7 and a positioning ring 8, the positioning plate 7 is fixed to the end frame by bolts, the positioning ring 8 is sleeved on the outside of the cabin body 3, the guide rail 9 is penetrated by the positioning plate 7 and the positioning ring 8, so that the positioning plate 7 and the positioning ring 8 are coaxial, and the positioning plate 7 and the positioning ring 8 can slide along the axis.

[0054] In some embodiments of the present invention, the countersunk screws 10 are passed through the end frame assembly surface 2 and the cabin body 3 in sequence to fix the two, including:

[0055] After the end frame reaches the preset position, preliminarily tighten the countersunk screw 10;

[0056] When the sealant is in a semi-cured state, tighten the countersunk screw 10 again.

[0057] Specifically, the composite material end frame and the end frame assembly surfaces and assembly holes of the composite material cabin body 3 are machined according to the requirements of the drawings.

[0058] Machine the groove for storing the sealing ring 6 in the composite cabin according to the drawing requirements.

[0059] After the end frame assembly surface, assembly holes and grooves are processed, the flash edges are polished to ensure that there are no visible burrs.

[0060] Wipe the end frame assembly surface, assembly holes and grooves with a cloth dipped in acetone. The cloth must be free of visible particles.

[0061] Place the sealing ring 6 in the groove of the composite cabin body 3 end frame assembly surface. When placing the sealing ring 6, the groove of the composite end frame assembly surface should be blown with an air gun, and the groove should be wiped clean with a cloth dipped in acetone. Before placing the sealing ring 6, it should be wiped clean with acetone and dried. The height of the sealing ring 6 protruding from the cabin body should be greater than the thickness of the applied sealant to ensure the sealing ring 6's blocking effect on the sealant.

[0062] The composite material end frame and the composite material cabin body 3 are trial assembled, and the above-mentioned grinding and acetone wiping cleaning operations are performed on the unsuitable parts of the assembly.

[0063] The composite material end frame and the composite material cabin body 3 are positioned at multiple points using positioning fixtures to control the concentric axes of the two to coincide with each other.

[0064] Wipe the composite end frame assembly surface with a cloth dipped in acetone until there is no visible particle left on the surface of the cloth. After wiping, let it stand for 30 minutes to allow the end frame assembly surface to dry completely.

[0065] Apply bonding primer to the end frame assembly surface. Use a brush to evenly apply bonding primer to the composite material end frame and composite material cabin end frame assembly surface. Let it dry for 30 minutes after application. During the operation and after application, it is strictly forbidden to touch the end frame assembly surface with your hands. If the end frame assembly surface is contaminated, the contaminated assembly surface must be re-applied with bonding primer.

[0066] Prepare the sealant according to the proportions in the sealant manual. The multi-component sealant should be prepared strictly according to the proportions in the manual, and the weighing should be done with an electronic scale (with an accuracy of not less than 0.01 grams) in an environment without external interference. After weighing, the multiple groups of sealants should be fully stirred and placed in a semi-fluid state before use.

[0067] Apply sealant, the thickness of which should be slightly larger than the assembly gap.

[0068] The composite cabin body 3 is fixed, and the composite end frame is axially pushed into the composite cabin body using the positioning tooling guide rail 9, and the composite end frame plane is used to complete the assembly limit until the composite end frame flange surface is in contact with the composite cabin body end surface.

[0069] Install the countersunk screws 10 and tighten them with a torque wrench. Tighten the torque wrench initially (1-2 N·M) to squeeze the sealant out evenly from the end frame assembly surface.

[0070] Refer to the sealant curing time instructions, and when the sealant is in a semi-cured state, tighten the countersunk screw 10 again with a torque wrench (8-10N·M).

[0071] After assembly, follow the instructions for the sealant to perform subsequent curing.

[0072] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent replacements for some of the technical features therein. However, these modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A composite cabin body with an inner flow channel, characterized in that: It includes a cabin body and end frames; A mounting opening is provided at one end of the cabin body to install the end frame, and the end frame includes a cover and an annular end frame assembly surface, the end frame assembly surface is perpendicular to the cover, and an annular groove is provided on the inner wall of one end of the cabin body close to the mounting opening, and sealants are respectively coated on a preset position of the end frame assembly surface and a side of the annular groove away from the mounting opening, so that after the end frame assembly surface is fully inserted into the mounting opening, two sealants are respectively located on both sides of the annular groove, so that the sealants at both ends and the outer wall of the end frame assembly surface cooperate to seal the annular groove.

2. The composite cabin according to claim 1, characterized in that: The difference between the inner radius of the inner wall of the hull body and the outer radius of the end frame assembly surface is a preset distance, so that after the end frame is coaxially assembled into the hull body, there is a gap between the end frame assembly surface and the inner diameter of the hull body to provide space for the sealant layer.

3. The composite cabin according to claim 2, characterized in that: Before assembly, the thickness of the two layers of sealant is greater than the preset distance, so that after the end frame is assembled into the cabin body, the two layers of sealant are fully squeezed and fitted with the inner wall of the cabin body on both sides and the outer wall of the end frame assembly surface.

4. The composite cabin according to claim 1, characterized in that: A sealing ring is provided on one side of the annular groove close to the installation port, and the height of the sealing ring protruding from the cabin body should be greater than the thickness of the applied sealant, so that the sealing ring can block the sealant during the assembly process to prevent the sealant coated on the end frame assembly surface from entering the annular groove during the assembly process.

5. The composite cabin according to claim 1, characterized in that: After the end frame and the cabin body are assembled, countersunk screws are passed through the end frame assembly surface and the cabin body in sequence to fix the two.

6. The composite cabin body according to claim 5, characterized in that: The countersunk screws are located between the two layers of sealant.

7. The composite cabin according to claim 5, characterized in that: The cover is provided with an operation hole, and the operation hole is used to allow manual labor or a device to enter the interior of the cabin body to install the countersunk screw.

8. An assembly process for a composite cabin body with an inner flow channel, characterized in that: Used to prepare the composite cabin body according to any one of claims 1 to 7, the preparation method comprising: Applying an adhesive primer on the end frame assembly surface and the side of the annular groove away from the mounting opening; After the bonding primer is dried, applying a sealant on the bonding primer; Inserting the end frame into the cabin body through the installation opening; Passing the end frame assembly surface and the cabin body through countersunk screws in sequence to fix the two; Carry out curing treatment.

9. The preparation method according to claim 8, characterized in that: The step of inserting the end frame into the cabin body through the installation opening comprises: The end frame is inserted into the cabin body through the installation port by using a positioning tool so that the end frame and the cabin body are coaxial; wherein the positioning tool comprises a guide rail, a positioning plate and a positioning ring, the end frame is fixed to the positioning plate by bolts, the positioning ring is sleeved on the outside of the cabin body, the guide rail connects the positioning plate and the positioning ring so that the positioning plate and the positioning ring are coaxial and can slide along the axis.

10. The preparation method according to claim 8, characterized in that: The method of sequentially passing the end frame assembly surface and the cabin body through the countersunk screws to fix the two includes: After the end frame reaches the preset position, the countersunk screws are initially tightened; When the sealant is in a semi-cured state, tighten the countersunk screws again.

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