Method for bonding low-temperature heat pipe to satellite aluminum-skinned honeycomb panel and satellite honeycomb panel

Abstract

The application provides a satellite aluminum skin honeycomb plate low-temperature heat pipe bonding method and a satellite honeycomb plate in the technical field of composite material bonding assembly, and the specific steps are as follows: S1, sequentially assembling a lower skin, a pre-embedded block, foaming glue, a separation plate, a short honeycomb, a reinforcing skin, a honeycomb core, an upper skin and a compensation plate in a tooling mold, and combining the mold to make a vacuum bag; S2, high-temperature curing forming; S3, removing the mold, taking out the compensation plate, the separation plate, the pre-embedded block and the foaming glue patch on the side edge of the pre-embedded block; S4, bonding; S5, normal-temperature curing; S6, removing the heavy object and cleaning residual glue. The application solves the technical problem that the high-temperature curing forming honeycomb plate cannot be internally embedded with a low-temperature heat pipe, arranges the reinforcing skin around the low-temperature heat pipe, improves the external skin bonding performance and the low-temperature heat pipe area flatness, and uses the foaming glue patch to solve the honeycomb plate weight increase problem caused by excessive injection amount of the low-temperature heat pipe in normal-temperature bonding.

Description

Technical Field

[0001] This invention relates to the field of composite material bonding and assembly technology, specifically to a method for bonding low-temperature heat pipes to aluminum skin honeycomb panels for satellites, and to the honeycomb panels for satellites. Background Technology

[0002] As a crucial component of satellites and other spacecraft, satellite honeycomb panels often house various onboard equipment to ensure the smooth operation of satellite functions. Due to the excessive power of some equipment, a large amount of heat is generated during operation, affecting normal equipment operation and generating temperature stress, which impacts the stability of the satellite structure. To avoid equipment overheating failures and reduce temperature stress within the honeycomb panel, it is necessary to enhance the thermal conductivity and isothermal properties of the embedded heat pipe structure within the honeycomb panel.

[0003] Due to varying on-orbit environments of satellite equipment, the types of heat pipes embedded in honeycomb panels also differ. Currently, there are mainly two types: room-temperature heat pipes and low-temperature heat pipes. Room-temperature heat pipes can withstand honeycomb panel molding temperatures of ≤90℃, and therefore can be bonded using J-78B adhesive film and J-78D2 foam adhesive. However, low-temperature heat pipes can only withstand honeycomb panel molding temperatures of ≤35℃, and therefore cannot be bonded using high-temperature curing adhesives. If room-temperature curing adhesives are used exclusively to bond honeycomb panels containing low-temperature heat pipes, on the one hand, the amount of adhesive used in the honeycomb panel will increase significantly, increasing the weight of the honeycomb panel structure; on the other hand, during the vacuum bag making process, the amount of curing agent volatilization will be large, leading to a decrease in adhesive performance and affecting the structural stability of the honeycomb panel.

[0004] To overcome the shortcomings of the prior art, the present invention aims to provide a process for bonding low-temperature heat pipes to aluminum skin honeycomb panels for satellites, thereby solving the technical difficulty that low-temperature heat pipes cannot withstand the curing temperature of high-temperature curing adhesives. Summary of the Invention

[0005] To address the shortcomings of existing technologies, the purpose of this invention is to provide a method for bonding low-temperature heat pipes to aluminum skin honeycomb panels for satellites, as well as the honeycomb panels for satellites.

[0006] According to the present invention, a method for bonding a low-temperature heat pipe to an aluminum skin honeycomb panel for satellite use comprises the following steps:

[0007] S1. Sequentially assemble the lower skin, embedded block, foam, isolation plate, low honeycomb, reinforcing skin, honeycomb core, upper skin and compensation plate in the tooling mold, and close the mold to make a vacuum bag.

[0008] S2, High-temperature curing molding;

[0009] S3. Remove the mold, take out the compensation plate, isolation plate, embedded block and the foam adhesive patch on the side of the embedded block;

[0010] S4. At room temperature, glue the expanding foam patch to the gap on the side of the low temperature heat pipe, glue the low temperature heat pipe and the expanding foam patch together into the reserved groove of the honeycomb panel, glue the outer skin above the low temperature heat pipe and the reinforcing skin, and apply a heavy object to the outer skin to compact it.

[0011] S5, Cures at room temperature;

[0012] S6. Remove heavy objects and clean up any remaining adhesive.

[0013] Preferably, in step S1, a release agent is applied to the surfaces of the isolation plate and the embedded block, and adhesive film is applied to the adhesive surfaces of the upper skin, lower skin, and reinforcing skin; the honeycomb panel is assembled, the lower skin is placed in the tooling mold, the embedded block is placed at the low-temperature heat pipe position, foam is placed in the side gap of the embedded block, the isolation plate is placed outside the foam, the foam is wrapped around the outside of the isolation plate, short honeycombs with the same width as the reinforcing skin are placed around the foam, honeycomb cores are placed in other areas, the reinforcing skin is placed above the short honeycombs, the upper skin is placed above the reinforcing skin and the honeycomb core, a compensation plate is placed in the opening in the middle of the upper skin, and the mold is closed to make a vacuum bag.

[0014] Preferably, in step S1, the vacuum gauge pressure of the vacuum bag is ≤ -0.095 MPa.

[0015] Preferably, in step S1, the surface of the embedded block has a demolding hole.

[0016] Preferably, in step S1, the embedded block has the same outline as the low-temperature heat pipe.

[0017] Preferably, in step S1, the height difference between the short honeycomb and the honeycomb core is consistent with the thickness of the reinforcing skin.

[0018] Preferably, in step S2, a high-temperature curing adhesive is used for high-temperature curing, and the high-temperature curing adhesive includes J-78B adhesive film and J-78D2 foam adhesive.

[0019] Preferably, in step S4, when bonding the outer skin, a heavy object is applied to the surface of the skin to compact it, and excess adhesive is cleaned up after 15 minutes until there is no excess adhesive.

[0020] Preferably, in step S5, a room temperature curing adhesive is used for room temperature curing, and the room temperature curing adhesive includes J-133 adhesive.

[0021] The present invention also provides a satellite honeycomb panel, which uses a satellite aluminum skin honeycomb panel to bond a low-temperature heat pipe.

[0022] Compared with the prior art, the present invention has the following beneficial effects:

[0023] This invention solves the technological challenge of embedding low-temperature heat pipes in high-temperature cured honeycomb panels. By arranging reinforcing skin around the low-temperature heat pipes, the bonding performance of the outer skin and the flatness of the low-temperature heat pipe area are improved. The use of expanding foam patches solves the problem of increased weight of the honeycomb panel caused by excessive glue application when bonding low-temperature heat pipes at room temperature. Attached Figure Description

[0024] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings:

[0025] Figure 1 This is a process flow diagram of a method for bonding a low-temperature heat pipe to an aluminum skin honeycomb panel for satellites according to the present invention.

[0026] Figure 2 This is an assembly diagram illustrating a method for bonding a low-temperature heat pipe to an aluminum skin honeycomb panel for satellites according to the present invention.

[0027] Figure 3 for Figure 2 A magnified view of the local structure;

[0028] Figure 4 This is a schematic diagram of the method for bonding a low-temperature heat pipe to an aluminum skin honeycomb panel for satellites according to the present invention.

[0029] Figure 5 for Figure 4 A magnified view of the local structure.

[0030] Numbering on the map:

[0031] 1. Embedded block; 2. Expanding foam; 3. Upper skin; 4. Lower skin; 5. Honeycomb core; 6. Reinforcing skin; 7. Compensation plate; 8. Isolation plate; 9. Low temperature heat pipe; 10. Expanding foam patch; 11. Cured expanding foam; 12. External skin; 13. Low honeycomb. Detailed Implementation

[0032] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the scope of protection of the present invention.

[0033] Example 1

[0034] This invention provides a method for bonding low-temperature heat pipes to aluminum skin honeycomb panels for satellites, such as... Figure 1-5 As shown, the specific steps are as follows:

[0035] S1. Apply release agent to the surfaces of the isolation plate 8 and the embedded block 1, and apply adhesive film to the adhesive surfaces of the upper skin 3, lower skin 4 and reinforcing skin 6; assemble the honeycomb panel, place the lower skin 4 in the tooling mold, place the embedded block 1 at the position of the low temperature heat pipe 9, place foam 2 in the side gap of the embedded block 1, place the isolation plate 8 outside the foam 2, wrap the foam 2 outside the isolation plate 8, place the low honeycomb 13 with the same width as the reinforcing skin 6 around the foam 2, place the honeycomb core 5 in other areas, place the reinforcing skin 6 above the low honeycomb 13, place the upper skin 3 above the reinforcing skin 6 and the honeycomb core 5, place the compensation plate 7 in the opening in the middle of the upper skin 3, and close the mold to make a vacuum bag;

[0036] S2, High-temperature curing molding;

[0037] S3. Remove the mold, take out the compensation plate 7, the isolation plate 8, the embedded block 1, and the foam adhesive patch 10 on the side of the embedded block 1;

[0038] S4. At room temperature, glue the expanding foam patch 10 to the side gap of the low temperature heat pipe 9, glue the low temperature heat pipe 9 and the expanding foam patch 10 together to the pre-reserved groove of the honeycomb panel, glue the outer skin 12 above the low temperature heat pipe 9 and the reinforcing skin 6, and apply a heavy object to the outer skin 12 to compact it.

[0039] S5, Cures at room temperature;

[0040] S6. Remove heavy objects and clean up any remaining adhesive.

[0041] In step S1, the embedded block 1 is made of aluminum alloy, and 2-M8 demolding holes are left on the upper surface of the embedded block 1; the outline of the embedded block 1 is consistent with that of the low-temperature heat pipe 9. The height difference between the short honeycomb 13 and the honeycomb core 5 is consistent with the thickness of the reinforcing skin 6. The vacuum gauge pressure of the vacuum bag is ≤-0.095Mpa. In step S2, a high-temperature curing adhesive is used, including J-78B adhesive film and J-78D2 foaming adhesive. In step S3, the thickness of the isolation plate 8 is 0.3mm. In step S4, when bonding the outer skin 12, a heavy object is applied to the surface of the skin to compact it, and the excess adhesive is cleaned up after 15 minutes until there is no excess adhesive. The surface of the heavy object applied to the outer skin 12 is flat, and the outer skin 12 and the heavy object have the same dimensions. In step S5, a room-temperature curing adhesive is used, including J-133 adhesive.

[0042] More specifically, the opening size of the skin 3 on the low-temperature heat pipe 9 area is 30mm larger on one side than the outer dimensions of the low-temperature heat pipe 9. The outer skin 12 is 29.9mm larger on one side than the outer dimensions of the low-temperature heat pipe 9. The internal opening size of the reinforcing skin 6 is 0.4mm larger on one side than the outer dimensions of the low-temperature heat pipe 9. The outer dimensions of the reinforcing skin 6 are 60mm larger on one side than the outer dimensions of the low-temperature heat pipe 9.

[0043] The honeycomb panel and the foam patch 10 are cured at high temperature. The foam patch 10 is glued to the side gap of the low temperature heat pipe 9 at room temperature. The low temperature heat pipe 9 and the foam patch 10 are glued to the honeycomb panel in the pre-reserved groove at room temperature. The outer skin 12 is glued at room temperature, and finally the honeycomb panel containing the low temperature heat pipe 9 is formed.

[0044] Example 2

[0045] This second embodiment is based on the first embodiment, and the specific implementation steps are as follows:

[0046] S1 Assembly: Apply release agent to the surfaces of embedded block 1 and partition plate 8. Place the lower skin 4 with J-78B adhesive film attached to the adhesive side in the tooling mold, with the adhesive film facing upward. Wrap J-78D2 expanding foam 2 around the side gap of embedded block 1 and place it on the lower skin 4. Place partition plate 8 around embedded block 1. Wrap J-78D2 expanding foam 2 on the outside of the partition plate. Place a short honeycomb 13 with the same width as the reinforcing skin 6 outside the J-78D2 expanding foam 2. Place honeycomb core 5 in other areas. Attach J-78B adhesive film to the adhesive side of reinforcing skin 6. Place reinforcing skin 6 above the short honeycomb 13, with the adhesive film facing downward. Attach J-78B adhesive film to the adhesive side of upper skin 3. Place upper skin 3 above honeycomb core 5 and reinforcing skin 6, with the adhesive film facing downward. Place compensation plate 7 in the opening in the middle of upper skin 3. Close the mold to make a vacuum bag. Vacuum gauge pressure ≤ -0.095Mpa.

[0047] S2 curing: Curing at 90℃ for 4 hours.

[0048] S3 Demolding: Remove the tooling mold and take out the compensation plate 7, the isolation plate 8, the embedded block 1, and the foam adhesive patch 10 formed in the gap of the embedded block 1.

[0049] S4 Bonding: After evenly applying J-133 adhesive to the bonding surfaces of the low-temperature heat pipe 9 and the foam patch 10, bond the foam patch 10 to the side gap of the low-temperature heat pipe 9. Then, apply J-133 adhesive to the bonding surfaces of the low-temperature heat pipe 9 and the foam patch 10 and bond them to the pre-reserved groove of the honeycomb panel. Finally, apply J-133 adhesive to the bonding surface of the outer skin 12 and bond it to the upper surface of the low-temperature heat pipe 9 and the reinforcing skin 6. Apply a heavy object to the upper surface of the outer skin 12 to compact it.

[0050] S5 curing: Curing at room temperature for 72 hours, cleaning up any excess adhesive every 15 minutes until no more adhesive remains.

[0051] S6 Pliers: Remove heavy objects and clean residual adhesive.

[0052] Example 3

[0053] The present invention also provides a satellite honeycomb panel, which uses a satellite aluminum skin honeycomb panel to bond a low-temperature heat pipe.

[0054] In the description of this application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.

[0055] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A method of bonding a low temperature heat pipe to an aluminum-skinned honeycomb panel for a satellite, characterized by, The specific steps are as follows: S1. In the tooling mold, assemble the lower skin (4), embedded block (1), foam (2), isolation plate (8), short honeycomb (13), reinforcing skin (6), honeycomb core (5), upper skin (3) and compensation plate (7) in sequence, and close the mold to make a vacuum bag; S2, High-temperature curing molding; S3. Remove the mold and take out the compensation plate (7), the isolation plate (8), the embedded block (1) and the foam adhesive patch (10) on the side of the embedded block (1). S4. At room temperature, glue the foam patch (10) at the side gap of the low temperature heat pipe (9), glue the low temperature heat pipe (9) and the foam patch (10) together into the reserved groove of the honeycomb panel, glue the outer skin (12) above the low temperature heat pipe (9) and the reinforcing skin (6), and apply a heavy object to the outer skin (12) to compact it. S5, Cures at room temperature; S6. Remove heavy objects and clean up residual adhesive; In step S1, a release agent is applied to the surfaces of the isolation plate (8) and the embedded block (1), and adhesive film is applied to the adhesive surfaces of the upper skin (3), the lower skin (4) and the reinforcing skin (6); Assemble the honeycomb panel, place the lower skin (4) in the tooling mold, place the embedded block (1) at the position of the low temperature heat pipe (9), place the foam (2) in the side gap of the embedded block (1), place the isolation plate (8) outside the foam (2), wrap the foam (2) outside the isolation plate (8), place the short honeycomb (13) with the same width as the reinforcing skin (6) around the foam (2), place the honeycomb core (5) in other areas, place the reinforcing skin (6) above the short honeycomb (13), place the upper skin (3) above the reinforcing skin (6) and the honeycomb core (5), place the compensation plate (7) in the middle opening of the upper skin (3), and close the mold to make a vacuum bag.

2. The method of claim 1, wherein the method is characterized by: In step S1, the vacuum gauge pressure of the vacuum bag is ≤ -0.095 MPa.

3. The method of claim 1, wherein the method is characterized by: In step S1, the surface of the pre-embedded block (1) has a demolding hole.

4. The method of claim 1, wherein the method is characterized by: In step S1, the pre-embedded block (1) has the same outline as the low-temperature heat pipe (9).

5. The method of claim 1, wherein the method is characterized by: In step S1, the height difference between the short honeycomb (13) and the honeycomb core (5) is consistent with the thickness of the reinforcing skin (6).

6. The method of claim 1, wherein the method is characterized by: In step S2, a high-temperature curing adhesive is used for high-temperature curing, the high-temperature curing adhesive including J-78B adhesive film and J-78D2 foam adhesive.

7. The method of claim 1, wherein the method is characterized by: In step S4, when bonding the outer skin (12), a heavy object is applied to the surface of the skin to compact it, and the excess glue is cleaned up after 15 minutes until there is no excess glue.

8. The method of claim 1, wherein the method is a method of bonding a low temperature heat pipe to an aluminum skin honeycomb panel for a satellite, the method comprising: In step S5, a room temperature curing adhesive is used for room temperature curing, and the room temperature curing adhesive includes J-133 adhesive.

9. A honeycomb for satellites, characterized by, The method of bonding low-temperature heat pipes to aluminum skin honeycomb panels for satellites as described in any one of claims 1-8.

Images