Method for gluing heat insulation cork board on outer surface of rocket fairing

Abstract

The invention discloses a method for cementing a heat-insulating cork board on the outer surface of a rocket fairing. The method comprises the following steps: S1, splicing small standard blocks 1 of the heat-insulating cork board to manufacture a whole prefabricated slab; the whole prefabricated plate is manufactured, small heat insulation cork plates are independently formed in the splicing process, mass production can be achieved in advance, the process time of the rocket fairing is not occupied, and the production efficiency is improved; the whole prefabricated slab and the small heat insulation cork boards are in butt joint and are tightly fixed together, large splicing seams can be prevented from occurring during secondary laying, and the procedure of filling gaps during bonding is omitted; the whole prefabricated slab is glued, the operation is convenient, the number of operators can be reduced within the effective operation time of cork glue, and the labor cost is reduced; the splicing of the small heat-insulating cork boards does not need to be operated on a half-surface fairing, so that the fairing can adopt full-circle glue joint, the glue joint procedure of the heat-insulating cork boards is completed at a time, and the manufacturing period of the fairing is effectively shortened.

Description

Technical Field

[0001] The present invention relates to the technical field of aerospace vehicle manufacturing, and particularly relates to a method for adhesively bonding heat-insulating cork boards on the outer surface of a rocket fairing. Background Art

[0002] The rocket fairing is located at the top of the launch vehicle and can reduce the flight resistance of the rocket and protect the payload. When the rocket flies in the atmosphere, a large amount of heat is generated due to intense friction with the air. Adhesively bonding heat-insulating cork boards on the outer surface of the rocket fairing can effectively block external heat from entering the interior of the fairing, ensuring that the payload is in a normal operating temperature environment and preventing damage from high temperatures. At the same time, the heat-insulating cork board has a certain elasticity and flexibility, and when the rocket passes through the atmosphere, it plays a role in buffering and shock absorption, reducing the impact of vibration and shock on the equipment and protecting the structural integrity and performance stability of the payload.

[0003] The heat-insulating cork board used is a square thin plate type wood board produced according to standards, with a side length of 480 mm. The rocket fairing is a carbon fiber composite structural part with a large outer surface area. The bonding process uses two half-surfaces to bond the heat-insulating cork boards respectively. First, on the half-fairing surface with the outer surface facing up, the entire layer of heat-insulating cork boards is pre-laid in a butt-jointed puzzle pattern. The joints between adjacent heat-insulating cork boards are connected with masking tape with self-adhesive. A few large-sized splicing blocks are formed, and the splicing blocks at this position are cut according to the edge of the half-shell, numbered according to the coordinate positions on the splicing blocks, and then removed for standby. Softwood glue is scraped on the outer surface of the fairing, and the standby splicing blocks are adhesively bonded to the corresponding positions on the outer surface of the fairing according to the coordinate numbers. The butting edges of adjacent splicing blocks are connected again with masking tape with self-adhesive. After all the splicing blocks are laid, the entire fairing is placed in a vacuum bag, and curing is carried out by means of vacuum pumping and negative pressure.

[0004] In the above bonding process, the splicing and trimming of small pieces of heat-insulating cork boards both require a long process time for the fairing. When the splicing blocks are re-laid on the curved outer surface of the fairing; due to the difficulty of accurately laying them in the position of the first laying, a large splicing seam will be generated, and small strips of heat-insulating cork boards need to be cut for repair, and the small splicing seams are filled with cork glue caulking agent. The cork glue is a two-component type, which needs to be prepared before use, and the operable time is within 1 hour. Therefore, the time for large-area glue application, laying heat-insulating cork boards, and installing the vacuum bag is limited, and more personnel are required to operate simultaneously to meet the progress and quality requirements.

[0005] With the increase in the production volume of satellite launches, the process time and personnel occupied by the above bonding process limit the production rhythm of the rocket fairing and are difficult to meet the strong mass production demand of the rocket fairing. Summary of the Invention

[0006] The object of the present invention is to solve the deficiencies existing in the prior art, and a method for adhesively bonding heat-insulating cork boards on the outer surface of a rocket fairing is proposed. The method realizes that the heat-insulating cork boards are separately spliced into a whole prefabricated board, which can be laid and adhesively bonded to the outer surface of the fairing at one time, and then vacuum bag pressing is used for adhesive curing.

[0007] In order to achieve the above object, the present invention adopts the following technical solutions: A method for adhesively bonding heat-insulating cork boards on the outer surface of a rocket fairing, the method comprising the following steps: S1: Splicing standard small pieces 1 of heat-insulating cork boards to make a whole prefabricated board; S2: Treating the outer surface of the fairing; S3: Adhesive bonding and curing.

[0008] Preferably, in S1, the steps of splicing standard small pieces 1 of heat-insulating cork boards to make a whole prefabricated board are as follows: S1.1: Butt-joint and lay several heat-insulating cork boards on a large-size flat plate to form a cork splicing board with a size larger than the unfolded size of the outer surface of the fairing; S1.2: Apply a layer of mesh cloth with hot melt adhesive on the cork splicing board, and the overall size of the mesh cloth is the same as the unfolded size of the outer surface of the fairing; S1.3: Cover a layer of release cloth on the mesh cloth, lay a vacuum bag on the large-size flat plate, and use the vacuum bag pressing method for overall pressurization; S1.4: Send the vacuum bag system into the drying oven. After the hot melt adhesive on the mesh cloth is quickly melted by heat, remove it from the drying oven. After cooling, the mesh cloth bonds the cork splicing board into a whole board, and remove the vacuum bag system; S1.5: Cut off the excess heat-insulating cork boards according to the edge of the mesh cloth to make a whole prefabricated board.

[0009] Preferably, the steps of treating the outer surface of the fairing in S2 are as follows: S2.1: Sand the surface of the rocket fairing to be adhesively bonded; S2.2: Remove the surface dust and clean it with a cleaning solvent.

[0010] Preferably, the steps of adhesive bonding and curing in S3 are as follows: S3.1: Scrape a layer of cork glue on the surface of the rocket fairing; S3.2: Fit and adhesively bond the whole prefabricated board to the outer surface of the fairing, and align the edge of the whole prefabricated board with the adhesive bonding edge of the fairing; S3.3: Put the adhesively bonded fairing as a whole into the vacuum bag, and adopt vacuum pumping and pressurization for room temperature curing; S3.4. After curing, remove the vacuum bag system, move the fairing into the drying oven, and the hot melt adhesive on the mesh cloth melts when heated, so that the mesh cloth can be easily torn off from the outer surface of the fairing.

[0011] Preferably, the mesh cloth is made of high-temperature resistant material and has bending flexibility.

[0012] Preferably, the hot melt adhesive can be reused.

[0013] Preferably, the mesh cloth is cut according to the surface development drawing of the product, and the edge is sealed with a hot melt film strip.

[0014] Compared with the prior art, the beneficial effects of the present invention are as follows: 1. By making a whole prefabricated board, the splicing process of small pieces of adiabatic cork boards is formed separately, which can be mass-produced in advance, does not occupy the process time of the rocket fairing, and improves production efficiency; 2. Using a whole prefabricated board, small pieces of adiabatic cork boards are closely butted and fixed together, which can avoid large splicing seams during secondary laying and save the process of filling gaps during bonding; 3. The whole prefabricated board is glued, which is convenient to operate. During the effective operation time of the cork glue, the number of operators can be reduced and the labor cost can be reduced; 4. The splicing of small pieces of adiabatic cork boards does not need to be operated on the half fairing. Therefore, the fairing can be glued in a whole circle, and the gluing process of the adiabatic cork boards can be completed at one time, effectively shortening the production cycle of the fairing. Description of the Drawings

[0015] In order to more specifically and intuitively illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the drawings required for use in the description of the embodiments or the prior art.

[0016] Figure 1 It is a schematic flow chart of the gluing method according to the embodiment of the present invention; Figure 2 It is a schematic structural diagram of the splicing of adiabatic cork boards on a metal flat plate according to the embodiment of the present invention; Figure 3 It is a schematic structural diagram of the side whole prefabricated board made by pasting the adiabatic cork board splicing block and the mesh cloth according to the first embodiment of the present invention; Figure 4 It is a schematic structural diagram of the bottom whole prefabricated board made by pasting the adiabatic cork board splicing block and the mesh cloth according to the second embodiment of the present invention; Figure 5 It is a schematic structural diagram of the rocket fairing according to the embodiment of the present invention; Figure 6 It is a schematic structural diagram of the fairing after completing the gluing of the adiabatic cork board according to the embodiment of the present invention; Figure 7 Schematic cross-sectional structure diagram of the vacuum bag system for press-bonding the heat-insulating cork board splicing block and the mesh cloth bag in the embodiment of the present invention.

[0017] In the figure: standard small piece of heat-insulating cork board 1, metal flat plate 2, sealing putty strip 3, side mesh cloth 4, side heat-melt film strip 5, side whole prefabricated board 6, bottom mesh cloth 7, bottom heat-melt film strip 8, bottom heat-insulating cork board layer 9, carbon fiber composite material side 10, metal bottom 11, side heat-insulating cork board layer 12, bottom heat-insulating cork board layer 13, release cloth 14, breathable felt 15, vacuum bag film 16, quick-connect air nozzle 17. Specific embodiments

[0018] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments.

[0019] Embodiment 1 As Figure 5 shown, the rocket fairing is a carbon fiber composite material side 10, with a front conical shape and a middle and rear cylindrical shape. The plan view unfolded along any generatrix on the side is as Figure 3 shown, which is a plan view of two upper trapezoids and a lower rectangle.

[0020] As Figures 1 - 6 shown, an embodiment of the method for bonding the heat-insulating cork board to the carbon fiber composite material side 10 of the rocket fairing includes the steps of splicing and fabricating the side whole prefabricated board 6 with the standard small pieces of heat-insulating cork board 1, the surface treatment step of the carbon fiber composite material side 10 of the rocket fairing, and the bonding and curing steps.

[0021] The steps of splicing and fabricating the side whole prefabricated board 6 with the standard small pieces of heat-insulating cork board 1 include: As Figure 4 shown, S1.1, draw the plan view of the unfolded carbon fiber composite material side 10 of the rocket fairing.

[0022] Paste a whole circle of sealing putty strip 3 around the clean metal flat plate 2 for sealing the vacuum bag film 16.

[0023] Calculate the maximum outer dimension of the unfolded drawing, and butt and lay the standard small pieces of heat-insulating cork board 1 on the metal flat plate 2. The thickness of the standard small pieces of heat-insulating cork board 1 is 3 mm, and the half of the misaligned side length of the butt joint of adjacent layers is formed into a cork splicing board with a size slightly larger than the maximum outer dimension.

[0024] S1.2. Cut the planar shape of the side grid cloth 4 with hot melt adhesive according to the planar drawing developed from the side 10 of the carbon fiber composite material. Use the side hot melt film strip 5 to perform hot melt edge binding on the side grid cloth 4, and trim the edges so that the planar outer shape of the side grid cloth 4 is the same as the developed drawing of the side 10 of the carbon fiber composite material.

[0025] Lay the side grid cloth 4 on the cork splicing board, with the four sides of the side grid cloth 4 all inside the cork splicing board, and leave the cutting allowance for the heat-insulating cork board.

[0026] As Figure 7 shown, S1.3. Lay the release cloth 14, the breather felt 15 and the vacuum bag film 16 on the side grid cloth 4 in sequence. Place the quick-connect air nozzle 17 on the breather felt 15 at the edge, and use the sealing putty strip 3 to seal with the vacuum bag film 16 to make a vacuum bag system.

[0027] The release cloth 14 is used to prevent the hot melt adhesive from transferring to the breather felt 15, so that the breather felt 15 can be reused. The breather felt 15 is used for air conduction in the vacuum bag system. The quick-connect air nozzle 17 is connected to the vacuum pipeline, and vacuum is pumped to perform overall bag pressing.

[0028] S1.4. Send the vacuum bag pressing system into the drying oven. After heating up to quickly melt the hot melt adhesive on the side grid cloth 4, take it out of the drying oven and cool it, and remove the vacuum bag system. At this time, the side grid cloth 4 bonds the standard small pieces 1 of the small-sized heat-insulating cork board into a large-sized whole board.

[0029] S1.5. Cut the excess heat-insulating cork board according to the edge of the side grid cloth 4 to make the side whole prefabricated board 6.

[0030] The steps for the outer surface treatment of the rocket fairing include: S2.1. Sand the side 10 of the carbon fiber composite material of the rocket fairing with sandpaper to remove the release agent and oil stain on the surface; S2.2. Remove the surface dust, and use a cleaning solvent to clean the dust on the side 10 of the carbon fiber composite material.

[0031] The steps for bonding and curing include: S3.1. On the cleaned side 10 of the carbon fiber composite material, scrape a layer of cork glue with a serrated plastic scraper; S3.2. Bond the side whole prefabricated board 6 and the side 10 of the carbon fiber composite material of the rocket fairing by fitting them together. Align the edge of the side whole prefabricated board 6 with the bonding edge of the side 10 of the carbon fiber composite material; Use pressure-sensitive tape to connect the butt edges of the generatrix laid by the side whole prefabricated board 6.

[0032] S3.3. Integrally place the rocket fairing with the adhesively bonded side heat-insulating cork board layer 12 into a vacuum bag, and cure it at room temperature under vacuum pressure. The laying method of the vacuum bag system is the same as that in S1.3.

[0033] S3.4. After curing, remove the vacuum bag system, move the rocket fairing into an oven. The hot-melt adhesive on the side grid cloth 4 melts when heated, and tear the side grid cloth 4 from the surface of the side heat-insulating cork board layer 12 of the rocket fairing, then move the rocket fairing out of the oven to complete the bonding process of the side heat-insulating cork board layer 12.

[0034] Example Two As Figure 4 shown, the bottom surface of the rocket fairing is made of lightweight metal material, which is a circular plane and does not require expansion calculation.

[0035] As Figures 1 - 6 shown, an example of the method for bonding the heat-insulating cork board to the metal bottom surface 11 of the rocket fairing includes the steps of splicing and fabricating the entire bottom heat-insulating cork board layer 9 from standard small pieces of heat-insulating cork board 1, surface treatment of the metal bottom surface 11, and bonding and curing steps.

[0036] The steps of splicing and fabricating the entire bottom heat-insulating cork board layer 9 from standard small pieces of heat-insulating cork board 1 include: S1.1. Paste a whole circle of sealing putty strips 3 around the periphery of the clean metal plate 2 for use in sealing the vacuum bag film 16.

[0037] Calculate the maximum outer dimension of the bottom circle, and butt and lay several standard small pieces of heat-insulating cork board 1 on the metal plate 2. The thickness of the standard small pieces of heat-insulating cork board 1 is 1 mm, and the half of the misaligned side length of the butt joint of adjacent layers is formed into a cork splicing board with a size slightly larger than the maximum outer dimension.

[0038] S1.2. Cut the planar shape of the bottom grid cloth 7 with hot-melt adhesive according to the circular drawing of the metal bottom surface 11 of the rocket fairing. Use the bottom hot-melt film strip 8 to perform hot-melt edge binding on the bottom grid cloth 7 and trim the edges so that the circle of the bottom grid cloth 7 is the same as the circle of the metal bottom surface of the rocket fairing.

[0039] Lay the bottom grid cloth 7 on the cork splicing board, with the four sides of the bottom grid cloth 7 all inside the cork splicing board, and leave the cutting allowance for the heat-insulating cork board.

[0040] S1.3. As Figure 7 shown, lay the release cloth 14, the breather felt 15 and the vacuum bag film 16 on the bottom grid cloth 7 in sequence. Place the quick-connect air nozzle 17 on the breather felt 15 at the edge, and use the sealing putty strip 3 to seal with the vacuum bag film 16 to make a vacuum bag system.

[0041] The release cloth 14 is used to prevent the hot melt adhesive from transferring to the breathable felt 15, so that the breathable felt 15 can be reused. The breathable felt 15 is used for air conduction in the vacuum bag system. The quick-connect air nozzle 17 is connected to the vacuum pipeline, and vacuum is pumped to perform integral bag pressing.

[0042] S1.4. Send the vacuum bag pressing system into the drying oven. After heating up to quickly melt the hot melt adhesive on the bottom grid cloth 7, remove it from the drying oven and cool it, and remove the vacuum bag system. At this time, the bottom grid cloth 7 bonds the small-sized standard pieces of adiabatic corkboard 1 into a large-sized whole board.

[0043] S1.5. Cut off the excess adiabatic corkboard along the edge of the standard piece of adiabatic corkboard 1 to make the bottom whole bottom adiabatic corkboard layer 9.

[0044] The processing steps of the metal bottom surface 11 of the rocket fairing include: S2.1. Polish the metal bottom surface 11 of the rocket fairing to be bonded with sandpaper to remove the oil stains on the surface; S2.2. Remove the surface dust and clean the dust on the metal bottom surface 11 with a cleaning solvent.

[0045] The bonding and curing steps include: S3.1. Use a serrated plastic scraper to apply a layer of cork glue on the cleaned metal bottom surface 11; S3.2. Bond the bottom adiabatic corkboard layer 9 and the metal bottom surface 11 of the rocket fairing, and align the edge of the bottom adiabatic corkboard layer 9 with the bonding edge of the metal bottom surface 11 of the rocket fairing.

[0046] S3.3. Put the rocket fairing bonded with the bottom adiabatic corkboard layer 13 into the vacuum bag as a whole, and cure it at room temperature by vacuum pumping and pressurization. The laying method of the vacuum bag system is the same as that in S1.3.

[0047] S3.4. After curing, remove the vacuum bag system, move the rocket fairing into the drying oven, the hot melt adhesive on the bottom grid cloth 7 is heated and melted, tear the bottom grid cloth 7 from the bottom adiabatic corkboard layer 13 of the rocket fairing, and remove the rocket fairing from the drying oven to complete the bonding process of the bottom adiabatic corkboard layer 13.

[0048] The above is only the preferred specific implementation manner of the present invention, but the protection scope of the present invention is not limited thereto. Any person skilled in the art within the technical scope disclosed by the present invention, according to the technical solution and inventive concept of the present invention, makes equivalent substitutions or changes, and should be covered by the protection scope of the present invention.

Claims

1. A method for adhesively bonding heat-insulating cork boards to the outer surface of a rocket fairing, characterized in that, The method comprises the following steps: S1: Assembling standard small pieces of adiabatic cork board 1 to fabricate an entire prefabricated board; S2: Treating the outer surface of the fairing; S3: Gluing and curing.

2. The method for adhesively bonding an insulating cork board to the outer surface of a rocket fairing according to claim 1, characterized in that, In S1, the steps of assembling standard small pieces of adiabatic cork board 1 to fabricate an entire prefabricated board are as follows: S1.1: Butt-joint and lay several pieces of adiabatic cork board on a large-sized flat plate to form a cork splicing board with a size larger than the unfolded size of the outer surface of the fairing; S1.2: Apply a layer of fiberglass mesh with hot-melt adhesive on the cork splicing board, and the overall size of the fiberglass mesh is the same as the unfolded size of the outer surface of the fairing; S1.3: Cover a layer of release cloth on the fiberglass mesh, lay a vacuum bag on the large-sized flat plate, and use the vacuum bag pressing method for overall pressurization; S1.4: Send the vacuum bag system into the drying oven. After the hot-melt adhesive on the fiberglass mesh is quickly melted by heat, remove it from the drying oven. After cooling, the fiberglass mesh bonds the cork splicing board into an integral board, and then remove the vacuum bag system; S1.5: Cut off the redundant adiabatic cork board along the edge of the fiberglass mesh to fabricate an entire prefabricated board.

3. A method for adhesively bonding an insulating cork board to the outer surface of a rocket fairing according to claim 2, characterized in that, The steps of treating the outer surface of the fairing in S2 are as follows: S2.1: Polish the surface of the rocket fairing to be glued with sandpaper; S2.2: Remove the surface dust and clean it with a cleaning solvent.

4. A method for adhesively bonding an insulating cork board to the outer surface of a rocket fairing according to claim 3, characterized in that, The steps of gluing and curing in S3 are as follows: S3.1: Scrape a layer of cork glue on the surface of the rocket fairing; S3.2: Bond the entire prefabricated board to the outer surface of the fairing, and align the edge of the entire prefabricated board with the bonding edge of the fairing; S3.3: Put the glued fairing into the vacuum bag as a whole, and cure it at room temperature under vacuum pressure; S3.4: After curing, remove the vacuum bag system, move the fairing into the drying oven, and the hot-melt adhesive on the fiberglass mesh is melted by heat, and the fiberglass mesh can be easily torn off from the outer surface of the fairing.

5. The method for adhesively bonding an insulating cork board to the outer surface of a rocket fairing according to claim 4, characterized in that, The fiberglass mesh is a high-temperature resistant material and has bending flexibility.

6. The method for adhesively bonding an insulating cork board to the outer surface of a rocket fairing according to claim 5, characterized in that, The hot-melt adhesive can be reused.

7. A method for adhesively bonding an insulating cork board to the outer surface of a rocket fairing according to claim 6, characterized in that, The fiberglass mesh is cut according to the surface development drawing of the product, and the edge is sealed with a hot-melt film strip.

Images