Method for bonding a flexible blanket to a base for a spacecraft and flexible blanket for a spacecraft

Abstract

The application discloses a kind of spacecraft with flexible blanket and base bonding method and spacecraft with flexible blanket, comprising: surface treatment step, bonding prepreg step, vacuum curing step, film pasting step, bonding step and pressurized curing step.Polish the surface of base, the first adhesive film is bonded in the bonding area of flexible blanket, and heated to make the first adhesive film and flexible blanket fit;Prepreg is set on the first adhesive film, and heated to make prepreg fixed on the first adhesive film;Flexible blanket is cured under vacuum condition;Second adhesive film is bonded on the prepreg of flexible blanket.Flexible blanket and the bonding area of base are aligned and bonded;Non-bonding area of flexible blanket is wound on the base, and is wound according to predetermined tension using adhesive tape, and then is put into curing oven for curing.The bonding method of the present application increases the structural strength of the bonding area position of the blanket surface, facilitates bonding positioning, and avoids defects such as bubbles and wrinkles, and is widely applicable to planar or curved bonding.

Description

Technical Field

[0001] This invention relates to the field of aerospace equipment, specifically to a method for bonding a flexible blanket for spacecraft to a base and the flexible blanket for spacecraft. Background Technology

[0002] As spacecraft gradually develop towards larger sizes and more multifunctionality, higher requirements are placed on indicators such as on-orbit energy supply and orbit control. The design requirements for key components such as solar arrays, large-array antennas, and solar sails are also developing towards larger sizes and greater flexibility. The flexible materials used extensively in these components are collectively referred to as "flexible blankets." The flexibility of these blankets allows for a higher packing ratio, and their end fixing is a crucial aspect of component assembly. The fixing methods for flexible blankets used in spacecraft differ from those used on the ground, requiring comprehensive consideration of factors such as deployment reliability, vacuum, extreme temperatures (typically ±90℃), temperature shock, thermal deformation and thermal stress, radiation, and usage boundaries (such as tension).

[0003] Currently, there are several common methods for fixing flexible components: one is adhesive fixing, which is a simple and effective method. Specialized adhesive is used to bond the flexible component to the desired location. Another method is mechanical fixing, typically achieved using screws, clips, pressure plates, or other fasteners. This method requires pre-drilled mounting holes and fasteners, and the installation area is larger than that of adhesive fixing. A third method is fixing using specialized clamps. These clamps need to be custom-designed according to the shape and size of the flexible component, but their high degree of specialization, design, and cost make them unsuitable for low-cost production and widespread adoption.

[0004] In summary, of the three fixing methods, adhesive bonding is the simplest and most effective. The flexible blanket can be directly adhered to the base surface, requiring almost no additional installation space and not significantly increasing the weight. Considering factors such as quality, ease of implementation, cost, and reliability, adhesive bonding is the preferred method for fixing flexible blankets used in aerospace.

[0005] However, the bonding technology for flexible blankets used in spacecraft faces the following technical challenges: (1) The adhesive used for bonding must not fail under extreme temperature conditions, and the bonding strength must meet the requirements for use. It must also have a certain resistance to radiation and should not show obvious aging or even failure within its service life. (2) The bonding process for flexible blankets used in spacecraft has strict requirements and higher requirements for positional tolerance (±0.2mm). Therefore, it must be easy to implement and convenient to position. (3) The bonding state of flexible blankets used in spacecraft must not produce defects such as breakage, bubbles (closed space), or wrinkles. Under alternating high and low temperatures and vacuum environments, breakage may extend. For example, bubbles (closed space) and wrinkles may cause defects to grow larger, which may lead to the risk of adhesive peeling. These defects are prohibited in aerospace products. (4) The bonding of flexible blankets used in aerospace should be repairable and convenient for repair under special circumstances. Summary of the Invention

[0006] In order to solve the problems existing in the prior art, the present invention provides a method for bonding a flexible blanket for spacecraft to a base and a flexible blanket for spacecraft.

[0007] According to a first aspect of this disclosure, a method for bonding a flexible blanket for spacecraft to a base is provided, the bonding method comprising the following steps: Surface treatment step: Grinding the base; Prepreg bonding steps: The first adhesive film is bonded to the bonding area of ​​the flexible blanket and heated until the first adhesive film is adhered to the flexible blanket; prepreg is placed on the first adhesive film and heated until the prepreg is fixed on the first adhesive film; Vacuum curing step: The flexible blanket is cured under vacuum conditions; Application steps: Adhere the second adhesive film to the prepreg of the flexible blanket; Bonding steps: Align the flexible blanket with the base and bond them together; Pressure curing step: The non-adhesive area of ​​the flexible blanket is wound onto the base and wrapped with tape at a predetermined tension, and then placed in a curing oven for curing.

[0008] In one embodiment of this disclosure, a protective step is provided between the surface treatment step and the prepreg bonding step: protecting the non-bonded areas of the flexible blanket with a first release fabric; and / or, The base includes an adhesive area and a non-adhesive area, and the protection step further includes protecting the non-adhesive area of ​​the base.

[0009] In one embodiment of this disclosure, in the bonding prepreg step, a compaction operation is performed during the heating process; wherein the prepreg is carbon fiber.

[0010] In one embodiment of this disclosure, the vacuum curing step further includes sequentially attaching a second release cloth, a nonwoven fabric, and a vacuum film onto the flexible blanket, and performing a vacuum treatment on the flexible blanket within the vacuum film; after the vacuum curing step, a demolding step is further included: removing the vacuum film, the second release cloth, and the nonwoven fabric.

[0011] In one embodiment of this disclosure, in the film application step, at least two second adhesive films are provided, and the at least two second adhesive films are arranged at intervals along the width direction of the flexible blanket to form an exhaust channel between adjacent two second adhesive films.

[0012] In one embodiment of this disclosure, the second adhesive film is provided with at least three strips, wherein at least one of the second adhesive films extends along the length direction of the flexible blanket.

[0013] In one embodiment of this disclosure, a release paper is provided on the outer side of each of the second adhesive films. In the bonding step, the release paper is gradually peeled off after the flexible blanket is aligned with the base, so that the second adhesive film is gradually bonded to the base.

[0014] In one embodiment of this disclosure, during the bonding step, the second adhesive film bonded to the base is heated, and air bubbles in the bonding area are removed.

[0015] In one embodiment of this disclosure, in the pressure curing step, a heat-shrinkable tape is used to wrap the flexible blanket.

[0016] According to a second aspect of this disclosure, a flexible blanket for spacecraft is provided, which is obtained by an bonding method according to a first aspect of this disclosure.

[0017] This invention employs multiple technical measures to solve a series of structural and technological challenges encountered when bonding ultra-thin blankets over large areas, such as difficulty in positioning, easy tearing, air bubbles, and wrinkles. By attaching a layer of prepreg to the bonding area of ​​the flexible blanket, it eliminates the possibility of bulging (air bubbles) in the bonding area; it also increases the structural strength of the bonding area, facilitating bonding positioning, increasing tear resistance, and reducing the risk of wrinkling during bonding.

[0018] Other features and advantages of the invention will become clear from the following detailed description of exemplary embodiments of the invention with reference to the accompanying drawings. Attached Figure Description

[0019] Figure 1 This is a schematic diagram illustrating the bonding state between the flexible blanket and the base in an embodiment of this disclosure; Figure 2 This is a flowchart illustrating the bonding process between the flexible blanket and the base in an embodiment of this disclosure. Figure 3This is a schematic diagram of the flexible blanket, the base bonding area, and the non-bonding area in an embodiment of this disclosure; Figure 4 This is a schematic diagram of the flexible blanket bonding the second adhesive film in an embodiment of this disclosure.

[0020] Icons: 1-Flexible blanket, 2-Base, 11-Non-adhesive area of ​​flexible blanket, 12-Adhesive area of ​​flexible blanket, 122-Exhaust channel, 121-Second adhesive film. Detailed Implementation

[0021] To make the inventive objectives, technical solutions, and beneficial technical effects of this application clearer, the following detailed description is provided in conjunction with specific embodiments. It should be understood that the embodiments described in this specification are merely illustrative and not intended to limit the scope of this application.

[0022] For simplicity, this paper only explicitly discloses some numerical ranges. However, any lower limit can be combined with any upper limit to form an unspecified range; and any lower limit can be combined with other lower limits to form an unspecified range, just as any upper limit can be combined with any other upper limit to form an unspecified range. Furthermore, although not explicitly stated, every point or individual value between the endpoints of a range is included within that range. Therefore, each point or individual value can serve as its own lower or upper limit and be combined with any other point or individual value, or with other lower or upper limits, to form an unspecified range.

[0023] In the description of this article, it should be noted that, unless otherwise stated, "above" and "below" include the number itself, and "several" in "one or more" means two or more.

[0024] The foregoing description of this invention is not intended to describe every disclosed embodiment or implementation. Instead, the following description provides more specific examples of exemplary embodiments. Throughout the application, guidance is provided through a series of embodiments that can be used in various combinations. The examples listed are merely representative and should not be construed as exhaustive.

[0025] This invention provides a method for bonding a flexible blanket for spacecraft to a base, mainly including steps such as surface treatment, bonding prepreg, vacuum curing, film application, bonding, and pressure curing. By bonding the flexible blanket to the base using the above method, the bonding strength between the base and the flexible blanket can be increased, avoiding defects such as bubbles and wrinkles. The method disclosed herein is widely applicable to bonding planar or curved surfaces.

[0026] Figure 1 A schematic diagram showing the bonding state between the flexible blanket of this disclosure and the base is illustrated. Figure 1In the illustrated embodiment, the base 2 is an elongated cylindrical structure with connectors at both ends for attachment to the spacecraft. The axial dimension of the base 2 matches the dimension of the flexible blanket 1 in that direction. The flexible blanket 1 can be square, rectangular, or other shapes, depending on its function on the spacecraft, and no specific limitations are imposed here. The bonding requirements between the flexible blanket 1 and the base 2 on the spacecraft are as follows: (1) Apply adhesive to the designated area of ​​the flexible blanket, such as Figure 3 As shown, the flexible blanket 1 includes an adhesive area 12 and a non-adhesive area 11. The flexible blanket 1 is bonded to the base 2 through its adhesive area 12. The base 2 has a cylindrical structure, meaning its outer surface is an arc-shaped curved surface, requiring the adhesive area 12 of the flexible blanket 1 to be bonded to the arc-shaped curved surface of the base 2. Specifically, the outer surface of the base 2 may also include an adhesive area and a non-adhesive area, meaning the flexible blanket 1 does not cover the entire surface of the base 2, but is bonded to a portion of its surface. In other embodiments, the adhesive area of ​​the base 2 may also be planar or of other shapes, which is not limited herein.

[0027] (2) The outer edge of the bonding area 12 of the flexible blanket 1 must be parallel to the axis of the base 2 within the required tolerance. The starting position of the bonding area 12 of the flexible blanket on the base 2 also has tolerance requirements. The distance between the edge of the flexible blanket 1 along the axial direction of the base 2 and the end face of the base has tolerance control requirements. By meeting the above requirements, the installation error between the flexible blanket 1 and the base 2 can be controlled within the required range.

[0028] refer to Figure 2 The method for bonding a flexible blanket for spacecraft to a base disclosed herein includes the following steps: Surface treatment steps: Grinding the base. Specifically, the bonding area of ​​the base can be ground, or for ease of processing, the entire surface of the base can be ground. Grinding the bonding area of ​​base 2 increases the surface roughness of the bonding area, thereby increasing the bonding strength between base 2 and flexible blanket 1. After grinding, excess material such as dust and debris needs to be removed from the surface of base 2 to avoid affecting the bonding strength between base 2 and flexible blanket 1 during subsequent bonding processes. In addition, the base can be pre-treated before grinding to remove oil, rust, dust, etc., adhering to its surface, depending on the specific circumstances.

[0029] Prepreg bonding steps: The first adhesive film is bonded to the bonding area of ​​the flexible blanket 1, and heated until the first adhesive film adheres to the flexible blanket; prepreg is then placed on the first adhesive film and heated until the prepreg is fixed onto the first adhesive film. (Reference) Figure 3The flexible blanket 1 is rectangular, including a non-adhesive area 11 and an adhesive area 12, with the shaded area representing the flattened state of the adhesive area 12. The first adhesive film is a thin-film adhesive made of a high-molecular polymer, typically processed through coating, stretching, or casting. It is a stable, thin-film solid at room temperature and can be directly cut to fit the bonding surface, simplifying the process. Furthermore, the adhesive film itself possesses elasticity and extensibility, allowing it to adhere not only to flat surfaces but also to slightly curved or arc-shaped surfaces. Most adhesive films require heating and pressure to achieve their adhesive properties. As the temperature rises, the adhesive film slowly softens and melts, wetting the surface of the materials to be bonded. However, upon cooling, it solidifies and bonds tightly to the materials, forming a high-strength adhesive layer. In the adhesive prepreg step of this disclosure, after the first adhesive film is bonded to the adhesive area 12 of the flexible blanket 1, heating softens the first adhesive film, allowing it to adhere and bond with the flexible blanket 1.

[0030] In one specific embodiment of this disclosure, during the prepreg bonding step, the first adhesive film is compacted during heating. Specifically, as the temperature rises, the first adhesive film slowly softens and melts, wetting the surface of the bonding area 12 of the flexible blanket. During this process, a compaction operation is performed, thereby ensuring that the first adhesive film adheres tightly to the bonding area 12 of the flexible blanket under a certain pressure. This eliminates initial gaps caused by uneven surfaces or poor adhesion. Furthermore, the pressure drives the fluid-state first adhesive film to flow into and fill irregularities such as pores and scratches in the bonding area 12 of the flexible blanket, greatly enhancing the bonding strength. Simultaneously, the compaction operation squeezes and expels any remaining micro-air bubbles from the bonding area 12.

[0031] The prepreg disclosed herein can be carbon fiber, a novel fiber material with high carbon content, possessing significant advantages such as high strength and lightweight. As a non-metallic material, carbon fiber has stable chemical properties and is suitable for spacecraft components operating under harsh conditions such as long-term on-orbit operation and deep space exploration.

[0032] The prepreg is laid on the first adhesive film and heated until it is fixed in place. The first adhesive film softens during heating, allowing the prepreg to adhere to it. Compaction of the prepreg during heating ensures uniform adhesion to the first adhesive film. This can be understood as the first adhesive film melting upon heating, allowing some of the adhesive to penetrate the gaps in the carbon fiber prepreg. Upon cooling, this allows the prepreg to bond firmly to the first adhesive film, increasing the bond strength.

[0033] In one specific embodiment of this disclosure, a protective step is provided between the surface treatment step and the prepreg bonding step: protecting the non-bonded area of ​​the flexible blanket with a first release cloth; and / or, the base includes both bonded and non-bonded areas, and the protective step further includes protecting the non-bonded area of ​​the base. Specifically, to avoid damage to the non-bonded areas during the bonding process, the non-bonded areas of the flexible blanket and the base can be protected. In embodiments of this disclosure, the first release cloth can be a polytetrafluoroethylene (PTFE) release cloth. The first release cloth is covered on the surface of the non-bonded area of ​​the base and the surface of the non-bonded area 11 of the flexible blanket for protective treatment. The release cloth acts as a physical barrier, effectively isolating the non-bonded area from the adhesive film, prepreg, etc., during the bonding process. The release cloth is a special fabric material with low surface energy and high isolation properties, used to solve the problems of finished product sticking and difficult demolding, while improving the surface smoothness of the finished product.

[0034] In the aerospace field, residual air bubbles can cause a series of hazards in the extreme environment of space. Tiny bubbles expand continuously in the vacuum, disrupting the originally smooth structure of the flexible blanket, leading to poor adhesion between the blanket and the base, or even damage to the blanket itself. Furthermore, the extreme and frequent temperature changes in space cause bubbles to continuously expand and contract, resulting in micro-cracks in the surrounding flexible blanket due to constant stretching. As these cracks gradually expand, they can cause the flexible blanket to delaminate and detach.

[0035] Therefore, the bonding method disclosed herein also includes a vacuum curing step: curing the flexible blanket under vacuum conditions. Specifically, in operation, the flexible blanket 1 can be placed on a platform, and a vacuum operation can be performed to forcibly remove any remaining air bubbles through a negative pressure environment. Then, the flexible blanket 1 is placed in a curing oven for curing, thereby further strengthening the bonding strength between the prepreg, the first adhesive film, and the flexible blanket.

[0036] In one specific embodiment of this disclosure, the vacuum curing step further includes sequentially attaching a second release cloth, a non-woven fabric, and a vacuum film to the flexible blanket, and then vacuuming the flexible blanket within the vacuum film. Following the vacuum curing step, a demolding step is also included: removing the vacuum film, the second release cloth, and the non-woven fabric. Specifically, in the vacuum curing step, the material of the second release cloth can be the same as that of the first release cloth. The second release cloth is directly attached to the bonding area, covering the prepreg and the cured first adhesive film in the bonding area. Alternatively, the second release cloth can extend to the surface of the first release cloth, thus covering the entire flexible blanket. Then, the non-woven fabric is placed on top of the second release cloth to buffer pressure and allow air to be evenly extracted during vacuuming. Finally, the entire flexible blanket is wrapped with the vacuum film, forming a sealed vacuum environment. A vacuum environment is created inside the vacuum film under the action of a vacuum pump, eliminating interlayer bubbles and compacting the carbon fibers under atmospheric pressure. The blanket is then sent to a curing oven for curing at a set temperature and pressure. After curing, remove the vacuum film, nonwoven fabric, and second release cloth in sequence. After demolding, inspect the area where the prepreg is bonded. If any prepreg extends beyond the protected area, align and remove it to ensure the dimensions of the prepreg bonding area meet design requirements.

[0037] Application Steps: The second adhesive film is bonded to the prepreg of the flexible blanket. The second adhesive film can be made of the same material as the first adhesive film. Specifically, before bonding the second adhesive film, the bonding surface of the flexible blanket can be treated. For example, the area to be bonded can be sanded to increase the subsequent bonding strength with the base and remove excess material. The second adhesive film can then be cut to the appropriate size and applied to the bonding area of ​​the flexible blanket, i.e., the surface of the flexible blanket prepreg. This area is heated, and during the heating process, a compaction operation is performed to remove internal air bubbles, ensuring the second adhesive film is completely bonded to the flexible blanket prepreg.

[0038] In one embodiment of this disclosure, during the film application step, at least two second adhesive films are provided, and these at least two second adhesive films are spaced apart along the width direction of the flexible blanket to form an air venting channel between adjacent second adhesive films. (See reference...) Figure 4The second adhesive film 121 is located in the bonding area of ​​the flexible blanket, and the second adhesive films 121 are arranged at intervals along the width direction of the flexible blanket, forming an exhaust channel 122 between each pair of adjacent second adhesive films 121. Specifically, the second adhesive films 121 are not bonded to the entire bonding area of ​​the flexible blanket, but are arranged in strips at predetermined intervals. In this embodiment, since the width direction of the flexible blanket needs to be bonded to the axial direction of the base, each second adhesive film 121 needs to completely cover the width direction of the flexible blanket, thereby forming an exhaust channel 122 between two adjacent second adhesive films 121. This allows air bubbles at the second adhesive film 121 to be discharged through the exhaust channel 122 during the subsequent bonding process with the base 2, thus ensuring that the second adhesive film 121 can adhere to the flexible blanket and the base.

[0039] In one specific embodiment of this disclosure, at least three second adhesive films are provided, wherein at least one of the second adhesive films 121 extends along the length direction of the flexible blanket. (See reference...) Figure 4 Four second adhesive films are provided, three of which are arranged at intervals along the width direction of the flexible blanket, and one extends along the length direction of the flexible blanket within the bonding area, interleaving with the three second adhesive films arranged in the width direction. At least one second adhesive film extending along the length direction of the flexible blanket forms a force resisting lateral tensile force, which, together with the second adhesive film along the width of the flexible blanket providing a shear force resisting downward sliding, constitutes a mesh-like structure, enhancing the adhesion between the flexible blanket and the base.

[0040] Bonding Steps: Align the flexible blanket with the base and bond it. Specifically, first, align the bonding area of ​​the flexible blanket with the base along its axial direction, and then bond it along the circumference of the base 2. In one specific embodiment of this disclosure, a release paper is provided on the outer side of each second adhesive film. In the bonding step, after aligning the flexible blanket with the base, the release paper is gradually peeled off so that the second adhesive film is gradually bonded to the base. After bonding, if there is a deviation in the installation position, the bonding area can be heated to soften the second adhesive film, and the bonding position of the flexible blanket can be adjusted until the design requirements are met.

[0041] In one embodiment of this disclosure, during the bonding step, the second adhesive film bonded to the base is heated to remove air bubbles from the bonding area. Specifically, the bonded second adhesive film is heated to a certain temperature to soften it, thereby bonding the flexible blanket to the base through the second adhesive film. Simultaneously, a silk cloth can be used to remove internal air bubbles, ensuring complete adhesion between the flexible blanket and the base. This is because the base is a cylindrical structure with a continuously changing curved surface; the silk cloth can completely conform to any angle of the curved surface, ensuring pressure is applied to the entire area of ​​the base, thereby expelling any residual air.

[0042] Pressure curing step: The non-bonded area of ​​the flexible blanket is wound onto the base, and adhesive tape is used to wrap it at a predetermined tension, followed by curing in a curing oven. Specifically, after the bonding area 12 of the flexible blanket is bonded to the bonding area of ​​the base, the non-bonded area of ​​the flexible blanket can be wound onto the base. In this disclosure, polyimide tape is used to fix it at the end of the base to ensure the stability of the bonding area, and then it is placed into a curing oven for curing. This disclosure does not limit the type of tape used.

[0043] In one specific embodiment of this disclosure, a heat-shrinkable tape is used to wrap the flexible blanket during the pressure curing step. The heat-shrinkable tape is a strip material made from a high-performance thermoplastic or thermosetting resin as a base material, supplemented with functional additives such as toughening agents, flame retardants, and UV stabilizers. Upon heating, it can shrink radially and tightly adhere to the surface of the object being covered. The type of heat-shrinkable tape is not limited in this disclosure. Specifically, this disclosure uses heat-shrinkable tape to wrap and tighten the bonding area between the base and the flexible blanket at a certain tension, and then places it in a curing oven for curing at a set temperature and pressure. When the second adhesive film softens, and even the first adhesive film softens to a certain extent, the pressure applied by the heat-shrinkable tape to the flexible blanket on the base gradually increases after heating, thereby improving the bonding strength between the adhesive structures and ensuring a tight bond between the flexible blanket and the base. In subsequent steps, the protective layer and excess adhesive on the base and flexible blanket can be cleaned, and the appearance can be inspected; relevant equipment can also be used to detect flaws and check for delamination or bulging.

[0044] This invention also provides a flexible blanket for spacecraft, obtained by bonding the flexible blanket to a base. The flexible blanket obtained by this bonding method has high structural strength, is easy to bond and position, and is not prone to wrinkling.

[0045] The bonding method disclosed herein eliminates potential bulging (air bubbles) during bonding of the flexible blanket by attaching a layer of prepreg to the bonding area, increasing the structural strength of the bonding location, facilitating bonding positioning, and enhancing tear resistance. Furthermore, the increased blanket stiffness also eliminates the risk of bonding wrinkles. A "slice" bonding process is used between the prepreg and the base, ensuring bonding strength while avoiding the risk of air bubbles and providing venting channels. This bonding method for spacecraft flexible blankets to bases solves a series of structural and technological challenges faced when bonding ultra-thin blankets over large areas, including difficulties in positioning, tearing, air bubbles, and wrinkles. This process has a wide range of applications, adaptable from aerospace to ground use, and also provides guidance for bonding ultra-large area flexible blankets.

[0046] The various embodiments of the present invention have been described above. These descriptions are exemplary and not exhaustive, and are not limited to the disclosed embodiments. Many modifications and variations will be apparent to those skilled in the art without departing from the scope and spirit of the described embodiments. The terminology used herein is chosen to best explain the principles, practical application, or technical improvements to the embodiments in the market, or to enable others skilled in the art to understand the embodiments disclosed herein. The scope of the invention is defined by the appended claims.

Claims

1. A method for bonding a flexible blanket for spacecraft to a base, characterized in that, The flexible blanket includes an adhesive area and a non-adhesive area; the bonding method includes the following steps: Surface treatment step: Grinding the base; Prepreg bonding steps: The first adhesive film is bonded to the bonding area of ​​the flexible blanket and heated until the first adhesive film is adhered to the flexible blanket; prepreg is placed on the first adhesive film and heated until the prepreg is fixed on the first adhesive film; Vacuum curing step: The flexible blanket is cured under vacuum conditions; Application steps: Adhere the second adhesive film to the prepreg of the flexible blanket; Bonding steps: Align the flexible blanket with the base and bond them together; Pressure curing step: The non-adhesive area of ​​the flexible blanket is wound onto the base and wrapped with tape at a predetermined tension, and then placed in a curing oven for curing.

2. The bonding method according to claim 1, characterized in that, A protective step is provided between the surface treatment step and the prepreg bonding step: the non-bonded areas of the flexible blanket are protected using a first release fabric; and / or, The base includes an adhesive area and a non-adhesive area, and the protection step further includes protecting the non-adhesive area of ​​the base.

3. The bonding method according to claim 1, characterized in that, In the bonding prepreg step, a compaction operation is performed during the heating process; wherein the prepreg is carbon fiber.

4. The bonding method according to claim 1, characterized in that, The vacuum curing step further includes attaching a second release cloth, a non-woven fabric, and a vacuum film sequentially onto the flexible blanket, and performing a vacuum treatment on the flexible blanket inside the vacuum film; after the vacuum curing step, a demolding step is also included: removing the vacuum film, the second release cloth, and the non-woven fabric.

5. The bonding method according to claim 1, characterized in that, In the film application step, at least two second adhesive films are provided, and the at least two second adhesive films are arranged at intervals along the width direction of the flexible blanket to form an air venting channel between adjacent two second adhesive films.

6. The bonding method according to claim 5, characterized in that, The second adhesive film is provided with at least three strips, at least one of which extends along the length of the flexible blanket.

7. The bonding method according to claim 5, characterized in that, Each of the second adhesive films has a release paper on its outer side. In the bonding step, after aligning the flexible blanket with the base, the release paper is gradually peeled off so that the second adhesive film is gradually bonded to the base.

8. The bonding method according to claim 7, characterized in that, In the bonding step, the second adhesive film bonded to the base is heated, and air bubbles in the bonding area are removed.

9. The bonding method according to claim 1, characterized in that, In the pressure curing step, heat shrinkable tape is used to wrap the flexible blanket.

10. A flexible blanket for spacecraft, characterized in that, The flexible blanket is obtained by the bonding method according to any one of claims 1 to 9.

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