Multi-layer damping skin structure and integrated test cabinet skin
Through the multi-layer shock-absorbing skin structure, the use of carbon fiber composite materials and damping rubber layer design solves the problems of high spacecraft material weight and poor vibration reduction effect, achieves lightweight materials and vibration reduction effect, reduces space launch energy consumption, and increases carrying space.
Patent Information
- Application Number
- CN202422754629.7
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-11-12
- Publication Date
- 2025-09-12
- Estimated Expiration
- 2034-11-12
AI Technical Summary
Existing spacecraft materials are heavy and have poor vibration damping effects in extreme environments, resulting in high launch energy consumption and easy damage to equipment due to vibration.
A multi-layer shock-absorbing skin structure is adopted, including an outer skin layer, a shock-absorbing layer and an inner skin layer. The outer skin layer and the inner skin layer are paved with carbon fiber reinforced epoxy resin prepreg, the shock-absorbing layer is paved with damping rubber, and structural adhesive film is laid between the skin layers to form a composite material structure.
Significantly reduce material weight, reduce energy consumption of space launches, improve equipment's vibration resistance in vibration environments, and increase cargo space.
Smart Images
Figure CN223327112U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the technical field of composite products, in particular to a testing machine. Background Art
[0002] Given the extreme environment of space, the raw materials used to construct artificial celestial bodies and spacecraft capable of launching beyond Earth's atmosphere place extremely high demands on the materials used. Since a rocket consumes approximately 50 kg of energy for every kg of weight launched, reducing the weight of materials during launch is crucial for energy efficiency. Furthermore, vibrations during launch significantly impact the equipment being launched, necessitating extremely high vibration damping requirements. Materials that can both reduce the weight of equipment and effectively dampen its own vibrations are currently in high demand in the aerospace industry.
[0003] The scientific experiment cabinet is a test cabinet set up in the space station, in which a series of scientific experiments can be carried out. There are a large number of such cabinets in the space station. The reduction of their own weight and the ability to use vibration-damping materials will undoubtedly play a huge role in the construction of the space station. Utility Model Content
[0004] In view of the deficiencies in the prior art, the utility model provides an integrated test cabinet skin to achieve the purpose of reducing the weight of the test cabinet.
[0005] The purpose of the utility model is achieved as follows: a multi-layer shock-absorbing skin structure, including an outer skin layer, a shock-absorbing layer and an inner skin layer, the outer skin layer and the inner skin layer are both paved with carbon fiber reinforced epoxy resin prepreg, and the shock-absorbing layer is paved with damping rubber.
[0006] Furthermore, a structural adhesive film is laid between the outer skin and the damping rubber layer, and between the damping rubber layer and the inner skin.
[0007] An integrated test cabinet skin, comprising:
[0008] The composite skin is box-shaped, with an open bottom, side openings on both sides, and a top opening on the top;
[0009] The skin side cover is in the form of a flat plate and is installed on the side opening of the composite skin;
[0010] The skin top cover is flat and installed on the top opening of the composite skin;
[0011] The composite skin, skin side cover and skin top cover are all multi-layer shock-absorbing skin structures, which include an outer skin layer, a shock-absorbing layer and an inner skin layer. The outer skin layer and the inner skin layer are both made of carbon fiber reinforced epoxy resin prepreg, and the shock-absorbing layer is made of damping rubber.
[0012] Furthermore, a structural adhesive film is laid between the outer skin and the damping rubber layer, and between the damping rubber layer and the inner skin.
[0013] Furthermore, bolt holes are provided on the composite skin, the skin side covers and the skin top cover, and the skin side covers and the skin top cover are fixed to the composite skin by bolts.
[0014] Furthermore, a cross-shaped rib is provided on the top of the skin roof cover.
[0015] Compared with the prior art, the beneficial effects of the present invention are:
[0016] The utility model adopts carbon fiber composite materials to make the cabinet skin, which greatly reduces the weight of the skin and reduces the energy consumption of space launch; by arranging a shock-absorbing layer between the inner skin and the outer skin, it not only ensures the structural strength of the cabinet skin but also plays a vibration reduction role, reduces the use of dampers, reduces energy consumption during space launch, and optimizes the equipment placement space, so that the space for carrying cargo can be increased during a single launch. BRIEF DESCRIPTION OF THE DRAWINGS
[0017] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are merely embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on the provided drawings without paying any creative work.
[0018] Figure 1 This is a structural diagram of Example 1 of the present utility model.
[0019] Figure 2 This is a structural diagram of Example 2 of the present utility model.
[0020] Figure 3 This is an exploded view of Example 2 of the present utility model.
[0021] Among them, 101 is the outer skin layer, 102 is the shock-absorbing layer, 103 is the inner skin layer, 104 is the structural adhesive film, 200 is the composite skin, 300 is the skin side cover, 400 is the skin top cover, and 401 is the cross-shaped rib plate. DETAILED DESCRIPTION
[0022] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the embodiments described are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.
[0023] Example 1
[0024] like Figure 1 A multi-layer shock-absorbing skin structure shown includes an outer skin layer 101, a shock-absorbing layer 102 and an inner skin layer 103. The outer skin layer 101 and the inner skin layer 103 are both made of carbon fiber reinforced epoxy resin prepreg, and the shock-absorbing layer 102 is made of damping rubber.
[0025] Specifically, the carbon fiber reinforced epoxy resin prepreg uses T800 grade carbon fiber reinforced epoxy resin prepreg, and the damping rubber uses ZN-1 damping rubber. The two are mixed and laid. After laying, they are put into an autoclave at high temperature and high pressure for curing and molding. When laying, the shape of the specific mold can be selected according to needs.
[0026] Furthermore, a structural adhesive film 104 is laid between the outer skin and the damping rubber layer, and between the damping rubber layer and the inner skin.
[0027] It should be noted that the function of the structural adhesive film 104 is to ensure the bonding strength between the damping rubber and the prepreg.
[0028] Example 2
[0029] like Figure 2-3 An integrated test cabinet skin is shown, comprising:
[0030] The composite skin 200 is box-shaped, with an open bottom, side openings on both sides, and a top opening on the top;
[0031] The skin side cover 300 is in the form of a flat plate and is installed on the side opening of the composite skin 200;
[0032] The skin top cover 400 is flat and installed on the top opening of the composite skin 200;
[0033] The composite skin 200, the skin side cover 300, and the skin top cover 400 are all multi-layer shock-absorbing skin structures. The multi-layer shock-absorbing skin structure includes an outer skin layer 101, a shock-absorbing layer 102, and an inner skin layer 103. The outer skin layer 101 and the inner skin layer 103 are both made of carbon fiber reinforced epoxy resin prepreg, and the shock-absorbing layer 102 is made of damping rubber.
[0034] Specifically, the carbon fiber reinforced epoxy resin prepreg uses T800 grade carbon fiber reinforced epoxy resin prepreg, and the damping rubber uses ZN-1 damping rubber. A negative mold is used for paving, and the two are mixed and paved. After paving is completed, they are put into an autoclave for high temperature and high pressure curing and molding. The shape of the specific mold can be selected according to needs during paving.
[0035] It should be noted that aviation equipment generally requires that the product surface must be smooth and without sharp edges. Once a person in space is scratched by a sharp object, the bleeding is difficult to stop. Therefore, the mold surface of the cabinet body skin must be smooth and without defects, and must be made using a negative mold.
[0036] Furthermore, a structural adhesive film 104 is laid between the outer skin and the damping rubber layer, and between the damping rubber layer and the inner skin.
[0037] It should be noted that the function of the structural adhesive film 104 is to ensure the bonding strength between the damping rubber and the prepreg.
[0038] Furthermore, bolt holes are provided on the composite skin 200 , the skin side covers 300 , and the skin top cover 400 , and the skin side covers 300 and the skin top cover 400 are fixed to the composite skin 200 by bolts.
[0039] Furthermore, a cross-shaped rib 401 is provided on the top of the skin top cover 400 .
[0040] It should be noted that the design of the cross-shaped ribs 401 can enhance the strength of the skin top plate.
[0041] In summary, the present invention adopts carbon fiber composite materials to make cabinet skin, which greatly reduces the weight of the skin and reduces the energy consumption of space launch; the present invention adopts a mixed laying method of damping material and structural material, which not only ensures the structural strength of the cabinet skin but also plays a vibration reduction role, reduces the use of dampers, reduces energy consumption during space launch, and optimizes the equipment placement space, so that the space for carrying cargo can be increased during a single launch; the cabinet skin is made of composite materials, and its external dimensions are guaranteed by the mold. The cabinet skins produced in batches with a single set of molds are completely consistent in size and can be interchanged, effectively ensuring the spatial layout and installation accuracy in the space station, while reducing the maintenance difficulty for astronauts.
[0042] The above embodiments are only intended to help understand the method and core concept of the present invention. It should be noted that those skilled in the art can make various improvements and modifications to the present invention without departing from the principles of the present invention, and such improvements and modifications also fall within the scope of protection of the claims of the present invention.
Claims
1. A multi-layer shock-absorbing skin structure, characterized in that: It comprises an outer skin layer, a shock-absorbing layer and an inner skin layer. The outer skin layer and the inner skin layer are both made of carbon fiber reinforced epoxy resin prepreg, and the shock-absorbing layer is made of damping rubber.
2. The multi-layer shock-absorbing skin structure according to claim 1, characterized in that: Structural adhesive films are laid between the outer skin and the damping rubber layer, and between the damping rubber layer and the inner skin.
3. An integrated test cabinet skin, characterized in that: include: The composite skin is box-shaped, with an open bottom, side openings on both sides, and a top opening on the top; The skin side cover is in the form of a flat plate and is installed on the side opening of the composite skin; The skin top cover is flat and installed on the top opening of the composite skin; The composite skin, skin side cover and skin top cover are all multi-layer shock-absorbing skin structures, which include an outer skin layer, a shock-absorbing layer and an inner skin layer. The outer skin layer and the inner skin layer are both made of carbon fiber reinforced epoxy resin prepreg, and the shock-absorbing layer is made of damping rubber.
4. The integrated test cabinet skin according to claim 3, characterized in that: Structural adhesive films are laid between the outer skin and the damping rubber layer, and between the damping rubber layer and the inner skin.
5. The integrated test cabinet skin according to claim 3 or 4, characterized in that: Bolt holes are provided on the composite skin, the skin side cover and the skin top cover, and the skin side cover and the skin top cover are fixedly mounted on the composite skin by means of bolts.
6. The integrated test cabinet skin according to claim 3 or 4, characterized in that: A cross-shaped rib is provided on the top of the skin roof.