Ablation control surface coating structure

Abstract

The utility model discloses an ablative control surface coating structure, and relates to the technical field of control surface coating structures, the ablative control surface coating structure comprises a base body, protective coatings are sprayed on the upper surface and the lower surface of the base body, each protective coating comprises a hard layer and a soft layer, the hard layers and the soft layers are alternately distributed in the protective coatings, the hard layers are sprayed on the outermost portions of the protective coatings, nano-coatings are sprayed between the two protective coatings and the base body, wear-resistant coatings are sprayed on one sides of the opposite faces of the two protective coatings, and the wear-resistant coatings are coated on the other sides of the opposite faces of the two protective coatings. According to the scheme, the problems that in the using process of an existing control surface, due to the instability of the structure of the existing control surface, melting is caused, consequently, equipment is greatly affected, loss is increased, cost is increased, and the service life of the control surface is prolonged are solved. And therefore, improvement needs to be carried out.

Description

Technical Field

[0001] This utility model relates to the field of rudder surface coating structure technology, specifically to an ablation rudder surface coating structure. Background Technology

[0002] Control surfaces are aerodynamic surfaces that use deflection in airflow to generate balancing and control forces to maneuver missiles. They are also called control surfaces. Control surfaces are the control surfaces of an aircraft, typically in three directions: the horizontal one is called the elevator (or horizontal stabilizer), which controls the aircraft's ascent and descent; the vertical one is called the rudder, usually located on the vertical stabilizer, which controls the aircraft's heading; and the tilting one is called the aileron, usually located at the wingtips, which controls the aircraft's tilt.

[0003] However, existing control surfaces are prone to melting during use due to structural instability, which can significantly impact equipment, increase losses, and raise costs, thus requiring improvement. Utility Model Content

[0004] The purpose of this invention is to provide an ablation rudder surface coating structure to solve the problem mentioned in the background art that the existing rudder surface melts during use due to the instability of its own structure, which causes great impact on the equipment, increases losses, and raises costs, thus requiring improvement.

[0005] To achieve the above objectives, this utility model provides the following technical solution: an ablation rudder surface coating structure, comprising a substrate, wherein a protective coating is sprayed on both the upper and lower surfaces of the substrate, the protective coating comprising a hard layer and a soft layer, the hard layer and the soft layer being alternately distributed within the protective coating, and the outermost layer of the protective coating being sprayed with the hard layer, a nano-coating being sprayed between the two protective coating layers and the substrate, a wear-resistant coating being sprayed on one side opposite to the two protective coating layers, and an ablation coating being sprayed on one side opposite to the two wear-resistant coating layers, the ablation coating comprising an ablation layer, a transition layer and a heat insulation layer, the ablation layer being located on the outer surface of the ablation coating, and the heat insulation layer being located on the inner surface of the ablation coating.

[0006] Preferably, the nanocoating comprises nanomaterials and an organic solvent, wherein the nanomaterials are polymeric nanomaterials and the organic solvent is ethyl acetate.

[0007] Preferably, the hard layer is made of a nitride material, and the soft layer is made of a polymer soft material.

[0008] Preferably, the wear-resistant coating is a silicon carbide coating.

[0009] Preferably, the ablation layer is made of polyimide material.

[0010] Preferably, the heat insulation layer is made of phenolic resin material.

[0011] Preferably, the transition layer is located between the ablation layer and the heat insulation layer, and the transition layer is made of a metal oxide material.

[0012] Compared with the prior art, the beneficial effects of this utility model are:

[0013] This invention combines the advantages of hard and soft layers through a protective coating, providing excellent mechanical properties, wear resistance, and corrosion resistance. The nano-coating enhances the adhesion between the protective coating and the substrate, ensuring a more secure bond and reducing the risk of detachment. The ablation process, involving the decomposition, melting, evaporation, and sublimation of the coating at high temperatures, removes a significant amount of heat, preventing the control surface from burning or deforming due to high temperatures. This ensures the stability and safety of the control surface during high-speed flight, solving the problem that existing control surfaces, due to their structural instability, melt during use, causing significant damage to equipment, increasing losses, and raising costs, thus necessitating improvements. Attached Figure Description

[0014] Figure 1 This is a schematic diagram of the overall structure of this utility model;

[0015] Figure 2 This is a partial enlarged view of point A of this utility model;

[0016] Figure 3 This is a partial enlarged view of section B of this utility model;

[0017] Figure 4 This is a partial enlarged view of point C in this utility model;

[0018] In the figure: 1. Substrate; 2. Nanocoating; 3. Nanomaterial; 4. Organic solvent; 5. Protective coating; 6. Hard layer; 7. Soft layer; 8. Wear-resistant coating; 9. Ablation coating; 10. Ablation layer; 11. Transition layer; 12. Thermal insulation layer. Detailed Implementation

[0019] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present utility model. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments.

[0020] Please see Figure 1-4This utility model provides an embodiment of an ablation rudder surface coating structure, comprising a substrate 1. A protective coating 5 is sprayed onto both the upper and lower surfaces of the substrate 1. The protective coating 5 comprises a hard layer 6 and a soft layer 7, which are alternately distributed within the protective coating 5. The outermost layer of the protective coating 5 is coated with the hard layer 6, combining the advantages of both the hard layer 6 and the soft layer 7, providing excellent mechanical properties, wear resistance, and corrosion resistance. A nano-coating 2 is sprayed between the two protective coating layers 5 and the substrate 1. The nano-coating 2 comprises nanomaterials 3 and an organic solvent 4. The nanomaterials 3 are high-molecular nanomaterials, and the organic solvent 4 is ethyl acetate. The nano-coating 2 can significantly improve the adhesion between the protective coating 5 and the substrate 1, ensuring a more robust protective coating 5. The two protective coatings 5 ​​are attached to the surface of the substrate 1 to reduce the risk of detachment. A wear-resistant coating 8 is sprayed on one side of the back of the two protective coatings 5. The wear-resistant coating 8 is made of silicon carbide and can improve the compressive strength of the substrate 1. An ablation coating 9 is sprayed on one side of the back of the two wear-resistant coatings 8. The ablation coating 9 includes an ablation layer 10, a transition layer 11 and a heat insulation layer 12. The ablation layer 10 is located on the outer surface of the ablation coating 9 and the heat insulation layer 12 is located on the inner surface of the ablation coating 9. The ablation coating 9 will decompose, melt, evaporate and sublimate at high temperature. Through these physical and chemical changes, it consumes its own mass and carries away a large amount of heat, thereby preventing the control surface from burning or deforming due to high temperature. It can ensure the stability and safety of the control surface in high-speed flight. By spraying multiple coatings, the stability of the substrate 1 structure can be effectively improved.

[0021] Please see Figure 3 The hard layer 6 is made of nitride material, which has good wear resistance and scratch resistance, and can effectively protect the substrate 1 from external wear and impact. The soft layer 7 is made of polymer soft material, which has good elasticity and toughness, and can absorb energy when the protective coating 5 is impacted, reducing damage and peeling.

[0022] Please see Figure 4 The ablation layer 10 is made of polyimide material, which can maintain structural integrity and chemical stability at high temperatures and prevent thermal corrosion from damaging the control surface structure. The heat insulation layer 12 is made of phenolic resin material, which can further isolate heat and reduce heat conduction to other parts of the control surface. The transition layer 11 is located between the ablation layer 10 and the heat insulation layer 12. The transition layer 11 is made of metal oxide material, which can further enhance the overall thermal protection capability of the material.

[0023] It will be apparent to those skilled in the art that this invention is not limited to the details of the exemplary embodiments described above, and that it can be implemented in other specific forms without departing from the spirit or essential characteristics of this invention. Therefore, the embodiments should be considered illustrative and non-limiting in all respects, and the scope of this invention is defined by the appended claims rather than the foregoing description. Thus, it is intended that all variations falling within the meaning and scope of equivalents of the claims be included within this invention. No reference numerals in the claims should be construed as limiting the scope of the claims.

Claims

1. An ablation rudder surface coating structure, comprising a substrate (1), characterized in that: The upper and lower surfaces of the substrate (1) are coated with a protective coating (5). The protective coating (5) includes a hard layer (6) and a soft layer (7). The hard layer (6) and the soft layer (7) are alternately distributed inside the protective coating (5). The outermost part of the protective coating (5) is coated with the hard layer (6). A nano coating (2) is coated between the two protective coatings (5) and the substrate (1). A wear-resistant coating (8) is coated on one side of the two protective coatings (5) opposite to each other. An ablation coating (9) is coated on one side of the two wear-resistant coatings (8) opposite to each other. The ablation coating (9) includes an ablation layer (10), a transition layer (11), and a heat insulation layer (12). The ablation layer (10) is located on the outer surface of the ablation coating (9), and the heat insulation layer (12) is located on the inner surface of the ablation coating (9).

2. The ablation rudder surface coating structure according to claim 1, characterized in that: The nanocoating (2) includes nanomaterials (3) and organic solvents (4), wherein the nanomaterials (3) are polymeric nanomaterials and the organic solvents (4) are ethyl acetate solvents.

3. The ablation rudder surface coating structure according to claim 1, characterized in that: The hard layer (6) is made of nitride material, and the soft layer (7) is made of polymer soft material.

4. The ablation rudder surface coating structure according to claim 1, characterized in that: The wear-resistant coating (8) is a silicon carbide coating.

5. The ablation rudder surface coating structure according to claim 1, characterized in that: The ablation layer (10) is made of polyimide material.

6. The ablation rudder surface coating structure according to claim 1, characterized in that: The heat insulation layer (12) is made of phenolic resin material.

7. The ablation rudder surface coating structure according to claim 1, characterized in that: The transition layer (11) is located between the ablation layer (10) and the heat insulation layer (12), and the transition layer (11) is made of metal oxide material.

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