Ablation-resistant coating structure for rudder sheet

Abstract

The utility model discloses an ablation-resistant coating structure for a rudder sheet, relates to the field of rudder sheets, and aims to solve the problems that in the prior art, the temperature of the rudder sheet is high due to large friction between the rudder sheet and air during high-speed flight, and the rudder sheet is easy to damage after being used for a long time due to the fact that the existing rudder sheet is not provided with an ablation-resistant structure. The rudder sheet comprises a center plate and an ablation-resistant coating, the ablation-resistant coating comprises a base material layer, a middle transition layer and a surface ablation-resistant layer, the front end of one side of the rudder sheet is fixedly connected with a connecting shaft, and one side of the connecting shaft is connected with a driving shaft. In the utility model, the surface ablation-resistant layer is used as a first defensive line in direct contact with high-temperature airflow, and is made of polytetrafluoroethylene which is a material with extremely high melting point, excellent oxidation resistance and chemical stability, so that the surface ablation-resistant layer can be kept intact even in an extremely high-temperature environment, the ablation phenomenon is effectively prevented, and the long-term stable operation of the rudder sheet is ensured.

Description

Technical Field

[0001] This utility model relates to the field of rudder blades, specifically to an ablation-resistant coating structure for rudder blades. Background Technology

[0002] During the flight of missiles, rockets, and other aircraft, control blades, as crucial components for controlling the aircraft's flight direction, must withstand extremely high temperatures and pressures. Traditional control blade materials often cannot withstand such extreme environments, easily experiencing thermal deformation, ablation, or even failure, thus affecting the flight stability and safety of the aircraft. Therefore, developing a coating structure with high ablation resistance is of great significance for improving the flight performance and safety of aircraft.

[0003] For example, patent announcement number CN 216115657 U discloses a folding rudder structure, including a rudder holder and a folding rudder. A catapult pin and a pin spring are installed at the center of each of the two pin mounting holes. Two pin positioning holes corresponding to the catapult pins are opened at the bottom of the folding rudder. Two rudder torsion springs are installed between the rudder holder and the folding rudder. Torsion spring mounting holes corresponding to the two rudder torsion springs are opened on both sides of the top of the rudder holder and both sides of the bottom of the folding rudder. A beak-like shape is provided on both sides of the top of the rudder holder and one side of the bottom of the folding rudder. The rudder holder and the folding rudder are rotatably connected by a rotating shaft. This utility model, through the design of a folding rudder structure, can meet the folding requirements of the servo motor's rudder, reducing the space occupied during servo motor storage and transportation. It also has advantages such as convenient storage, transportation, and launch, and makes the unfolded state of the rudder wing as close as possible to an integrated rudder wing, ensuring the working state and accuracy of the servo motor.

[0004] Because the rudder blades experience high friction with the air during high-speed flight, their temperatures are also high. Currently, none of the rudder blades have an ablation-resistant structure, making them prone to damage after prolonged use. Therefore, there is an urgent market need to develop an ablation-resistant coating structure for rudder blades to help solve the existing problems. Utility Model Content

[0005] The purpose of this invention is to provide an ablation-resistant coating structure for rudder blades, in order to solve the problem mentioned in the background art that due to the high friction between the rudder blades and the air during high-speed flight, the rudder blades have high temperatures, and existing rudder blades do not have an ablation-resistant structure, making them prone to damage after long-term use.

[0006] To achieve the above objectives, this utility model provides the following technical solution: an ablation-resistant coating structure for a rudder blade, comprising a rudder blade, the rudder blade comprising a center plate and an ablation-resistant coating, the ablation-resistant coating comprising a base material layer, an intermediate transition layer and a surface ablation-resistant layer, a connecting shaft fixedly connected to one front end of one side of the rudder blade, and a drive shaft connected to one side of the connecting shaft.

[0007] Preferably, the base material layer covers the outer surface of the center plate, the intermediate transition layer covers the outer surface of the base material layer, and the surface ablation-resistant layer covers the outer surface of the intermediate transition layer.

[0008] Preferably, the base material layer is made of epoxy resin, the intermediate transition layer is made of ceramic, and the surface ablation-resistant layer is made of polytetrafluoroethylene.

[0009] Preferably, one end of the connecting shaft passes through the ablation-resistant coating and is fixedly connected to the center plate.

[0010] Preferably, a connecting pipe is fixedly connected to one side of the drive shaft, and the connecting shaft is inserted into the connecting pipe.

[0011] Preferably, the drive shaft is provided with limit grooves at both the upper and lower ends, and the connecting tube is fixedly provided with limit parts at both the upper and lower ends. After the connecting shaft is inserted into the connecting tube, the two limit parts are respectively inserted into the two limit grooves.

[0012] Preferably, the connecting pipe and the connecting shaft are fixedly connected by multiple bolts.

[0013] Compared with the prior art, the beneficial effects of this utility model are:

[0014] In this invention, the surface ablation-resistant layer, as the first line of defense directly in contact with the high-temperature airflow, uses polytetrafluoroethylene, a material with extremely high melting point, excellent oxidation resistance and chemical stability. It can remain intact even under extreme high-temperature environments, effectively preventing ablation and ensuring the long-term stable operation of the rudder blade.

[0015] In this invention, the base material layer, acting as a bridge between the coating and the center plate, utilizes an epoxy resin material with high bonding strength and good flexibility. This not only ensures that the coating adheres firmly to the surface of the center plate and is not easily detached, but also absorbs and disperses external impact forces to a certain extent, protecting the control blades from mechanical damage. The intermediate transition layer cleverly uses a ceramic material, whose low thermal conductivity effectively isolates the transmission of external high temperatures to the interior of the control blades, mitigating the impact of thermal stress on the coating and the control blade body. Its high thermal shock resistance ensures that the coating remains structurally stable and is not prone to cracking even under rapid temperature changes. This multi-layered ablation-resistant coating not only significantly improves the coating's ablation resistance but also enhances the overall bonding force between the coating and the control blade body through the complementary properties of each layer, effectively avoiding the risk of coating detachment or failure, and providing a solid guarantee for the safe flight of the aircraft.

[0016] In this utility model, the connection design between the connecting shaft and the drive shaft fully demonstrates its ingenuity and practicality. Through the clever combination of the limiting part and the bolts, a stable yet flexible connection is achieved between the rudder and the drive shaft. The design of the limiting part ensures that the connecting shaft can be accurately positioned after being inserted into the connecting tube of the drive shaft, preventing problems such as poor rotation or failure due to loosening or misalignment. At the same time, the tightening effect of the bolts further enhances the stability of the connection, allowing the rudder to maintain stable rotational performance even in high-speed flight and complex aerodynamic environments. Furthermore, this connection method fully considers the convenience and efficiency of maintenance. When the rudder needs repair or replacement, simply removing the bolts easily separates the connecting shaft from the drive shaft, greatly simplifying the maintenance process and reducing maintenance costs. Attached Figure Description

[0017] Figure 1 This is a front view of an ablation-resistant coating structure for a rudder blade according to the present invention;

[0018] Figure 2 This is a front sectional view of the present invention;

[0019] Figure 3 This is a side sectional view of the present invention;

[0020] Figure 4 This is a side sectional view of the connecting shaft of this utility model;

[0021] Figure 5 This is a detailed enlarged view of part A of the present invention;

[0022] In the diagram: 1. Rudder plate; 101. Center plate; 2. Erosion-resistant coating; 201. Base material layer; 202. Intermediate transition layer; 203. Surface erosion-resistant layer; 204. Semi-circular chamfer structure; 3. Connecting shaft; 301. Limiting groove; 4. Drive shaft; 401. Connecting pipe; 402. Limiting part; 403. Bolt. Detailed Implementation

[0023] 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.

[0024] Please see Figure 1-5This utility model provides an embodiment of an ablation-resistant coating structure for a rudder blade, comprising a rudder blade 1, which includes a center plate 101 and an ablation-resistant coating 2. The ablation-resistant coating 2 includes a base material layer 201, an intermediate transition layer 202, and a surface ablation-resistant layer 203. The base material layer 201 covers the outer surface of the center plate 101 and acts as a bridge between the coating and the center plate 101. It is made of epoxy resin material with high bonding strength and good flexibility, which not only ensures that the coating can be firmly adhered to the surface of the center plate 101 and is not easy to fall off, but also absorbs and disperses the impact force from the outside to a certain extent, protecting the rudder blade 1 from mechanical damage. The intermediate transition layer 202 covers the outer surface of the base material layer 201 and is made of ceramic. The intermediate transition layer 202 is made of ceramic material, whose low thermal conductivity effectively isolates the transmission of external high temperature to the interior of the rudder 1, reducing the impact of thermal stress on the ablation-resistant coating 2 and the rudder 1 body. Its high thermal shock resistance ensures that the ablation-resistant coating 2 can maintain structural stability and is not prone to cracking when subjected to rapid temperature changes. The surface ablation-resistant layer 203 covers the outer surface of the intermediate transition layer 202 and is made of polytetrafluoroethylene. As the first line of defense that comes into direct contact with the high-temperature airflow, the surface ablation-resistant layer 203 uses polytetrafluoroethylene, a material with extremely high melting point, excellent oxidation resistance and chemical stability. It can remain intact even in extreme high-temperature environments, effectively preventing ablation and ensuring the long-term stable operation of the rudder 1.

[0025] Please see Figure 2 and Figure 4 A connecting shaft 3 is fixedly connected to one front end of the rudder 1. A drive shaft 4 is connected to one side of the connecting shaft 3. One end of the connecting shaft 3 passes through the ablation-resistant coating 2 and is fixedly connected to the center plate 101. A connecting pipe 401 is fixedly connected to one side of the drive shaft 4. The connecting shaft 3 is inserted into the connecting pipe 401. Limiting grooves 301 are provided at both the upper and lower ends of the drive shaft 4. Limiting parts 402 are fixedly provided at both the upper and lower ends of the connecting pipe 401. After the connecting shaft 3 is inserted into the connecting pipe 401, the two limiting parts 402 are respectively inserted into the two limiting grooves 301. The connecting pipe 401 and the connecting shaft 3 are fixedly connected by multiple bolts 403. The drive shaft 4 drives the connecting pipe 401 to rotate, so that the connecting pipe 401 drives the connecting shaft 3 to rotate through the combined action of the limiting parts 402 and multiple bolts 403. In turn, the connecting shaft 3 drives the rudder 1 to deflect. At the same time, the multiple bolts 403 are removed, so that the connecting shaft 3 is separated from the connecting pipe 401. The rudder 1 can be separated from the drive shaft 4, which is convenient for the maintenance and replacement of the rudder 1.

[0026] Working Principle: During use, when the aircraft's flight direction needs to be adjusted, the drive shaft 4 precisely connects with the connecting shaft 3 via the connecting pipe 401. With the precise guidance of the limiting part 402 and the secure fastening of the bolts 403, a stable yet flexible connection system is formed. This design allows the drive shaft 4 to effectively drive the rudder blades 1 to deflect around the connecting shaft 3, thereby achieving precise control of the aircraft's flight direction and ensuring stable flight along a predetermined trajectory. Furthermore, when the rudder blades 1 wear out after prolonged use or require repair or replacement, the operator can easily disconnect the connection between the rudder blades 1 and the drive shaft 4 by simply loosening the bolts 403, achieving rapid separation. This design not only greatly improves the convenience of maintenance but also significantly enhances maintenance efficiency, reduces aircraft downtime due to rudder blade failure, and provides strong support for the continuous and stable operation of the aircraft.

[0027] 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-resistant coating structure for a rudder blade, comprising a rudder blade (1), characterized in that: The rudder (1) includes a center plate (101) and an ablation-resistant coating (2). The ablation-resistant coating (2) includes a base material layer (201), an intermediate transition layer (202), and a surface ablation-resistant layer (203). A connecting shaft (3) is fixedly connected to one front end of the rudder (1), and a drive shaft (4) is connected to one side of the connecting shaft (3).

2. The ablation-resistant coating structure for a rudder blade according to claim 1, characterized in that: The base material layer (201) covers the outer surface of the center plate (101), the intermediate transition layer (202) covers the outer surface of the base material layer (201), and the surface ablation resistant layer (203) covers the outer surface of the intermediate transition layer (202).

3. The ablation-resistant coating structure for a rudder blade according to claim 2, characterized in that: The base material layer (201) is made of epoxy resin, the intermediate transition layer (202) is made of ceramic, and the surface ablation resistant layer (203) is made of polytetrafluoroethylene.

4. The ablation-resistant coating structure for a rudder plate according to claim 1, characterized in that: One end of the connecting shaft (3) passes through the ablation-resistant coating (2) and is fixedly connected to the center plate (101).

5. The ablation-resistant coating structure for a rudder plate according to claim 4, characterized in that: A connecting pipe (401) is fixedly connected to one side of the drive shaft (4), and the connecting shaft (3) is inserted into the connecting pipe (401).

6. The ablation-resistant coating structure for a rudder plate according to claim 5, characterized in that: The drive shaft (4) is provided with limit grooves (301) at both the upper and lower ends. The connecting pipe (401) is provided with limit parts (402) at both the upper and lower ends. After the connecting shaft (3) is inserted into the connecting pipe (401), the two limit parts (402) are respectively inserted into the two limit grooves (301).

7. The ablation-resistant coating structure for a rudder plate according to claim 6, characterized in that: The connecting pipe (401) and the connecting shaft (3) are fixedly connected by multiple bolts (403).

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