A rudder shaft fairing cap integrated thermal protection structure based on jet active cooling

Abstract

The application relates to a rudder shaft fairing cap integrated heat protection structure based on jet active cooling, which comprises an air rudder, a fairing cap and a working medium spraying assembly; the air rudder is used for being rotatably installed on an aircraft; the fairing cap and the working medium spraying assembly are used for being installed on the aircraft; the fairing cap is internally provided with a spraying channel communicated with the working medium spraying assembly; a spraying surface is arranged on the trailing edge end surface of the fairing cap; a spraying opening of the spraying channel is arranged on the spraying surface and faces the air rudder; and the working medium spraying assembly is used for spraying working medium to the air rudder through the spraying channel. The spraying opening is arranged on the trailing edge end surface of the rudder shaft fairing cap facing the low-pressure area of the external flow field; the working medium spraying assembly is communicated with the spraying opening; the working medium flows in the spraying channel in the fairing cap and carries away heat; and finally, the working medium is sprayed into the external flow field through the spraying opening, active protection is realized, the fairing cap sprays working medium to the air rudder, high jet pressure is not needed, and the working medium spraying assembly has small burden.

Description

Technical Field

[0001] This invention relates to the technical field of high-speed aircraft, and in particular to an integrated thermal protection structure for a rudder shaft rectifier cap based on active jet cooling. Background Technology

[0002] High-speed aircraft inevitably face aerodynamic heating problems during flight caused by shock wave compression and air friction. This leads to an increase in air temperature near the aircraft walls, with heat being transferred to the aircraft walls, resulting in an increase in the structural temperature. High-speed aircraft typically control their flight attitude by manipulating aerodynamic control surfaces with servos to generate aerodynamic torque, making them extremely important functional components. Aerodynamic control surfaces protrude from the fuselage surface and face a more severe aerodynamic thermal environment than the large areas of the fuselage, especially in high-heat-flux areas such as the control shaft and leading edge, where the risk of structural deformation and failure is greater. Furthermore, precision electrical equipment such as servos must operate within a suitable ambient temperature range; otherwise, control system malfunctions are likely to occur. Therefore, effective thermal protection design is essential for aerodynamic control surfaces.

[0003] Existing active thermal protection technologies mainly rely on jet active cooling, which involves setting nozzles at the leading edge of the air rudder and then spraying the working fluid from the nozzles to form an air film in a local area of ​​the air rudder, thus isolating the high-temperature gas from the wall and achieving the purpose of thermal protection. However, in order to spray the low-temperature working fluid into the external high-speed flow field, a high jet pressure is required, which places a heavy burden on the working fluid supply system. Summary of the Invention

[0004] (a) Technical problems to be solved This invention provides an integrated thermal protection structure for the rudder shaft rectifier cap based on active jet cooling, aiming to solve the technical problem in the prior art that spraying working fluid onto the air rudder requires high jet pressure and places a heavy burden on the working fluid supply system.

[0005] (II) Technical Solution To address the above problems, the present invention provides an integrated thermal protection structure for a rudder shaft rectifier cap based on jet active cooling. The integrated thermal protection structure for a rudder shaft rectifier cap includes: an air rudder, a rectifier cap, and a working fluid spray assembly. The air rudder is used to rotate and is mounted on the aircraft; Both the rectifier cap and the working propellant spray assembly are used to be installed on the aircraft. The rectifier cap is provided with a spray channel communicating with the working propellant spray assembly, and a spray surface is provided on the rear edge end face of the rectifier cap. The spray surface is provided with spray nozzles that communicate with the spray channel. The spray nozzles face the air rudder. The working propellant spray assembly is used to spray working propellant onto the air rudder through the spray channel.

[0006] Optionally, the integrated thermal protection structure of the rudder shaft fairing cap also includes a linkage component. The fairing cap is rotatably mounted on the aircraft, and the linkage component is used to connect the fairing cap and the air rudder so that the fairing cap and the air rudder rotate synchronously.

[0007] Optionally, the linkage assembly includes a first gear, a second gear, and an intermediate gear, all rotatably mounted on the aircraft. The first gear is fixedly connected to the fairing cap, the second gear is fixedly connected to the aerodynamic rudder, and the intermediate gear is located between the first gear and the second gear, and meshes with the first gear and the second gear.

[0008] Optionally, the first gear, the second gear, and the intermediate gear have the same diameter and the same number of teeth.

[0009] Optionally, the linkage assembly includes a first gear, a second gear, a first link, and a second link, all rotatably mounted on the aircraft; The first gear is fixedly connected to the rectifier cap, the second gear is fixedly connected to the air rudder, one end of the first connecting rod is hinged to the first gear, the other end of the first connecting rod is hinged to the second gear, one end of the second connecting rod is hinged to the first gear, the second connecting rod is hinged to the second gear, the first connecting rod is located on one side of the line connecting the center of the first gear and the center of the second gear, and the second connecting rod is located on the other side of the line connecting the center of the first gear and the center of the second gear.

[0010] Optionally, the working fluid spraying assembly includes a working fluid tank, spraying pipes, and a working fluid pump; The working medium tank is used to store the working medium, and the working medium tank is connected to the spray channel through the spray pipe, and the working medium pump is installed on the spray pipe.

[0011] Optionally, the spray channel includes a main channel and multiple branch channels, and the spray surface is provided with spray nozzles that correspond one-to-one with the branch channels, and the branch channels are connected to the corresponding spray nozzles; The first end of the main channel is located at the center of the bottom surface of the rectifier cap, the second end of the main channel is connected to the main channel, and the spray pipe is connected to the first end of the main channel.

[0012] Optionally, the spray nozzle may be circular, triangular, quadrilateral, or elliptical in shape.

[0013] Optionally, the rectifier cap is in the shape of a triangular prism.

[0014] (III) Beneficial Effects The present invention has a spray nozzle on the rear edge end face of the rectifier cap facing the low-pressure area of ​​the external flow field. The working fluid spraying component is connected to the spray nozzle. The working fluid flows in the spraying channel inside the rectifier cap and carries away heat. Finally, it is sprayed into the external flow field through the spray nozzle to achieve active protection. This allows the rectifier cap to spray the working fluid onto the air rudder without the need for high spray pressure, and the working fluid spraying component is less burdened. Attached Figure Description

[0015] Figure 1 This is a schematic diagram of the integrated thermal protection structure of the rudder shaft rectifier cap of the present invention; Figure 2 This is a top view of the integrated thermal protection structure of the rudder shaft rectifier cap of the present invention; Figure 3 This is a schematic diagram of the structure of a linkage component in this invention; Figure 4 This is a schematic diagram of another linkage component in the present invention.

[0016] [Explanation of Labels in the Attached Image] 1: Air rudder; 2: rectifier cap; 21: Spray surface; 22: Spray channel; 23: Main channel; 24: Branch channel; 3: Working fluid spray assembly; 31: Working fluid tank; 32: Spray pipe; 33: Working fluid pump; 4: Linkage assembly; 41: First gear; 42: Second gear; 43: Intermediate gear; 44: First connecting rod; 45: Second connecting rod. Detailed Implementation

[0017] To better explain and facilitate understanding of the present invention, the present invention will be described in detail below with reference to the accompanying drawings and specific embodiments.

[0018] It should be noted that all directional indications (such as up, down, left, right, front, back, etc.) in the embodiments of the present invention are only used to explain the relative positional relationship and movement of each component in a certain specific posture (as shown in the figure). If the specific posture changes, the directional indication will also change accordingly.

[0019] Furthermore, in this invention, descriptions involving "first," "second," etc., are for descriptive purposes only and should not be construed as indicating or implying their relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this invention, "a plurality of" means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0020] In this invention, unless otherwise explicitly specified and limited, the terms "connection," "fixed," etc., should be interpreted broadly. For example, "fixed" can mean a fixed connection, a detachable connection, or an integral part; it can mean a mechanical connection or an electrical connection; it can mean a direct connection or an indirect connection through an intermediate medium; it can mean the internal communication of two components or the interaction between two components, unless otherwise explicitly limited. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0021] This invention provides an integrated thermal protection structure for a rudder shaft rectifier cap 2 based on jet active cooling. The integrated thermal protection structure for the rudder shaft rectifier cap 2 includes: an air rudder 1, a rectifier cap 2, and a working fluid spray assembly 3. The air rudder 1 is rotatably mounted on an aircraft. Both the rectifier cap 2 and the working fluid spray assembly 3 are mounted on the aircraft. The rectifier cap 2 is provided with a spray channel 22 that communicates with the working fluid spray assembly 3. A spray surface 21 is provided on the rear edge end face of the rectifier cap 2. The spray surface 21 is provided with spray nozzles that communicate with the spray channel 22. The spray nozzles face the air rudder 1. The working fluid spray assembly 3 is used to spray working fluid onto the air rudder 1 through the spray channel 22.

[0022] The trailing edge of the fairing cap 2 refers to the end face of the aircraft facing away from the high-speed airflow during flight. This invention provides a spray nozzle on the trailing edge of the fairing cap 2 facing the low-pressure area of ​​the external flow field. The working fluid spray assembly 3 is connected to the spray nozzle. The working fluid flows in the spray channel 22 within the fairing cap 2, carrying away heat, and is finally sprayed into the external flow field through the spray nozzle, achieving active protection. This allows the fairing cap 2 to spray the working fluid onto the air rudder 1 without requiring high jet pressure, thus reducing the burden on the working fluid spray assembly 3. Furthermore, since the fairing cap 2 is located at the leading edge of the air rudder 1, it shares some of the aerodynamic heating heat flow with the air rudder 1 and the rudder shaft (the part of the air rudder 1 that is rotatably mounted on the aircraft), thereby achieving passive protection. In summary, this invention can cool the fairing cap 2 while effectively controlling the temperature of high-heat-flow areas such as the rudder shaft and air rudder 1, solving problems such as thermal protection and thermal deformation in high-heat-flow areas of the rudder system under high-speed, long-endurance flight conditions.

[0023] Furthermore, the integrated thermal protection structure of the rudder shaft rectifier cap 2 also includes a linkage component 4. The rectifier cap 2 is rotatably mounted on the aircraft, and the linkage component 4 is used to connect the rectifier cap 2 and the air rudder 1 so that the rectifier cap 2 and the air rudder 1 rotate synchronously. When the aircraft is in flight, the air rudder 1 needs to rotate. This invention sets up the linkage component 4 to control the synchronous rotation of the rectifier cap 2 and the air rudder 1. This design ensures that no matter what deflection state the air rudder 1 is in, the working fluid sprayed from the nozzle can always effectively cover the leading edge area of ​​the rudder, achieving continuous and directional cooling of the high heat flux area, and improving the accuracy and reliability of thermal protection.

[0024] In one embodiment, the linkage assembly 4 includes a first gear 41, a second gear 42, and an intermediate gear 43, all rotatably mounted on the aircraft. The first gear 41 is fixedly connected to the fairing cap 2, the second gear 42 is fixedly connected to the air rudder 1, and the intermediate gear 43 is located between the first gear 41 and the second gear 42, meshing with both the first gear 41 and the second gear 42. In this scheme, the sequentially meshing first gear 41, intermediate gear 43, and second gear 42 ensure that the first gear 41 and the second gear 42 rotate in the same direction. Furthermore, the first gear 41 and the second gear 42 are connected to the fairing cap 2 and the air rudder 1, respectively. This ensures that the spray surface 21 on the fairing cap 2 always faces the air rudder 1, guaranteeing that the working fluid ejected from the spray nozzles effectively covers the leading edge area of ​​the rudder. Additionally, the first gear 41, second gear 42, and intermediate gear 43 have equal diameters and the same number of teeth. Setting them to have the same diameter and number of teeth ensures that the first gear 41 and the second gear 42 rotate at the same angle.

[0025] In another embodiment, the linkage assembly 4 includes a first gear 41, a second gear 42, a first connecting rod 44, and a second connecting rod 45, all rotatably mounted on the aircraft. The first gear 41 is fixedly connected to the fairing cap 2, and the second gear 42 is fixedly connected to the aerodynamic control 1. One end of the first connecting rod 44 is hinged to the first gear 41, and the other end is hinged to the second gear 42. One end of the second connecting rod 45 is hinged to the first gear 41, and the second connecting rod 45 is hinged to the second gear 42. The first connecting rod 44 is located on one side of the line connecting the center of the first gear 41 and the center of the second gear 42, and the second connecting rod 45 is located on the other side of the line connecting the center of the first gear 41 and the center of the second gear 42. In this embodiment, the first connecting rod 44 and the second connecting rod 45 are used to connect the first gear 41 and the second gear 42, achieving synchronous rotation of the first gear 41 and the second gear 42.

[0026] Furthermore, the working fluid spray assembly 3 includes a working fluid tank 31, a spray pipe 32, and a working fluid pump 33. The working fluid tank 31 stores the working fluid and is connected to the spray channel 22 via the spray pipe 32. The working fluid pump 33 is installed on the spray pipe 32. The working fluid pump 33 provides the flow power for the working fluid, pumping the cooling working fluid from the working fluid tank 31 to the external flow field. It can also adjust the working fluid flow rate as needed to achieve different thermal protection effects. The working fluid is a substance that can carry away heat from the heated parts. After fully absorbing heat within the rectifier cap 2, it ultimately forms an air film from the trailing edge of the rectifier cap 2, at the leading edge of the air rudder 1 and in the rudder shaft area, separating the wall surface from the high-temperature gas.

[0027] Furthermore, the spray channel 22 includes a main channel 23 and multiple branch channels 24. Spray nozzles corresponding to the branch channels 24 are provided on the spray surface 21. Each branch channel 24 is connected to its corresponding spray nozzle. The first end of the main channel 23 is located at the center of the bottom surface of the rectifier cap 2, and the second end of the main channel 23 is connected to it. The spray pipe 32 is connected to the first end of the main channel 23. The fact that the first end of the main channel 23 is located at the center of the bottom surface of the rectifier cap 2 ensures that one end of the main channel 23 coincides with the rotation center of the rectifier cap 2, and that the rotation of the rectifier cap 2 will not affect the connection between the working fluid spray assembly 3 and the spray channel 22.

[0028] Multiple branch channels 24 are provided on the rectifier cap 2, which increases the contact area between the working fluid and the rectifier cap 2 and improves the cooling effect of the working fluid on the rectifier cap 2. In addition, multiple spray nozzles are provided on the spray surface 21 to increase the spray range and improve the spraying effect on the air rudder 1.

[0029] Finally, the spray nozzle can be circular, triangular, quadrilateral, or elliptical. The rectifier cap 2 is a triangular prism. Its length and wedge angle are determined by considering the rudder shaft clearance height and the thermal environment.

[0030] It should be understood that the above description of specific embodiments of the present invention is only for illustrating the technical approach and features of the present invention, and is intended to enable those skilled in the art to understand the content of the present invention and implement it accordingly. However, the present invention is not limited to the specific embodiments described above. All changes or modifications made within the scope of the claims of the present invention should be covered within the protection scope of the present invention.

Claims

1. An integrated thermal protection structure for a rudder shaft rectifier cap based on jet active cooling, characterized in that, The integrated thermal protection structure of the rudder shaft rectifier cap includes: an air rudder (1), a rectifier cap (2), and a working fluid spray assembly (3). The air rudder (1) is used to rotate on the aircraft; The rectifier cap (2) and the working propellant spray assembly (3) are both used to be installed on the aircraft. The rectifier cap (2) is provided with a spray channel (22) that communicates with the working propellant spray assembly (3). The rectifier cap (2) is provided with a spray surface (21) on its rear edge end face. The spray surface (21) is provided with a spray nozzle that communicates with the spray channel (22). The spray nozzle faces the air rudder (1). The working propellant spray assembly (3) is used to spray working propellant onto the air rudder (1) through the spray channel (22).

2. The integrated thermal protection structure for the rudder shaft rectifier cap with active jet cooling as described in claim 1, characterized in that, The integrated thermal protection structure of the rudder shaft rectifier cap (2) also includes a linkage component (4). The rectifier cap (2) is rotatably mounted on the aircraft. The linkage component (4) is used to connect the rectifier cap (2) and the air rudder (1) so that the rectifier cap (2) and the air rudder (1) rotate synchronously.

3. The integrated thermal protection structure for the rudder shaft rectifier cap with active jet cooling as described in claim 2, characterized in that, The linkage component (4) includes a first gear (41), a second gear (42), and an intermediate gear (43) that are rotatably mounted on the aircraft. The first gear (41) is fixedly connected to the fairing cap (2), the second gear (42) is fixedly connected to the air rudder (1), and the intermediate gear (43) is located between the first gear (41) and the second gear (42), and the intermediate gear (43) meshes with the first gear (41) and the second gear (42).

4. The integrated thermal protection structure for the rudder shaft rectifier cap with active jet cooling as described in claim 3, characterized in that, The first gear (41), the second gear (42), and the intermediate gear (43) have the same diameter and the same number of teeth.

5. The integrated thermal protection structure for the rudder shaft rectifier cap with active jet cooling as described in claim 2, characterized in that, The linkage assembly (4) includes a first gear (41), a second gear (42), a first link (44), and a second link (45) that are rotatably mounted on the aircraft. The first gear (41) is fixedly connected to the rectifier cap (2), the second gear (42) is fixedly connected to the air rudder (1), one end of the first connecting rod (44) is hinged to the first gear (41), the other end of the first connecting rod (44) is hinged to the second gear (42), one end of the second connecting rod (45) is hinged to the first gear (41), the second connecting rod (45) is hinged to the second gear (42), the first connecting rod (44) is located on one side of the line connecting the center of the first gear (41) and the center of the second gear (42), and the second connecting rod (45) is located on the other side of the line connecting the center of the first gear (41) and the center of the second gear (42).

6. The integrated thermal protection structure for the rudder shaft rectifier cap with active jet cooling as described in any one of claims 1-5, characterized in that, The working fluid spray assembly (3) includes a working fluid tank (31), a spray pipe (32), and a working fluid pump (33). The working medium tank (31) is used to store the working medium, and the working medium tank (31) is connected to the spray channel (22) through the spray pipe (32). The working medium pump (33) is installed on the spray pipe (32).

7. The integrated thermal protection structure for the rudder shaft rectifier cap with active jet cooling as described in claim 6, characterized in that, The spray channel (22) includes a main channel (23) and multiple branch channels (24). The spray surface (21) is provided with spray nozzles that correspond one-to-one with the branch channels (24). The branch channels (24) are connected to the corresponding spray nozzles. The first end of the main channel (23) is located at the center of the bottom surface of the rectifier cap (2), the second end of the main channel (23) is connected to the main channel (23), and the spray pipe (32) is connected to the first end of the main channel (23).

8. The integrated thermal protection structure for the rudder shaft rectifier cap with active jet cooling as described in any one of claims 1-5, characterized in that, The spray nozzle can be circular, triangular, quadrilateral, or elliptical in shape.

9. The integrated thermal protection structure for the rudder shaft rectifier cap with active jet cooling as described in any one of claims 1-5, characterized in that, The rectifier cap (2) is a triangular prism.

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