A heat-resistant load-bearing integrated air rudder thermal resistance structure

Abstract

The present application relates to a heat-resistant load-bearing integrated air rudder thermal resistance structure, belonging to the technical field of air rudders. The heat-resistant load-bearing integrated air rudder thermal resistance structure includes a rudder framework, the rudder framework includes a fork-shaped groove, reinforcing ribs arranged on the periphery of the fork-shaped groove, and restraint protrusions arranged on the reinforcing ribs, a rudder skin, the rudder skin covers the outside of the rudder framework, a rudder shaft, the rudder shaft includes a rudder shaft support seat cooperatively connected with the fork-shaped groove and a rudder shaft column section arranged on one side of the rudder shaft support seat, a heat insulation sleeve, the heat insulation ring is arranged at one end of the rudder shaft support seat close to the rudder shaft column section, a first heat insulation plate, the first heat insulation plate wraps around the periphery of the rudder shaft support seat, a second heat insulation plate, the second heat insulation plate is arranged on the periphery of the fork-shaped groove; in the present application, the second heat insulation plate can be arranged on the periphery of the fork-shaped groove to reduce the temperature of the fork-shaped groove of the rudder framework itself, block the heat radiation of the high-temperature air inside the grid ribs to the fork-shaped groove of the rudder framework, reduce the heat conduction from the rudder framework to the rudder shaft, and achieve the purpose of thermal resistance.

Description

Technical Field

[0001] The present application relates to the technical field of air rudders, and particularly to a heat-resistant load-bearing integrated air rudder thermal resistance structure. Background Art

[0002] An air rudder is a key component of an aircraft. It controls the flight attitude of the aircraft by rotating. The air rudder is installed outside the aircraft. During the high-speed flight of the aircraft, the air rudder bears a harsh thermal environment and force loads. The design focus is to meet the requirements of heat insulation and load-bearing. An air rudder generally consists of a rudder surface and a rudder shaft. During flight, the aerodynamic pressure acts on the rudder surface to provide control power; the rudder shaft is the component connecting the air rudder with the bearing and the steering gear, realizing the reliable assembly and load transfer of the air rudder. There are generally two types of solutions for the rudder surface of the air rudder: an integrated heat-resistant load-bearing rudder surface and a heat-insulating outer layer and load-bearing skeleton rudder surface. The rudder shaft is commonly made of high-temperature-resistant, high-strength, and high-modulus metal materials. The integrated heat-resistant load-bearing rudder surface has the advantages of simple structure and thin rudder surface thickness. However, the heat-resistant load-bearing materials all have high thermal conductivity, and the thermal resistance design at the connection part between the rudder surface and the rudder shaft is a difficult point. If the temperature of the rudder shaft is too high, it will affect the normal operation of the rudder shaft and even cause the bearing to jam, resulting in flight failures of the aircraft.

[0003] In summary, as an actuator for controlling the flight attitude of an aircraft, the air rudder bears harsh thermal loads and force loads. For an integrated heat-resistant load-bearing air rudder, how to achieve the thermal resistance of the air rudder is the key point and difficulty in the design. Summary of the Invention

[0004] The embodiments of the present application provide a heat-resistant load-bearing integrated air rudder thermal resistance structure to solve the problem of poor thermal resistance efficiency of the air rudder in the related art.

[0005] The embodiments of the present application provide a heat-resistant load-bearing integrated air rudder thermal resistance structure, including

[0006] a rudder skeleton, the rudder skeleton includes a fork-shaped groove, reinforcing ribs arranged on the periphery of the fork-shaped groove, and restraint protrusions arranged on the reinforcing ribs;

[0007] a rudder skin, the rudder skin covers the outside of the rudder skeleton;

[0008] a rudder shaft, the rudder shaft includes a rudder shaft support seat that is cooperatively connected with the fork-shaped groove and a rudder shaft column section arranged on one side of the rudder shaft support seat;

[0009] a heat insulation sleeve, the heat insulation ring is arranged at one end of the rudder shaft support seat close to the rudder shaft column section;

[0010] a first heat insulation plate, the first heat insulation plate wraps around the periphery of the rudder shaft support seat;

[0011] a second heat insulation plate, the second heat insulation plate is arranged on the periphery of the fork-shaped groove.

[0012] In some embodiments, mounting holes are provided in the fork-shaped groove;

[0013] Boss holes corresponding to the mounting holes are provided in the rudder shaft support.

[0014] In some embodiments, the rudder shaft support and the fork-shaped groove are connected by rivets passing through the boss holes and the mounting holes in sequence.

[0015] In some embodiments, reinforcing bosses for strengthening the rudder shaft load are further provided on the rudder shaft support.

[0016] In some embodiments, the boss holes and the reinforcing bosses have the same height.

[0017] In some embodiments, there are several such reinforcing ribs, and the several reinforcing ribs form the framework of the rudder framework.

[0018] In some embodiments, there are several such restraint protrusions, and the several restraints are respectively arranged on the reinforcing ribs on the periphery of the fork-shaped groove.

[0019] In some embodiments, there are several such second heat insulation plates, and the several second heat insulation plates are respectively arranged between every two restraint protrusions.

[0020] In some embodiments, both the first heat insulation plate and the second heat insulation plate are aerogel heat insulation materials.

[0021] In some embodiments, the heat insulation sleeve is a fiberglass heat insulation and protection sleeve.

[0022] The embodiment of the present application provides a heat-resistant load-bearing integrated air rudder thermal resistance structure. By means of the heat insulation sleeve, the heating of the rudder shaft support by external aerodynamic heat is reduced, and the heat conduction from the rudder framework to the rudder shaft is blocked, achieving the purpose of thermal resistance.

[0023] By wrapping the first heat insulation plate around the periphery of the rudder shaft support, direct contact between the rudder shaft support and the rudder framework is avoided, and the heat conduction from the rudder framework to the rudder shaft is reduced, achieving the purpose of thermal resistance.

[0024] By arranging the second heat insulation plate on the periphery of the fork-shaped groove, it is used to reduce the temperature of the fork-shaped groove of the rudder framework itself, block the thermal radiation of the high-temperature air inside the grid ribs to the fork-shaped groove of the rudder framework, reduce the heat conduction from the rudder framework to the rudder shaft, and achieve the purpose of thermal resistance. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the following will briefly introduce the drawings required for the description of the embodiments. Obviously, the drawings in the following description are only some embodiments of the present application. For those of ordinary skill in the art, without creative efforts, other drawings can also be obtained based on these drawings.

[0026] Figure 1 The structural schematic diagram provided by the embodiment of the present application;

[0027] Figure 2 The sectional structural schematic diagram provided by the embodiment of the present application;

[0028] Figure 3 The internal structural schematic diagram provided by the embodiment of the present application;

[0029] Figure 4 The first side structural schematic diagram provided by the embodiment of the present application;

[0030] Figure 5 The second side structural schematic diagram provided by the embodiment of the present application;

[0031] Figure 6 The structural schematic diagram provided for the rudder framework in the embodiment of the present application;

[0032] Figure 7 The structural schematic diagram provided for the rudder shaft in the embodiment of the present application.

[0033] 1. Rudder shaft; 1a. Rudder shaft support; 1b. Boss hole; 1c. Reinforcing boss; 1d. Rudder shaft column section; 2. Rudder framework; 2a. Fork-shaped groove; 2c. Reinforcing rib; 2b. Constraint projection; 2d. Mounting hole; 3. First heat insulation plate; 4. Heat insulation sleeve; 5. Second heat insulation plate; 6. Rivet; 7. Rudder skin. Detailed implementation manners

[0034] To make the objectives, technical solutions and advantages of the embodiments of the present application clearer, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present application. Apparently, the described embodiments are some, but not all, of the embodiments of the present application. All other embodiments obtained by those of ordinary skill in the art based on the embodiments in the present application without creative efforts shall fall within the protection scope of the present application.

[0035] The embodiment of the present application provides a heat-resistant load-bearing integrated air rudder heat resistance structure, which can solve the problem of poor heat resistance efficiency of the air rudder.

[0036] Refer to Figures 1-7 As shown, the embodiment of the present application provides a heat-resistant load-bearing integrated air rudder heat resistance structure, including

[0037] A rudder framework 2, a rudder skin 7, a rudder shaft 1, a heat insulation sleeve 4, a first heat insulation plate 3 and a second heat insulation plate 5. The rudder framework 2, the rudder skin 7 and the rudder shaft 1 are all made of high-temperature alloy steel materials with good high-temperature mechanical properties and high thermal conductivity.

[0038] Among them, the rudder frame 2 includes a fork-shaped groove 2a, reinforcing ribs 2c arranged on the periphery of the fork-shaped groove 2a, and restraint protrusions 2b arranged on the reinforcing ribs 2c. The structural strength of the rudder frame 2 is strengthened by the reinforcing ribs 2c. The restraint protrusions 2b are used to clamp the second heat insulation plate 5 and are connected to the rudder shaft 1 through the fork-shaped groove 2a. The fork-shaped groove 2a is a groove opened at the side end of the rudder frame 2, and its notch faces away from the end of the reinforcing rib 2c.

[0039] Among them, the rudder skin 7 and the rudder frame 2 form a rudder surface.

[0040] Among them, the rudder shaft 1 includes a rudder shaft support 1a that is fitted and connected to the fork-shaped groove 2a and a rudder shaft column section 1d arranged on one side of the rudder shaft support 1a. The installation matching of the rudder shaft 1 and the rudder frame 2 is realized by the cooperation of the rudder shaft support 1a of the rudder shaft 1 and the fork-shaped groove 2a of the rudder frame 2.

[0041] Among them, the heat insulation sleeve 4 is arranged at one end of the rudder shaft support 1a close to the rudder shaft column section 1d. The heat insulation sleeve 4 reduces the heating of the rudder shaft support 1a by external aerodynamic heat, blocks the heat conduction from the rudder frame 2 to the rudder shaft 1, and realizes the purpose of thermal resistance.

[0042] Among them, the first heat insulation plate 3 is wrapped around the periphery of the rudder shaft support 1a, avoiding direct contact between the rudder shaft support 1a and the rudder frame 2 after the rudder shaft support 1a is inserted into the fork-shaped groove 2a, reducing the heat conduction from the rudder frame 2 to the rudder shaft 1, and realizing the purpose of thermal resistance.

[0043] Among them, the second heat insulation plate 5 is arranged on the periphery of the fork-shaped groove 2a, used to reduce the temperature of the fork-shaped groove 2a of the rudder frame 2 itself, block the thermal radiation of the high-temperature air inside the grid ribs to the fork-shaped groove 2a of the rudder frame 2, reduce the heat conduction from the rudder frame 2 to the rudder shaft 1, and realize the purpose of thermal resistance.

[0044] In this embodiment, both the first heat insulation plate 3 and the second heat insulation plate 5 are aerogel heat insulation materials. The aerogel heat insulation materials have low heat conduction efficiency and reduce the thermal radiation of the high-temperature air inside the rudder frame 2 to the fork-shaped groove 2a of the rudder frame 2.

[0045] In this embodiment, the heat insulation sleeve 4 is a fiberglass heat insulation and protection sleeve, and the heat insulation efficiency of the molded fiberglass material meets the heat insulation requirements.

[0046] In some alternative embodiments, as shown in Figures 3-7 Refer to the figure, an installation hole 2d is opened on the fork-shaped groove 2a, and a boss hole 1b corresponding to the installation hole is opened on the rudder shaft support 1a. The rudder shaft 1 can be installed in the fork-shaped groove 2a through the boss hole 1b and the installation hole 2d.

[0047] In this embodiment, the rudder shaft support 1a and the fork-shaped groove 2a are connected by a rivet 6 passing through the boss hole 1b and the mounting hole 2d in sequence. After the rudder shaft 1 inserts the rudder shaft support 1a into the fork-shaped groove 2a, the mounting hole 2d is aligned with the boss hole 1b, and then the rivet 6 passes through the mounting hole 2d and the boss hole 1b in sequence to fix and connect them. Through the boss hole 1b, the rudder shaft 1 is in direct contact with the rudder frame 2 to achieve the purpose of load transfer, and at the same time, the contact area is ensured to be limited to reduce heat conduction.

[0048] In this embodiment, a reinforcing boss 1c also protrudes outward from the rudder shaft support 1a. The load-bearing capacity of the rudder shaft support 1a is further enhanced through the reinforcing boss 1c, the ability of force load transfer is increased, the stress of the boss hole 1b is reduced, and the areas of the reinforcing boss 1c and the boss hole 1b should be as small as possible under the condition of meeting the bearing requirements to reduce heat conduction from the parts of the reinforcing boss 1c and the boss hole 1b.

[0049] In this embodiment, the boss hole 1b and the reinforcing boss 1c have the same height to avoid the situation where the boss hole 1b or the reinforcing boss 1 cannot contact the rudder frame 2 due to different heights, resulting in a reduction in its bearing capacity.

[0050] In some alternative embodiments, as shown in Figures 2-5 There are several reinforcing ribs 2c. The several reinforcing ribs 2c are the framework of the rudder frame 2, and the structural strength of the rudder frame 2 is enhanced by the arrangement of the reinforcing ribs 2c.

[0051] In this embodiment, there are several restraint protrusions 2b. The several restraint protrusions 2b are respectively arranged on the reinforcing ribs 2c on the periphery of the fork-shaped groove 2a, so that the second heat insulation plate 5 clamped on the restraint protrusions 2b can also be arranged on the periphery of the fork-shaped groove 2a.

[0052] In this embodiment, there are several second heat insulation plates 5. The several second heat insulation plates 5 are respectively arranged between every two restraint protrusions 2b. The second heat insulation plates 5 can be clamped and placed through the restraint protrusions 2b, and finally, they are fixed again by covering with the rudder skin 7 to prevent them from falling off.

[0053] The working principle and process of this application:

[0054] When the air rudder is in use, heat is conducted through the rudder frame 2. First, the second heat insulation plate 5 is arranged on the periphery of the fork-shaped groove 2a to reduce the temperature of the fork-shaped groove 2a of the rudder frame 2 itself, block the thermal radiation of the high-temperature air inside the grid ribs to the fork-shaped groove 2a of the rudder frame 2, reduce the heat conduction from the rudder frame 2 to the rudder shaft 1, and achieve the purpose of thermal resistance. Then, the first heat insulation plate 3 is wrapped around the periphery of the rudder shaft support 1a to prevent the rudder shaft support 1a from directly contacting the rudder frame 2, reduce the heat conduction from the rudder frame 2 to the rudder shaft 1, and achieve the purpose of thermal resistance. Finally, the heat insulation sleeve 4 reduces the heating of the rudder shaft support 1a by external aerodynamic heat, blocks the heat conduction from the rudder frame 2 to the rudder shaft 1, and achieves the purpose of thermal resistance.

[0055] In the description of the present application, it should be noted that the orientation or positional relationship indicated by terms such as "upper" and "lower" is based on the orientation or positional relationship shown in the drawings. It is only for the convenience of describing the present application and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation. Therefore, it should not be construed as a limitation to the present application. Unless otherwise clearly specified and limited, the terms "installed", "connected" and "connected" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection, an electrical connection; it can be directly connected, or indirectly connected through an intermediate medium, and it can be the communication inside two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present application can be understood according to specific circumstances.

[0056] It should be noted that in the present application, relational terms such as "first" and "second" are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any actual relationship or order between these entities or operations. Moreover, the terms "comprising", "including" or any other variant thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements not only includes those elements, but also includes other elements not expressly listed, or elements inherent to such process, method, article or device. Without further limitation, the element defined by the statement "including a..." does not exclude the existence of additional identical elements in the process, method, article or device including the said element.

[0057] The above are only specific embodiments of the present application, enabling those skilled in the art to understand or implement the present application. Various modifications to these embodiments will be obvious to those skilled in the art, and the general principles defined herein can be implemented in other embodiments without departing from the spirit or scope of the present application. Therefore, the present application will not be limited to these embodiments shown herein, but rather will be accorded the widest scope consistent with the principles and novel features claimed herein.

Claims

1. A heat-resistant load-bearing integrated air rudder thermal resistance structure, characterized in that, Comprising: A rudder framework (2), said rudder framework (2) including a fork-shaped groove (2a), reinforcing ribs (2c) arranged on the periphery of the fork-shaped groove (2a), and restraint protrusions (2b) arranged on the reinforcing ribs (2c); A rudder skin (7), said rudder skin (7) covering the outside of the rudder framework (2); A rudder shaft (1), said rudder shaft (1) including a rudder shaft support (1a) matingly connected with the fork-shaped groove (2a) and a rudder shaft column section (1d) arranged on one side of the rudder shaft support (1a); A heat insulation sleeve (4), said heat insulation sleeve (4) being arranged at one end of the rudder shaft support (1a) close to the rudder shaft column section (1d); A first heat insulation plate (3), said first heat insulation plate (3) wrapping around the periphery of the rudder shaft support (1a); A second heat insulation plate (5), said second heat insulation plate (5) being arranged on the periphery of the fork-shaped groove (2a); There are several of said reinforcing ribs (2c), and the several reinforcing ribs (2c) are the framework of the rudder framework (2); There are several of said restraint protrusions (2b), and the several restraint protrusions (2b) are respectively arranged on the reinforcing ribs (2c) on the periphery of the fork-shaped groove (2a); There are several of said second heat insulation plates (5), and the several second heat insulation plates (5) are respectively arranged between every two restraint protrusions (2b).

2. The heat-resistant load-bearing integrated air rudder heat resistance structure according to claim 1, characterized in that: An installation hole (2d) is opened on the fork-shaped groove (2a); A boss hole (1b) capable of corresponding to the installation hole (2d) is opened on the rudder shaft support (1a).

3. The heat-resistant load-bearing integrated air rudder heat resistance structure according to claim 2, characterized in that: The rudder shaft support (1a) and the fork-shaped groove (2a) are connected by a rivet (6) passing through the boss hole (1b) and the installation hole (2d) in sequence.

4. The heat-resistant load-bearing integrated air rudder heat resistance structure according to claim 3, characterized in that: A reinforcing boss (1c) for strengthening the load force of the rudder shaft (1) is further arranged on the rudder shaft support (1a).

5. The heat-resistant load-bearing integrated air rudder heat resistance structure according to claim 4, characterized in that: The boss hole (1b) and the reinforcing boss (1c) have the same height.

6. The heat-resistant load-bearing integrated air rudder heat resistance structure according to claim 1, characterized in that: Both the first heat insulation plate (3) and the second heat insulation plate (5) are aerogel heat insulation materials.

7. The heat-resistant load-bearing integrated air rudder heat resistance structure according to claim 1, characterized in that: The heat insulation sleeve (4) is a fiberglass heat insulation and prevention sleeve.

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