Multifunctional rudder wing structure

Abstract

This invention discloses a multifunctional rudder structure, wherein the rudder consists of an inner core, an outer layer, and a sandwich layer, achieving multiple functions such as lightweight, high temperature resistance, oil storage, and high load-bearing capacity. The rudder structure of this invention comprises four components: a closed inner core, a thermally insulated sandwich layer, a thermal insulation column, and a high-temperature resistant outer skin; the overall structural form is a frame, skin, and thermal insulation column. The entire rudder not only possesses good rigidity and strength but also solves the heat transfer problem between the inner and outer layers, meets the low-temperature requirements for internal oil storage, and effectively reduces the overall structural weight.

Description

Technical Field

[0001] This invention belongs to the field of aerospace and marine manufacturing technology, and particularly relates to a multifunctional rudder structure. This multifunctional rudder structure is used to manufacture products with multiple characteristics such as lightweight, fuel storage, heat insulation, high strength, and high temperature resistance, especially achieving complete heat insulation of the inner core. In some cases, the combination of different functions and the selection and specifications of materials for the characteristic structure are related to obtaining a lightweight characteristic structure. Background Technology

[0002] The fuselage and control wings of next-generation high-speed aircraft not only require high structural strength but also multifunctional requirements such as lightweight design, fuel storage, heat resistance, and thermal insulation. Employing lightweight, high-strength structural materials and lightweight structural design is one of the main ways to achieve high structural strength and lightweight control wings. Simultaneously, fully utilizing the control wing space for fuel storage can further reduce aircraft weight and improve space utilization. Fuel storage in control wings also contributes to improved flight stability. This presents significant challenges to the lightweight, heat-resistant, and thermally insulated structural design and manufacturing of fuel-storage control wings.

[0003] Currently, when designing the rudder or main fuselage structure of high-speed aircraft, the temperature of internal fuel and electronic components must be considered. Generally, the overall structure of the rudder is made of high-temperature alloys and other high-temperature resistant materials. The overall high temperature makes it impossible to store fuel internally, completely sacrificing the effective space inside the large rudder. Alternatively, lightweight metal is used to store fuel internally, and thermal protection is provided externally through heat-insulating tiles. By sacrificing the high precision requirements of the outer aerodynamic surface, typical structures such as the stainless steel rocket tanks used in SPACE-X and the space shuttle fuselage mainly result in excessive overall weight, reducing the effective payload and space.

[0004] Considering these challenges, it is essential to make extreme innovations in the structural design and manufacturing of future aircraft within the limited space, especially in terms of the operational requirements of aircraft rudders with high external temperatures and internal room temperature or even low temperatures. Summary of the Invention

[0005] The technical problem solved by this application is to overcome the shortcomings of the prior art and provide a multifunctional rudder structure. By systematically combining the advantages of various materials and structural characteristics, a composite sandwich design is formed. Different layers of materials meet different functional requirements. At the same time, the different components are rationally integrated into a structure to achieve lightweight, heat-resistant and heat-insulating structural design and manufacturing of the rudder.

[0006] The technical solution provided in this application is as follows:

[0007] A multi-functional rudder structure includes an outer skin assembly, a heat insulation interlayer, an inner core assembly, and heat insulation columns. The inner core assembly is located inside the outer skin assembly and is used to contain a liquid medium. The inner core assembly is provided with multiple mounting holes. The heat insulation columns pass through the mounting holes, and both ends of the heat insulation columns are fixedly connected to the outer skin assembly, so that the inner core assembly is fixed to the inside of the outer skin assembly through the heat insulation columns. The heat insulation interlayer is fixed between the inner core assembly and the outer skin assembly and is used to insulate the inner core assembly and the outer skin assembly.

[0008] In one possible implementation, the outer skin assembly includes an upper skin, a lower skin, and a skeleton, with the upper and lower skins fixed to the skeleton to form a sealed structure.

[0009] In one possible implementation, the inner core assembly is made of a lightweight alloy material; the outer skin assembly is made of a high-temperature resistant lightweight material; the thermal insulation layer is a strong thermal insulation material that will not be damaged by the thermal expansion and contraction deformation of the outer skin assembly during high-temperature and room-temperature cyclic temperature deformation; the thermal insulation layer is made of aerogel, hydrogel, or thermal insulation adhesive.

[0010] In one possible implementation, the surface of the outer skin assembly is a rudder plane, the angle between the heat insulation column and the rudder plane is 0-90°, and the mounting hole matches the tilt angle of the heat insulation column.

[0011] In one implementation, the insulating column includes an inner core and an insulating component fitted over the inner core, the insulating component being located within a mounting hole to separate the inner core and the inner core component, thereby preventing the formation of a thermal bridge between the inner core and the inner core component.

[0012] In one possible implementation, the insulation component is an insulation layer, the inner core of the column is fixed to the outer skin assembly, and the insulation layer is an insulation material.

[0013] In one possible implementation, the thermal insulation component includes an inner connecting layer, a thermal insulation layer, and an outer connecting layer arranged sequentially from the inside to the outside. Both the inner connecting layer and the outer connecting layer are cylindrical. The thermal insulation layer is fixed between the inner connecting layer and the outer connecting layer. The inner connecting layer is fixedly connected to the inner core of the cylinder, and the outer connecting layer is fixedly connected to the inner core component.

[0014] In one possible implementation, both the inner and outer connecting layers are cylindrical with varying diameters, where the outer diameters of the top and bottom of the inner connecting layer increase, and the inner diameters of the top and bottom of the outer connecting layer decrease.

[0015] In one possible implementation, the method of forming the thermal insulation component includes: sequentially pressing a plurality of annular thermal insulation rings between an inner connecting layer and an outer connecting layer, thereby forming an integral thermal insulation layer with the inner connecting layer and the outer connecting layer.

[0016] In summary, this application includes at least the following beneficial technical effects:

[0017] This multi-functional rudder structure can ensure that the inner core components do not deform due to thermal effects under complex high-temperature service conditions, thereby effectively maintaining the airtightness of the inner core tank structure and preventing leakage; at the same time, it can better meet the strength and rigidity requirements of the inner core in the overall structure, maintaining excellent overall performance.

[0018] This multi-functional rudder structure can effectively achieve complete isolation between the low temperature of the inner core and the high temperature of the outer skin, eliminating the need for additional thermal protection measures such as external heat insulation tiles, thereby achieving good oil storage in the inner core. Attached Figure Description

[0019] Figure 1 This is a schematic diagram of a typical structure of a multi-functional rudder provided in one embodiment;

[0020] Figure 2 This is a schematic diagram of a rudder structure with a circular inner core provided in one embodiment;

[0021] Figure 3 This is a schematic diagram of a heat insulation column provided in one embodiment;

[0022] Figure 4 This is a schematic diagram of another type of insulation column provided in one embodiment;

[0023] Figure 5 This is a schematic diagram of the insulation column at different tilt angles.

[0024] The reference numerals are as follows: 1. Outer skin assembly; 2. Thermal insulation layer; 3. Inner core assembly; 31. Mounting hole; 4. Thermal insulation column; 41. Core inside the column; 42. Thermal insulation assembly; 421. Inner connecting layer; 422. Thermal insulation layer; 423. Outer connecting layer. Detailed Implementation

[0025] The term “exemplary” as used herein means “serving as an example, embodiment, or illustration.” Any embodiment illustrated herein as “exemplary” is not necessarily to be construed as superior to or better than other embodiments. Although various aspects of embodiments are shown in the accompanying drawings, the drawings are not necessarily drawn to scale unless specifically indicated otherwise.

[0026] This embodiment presents a multi-functional rudder structure, such as Figure 1As shown, the structure includes an outer skin assembly 1, a thermal insulation layer 2, an inner core assembly 3, and thermal insulation columns 4. The inner core assembly 3 is located inside the outer skin assembly 1 and has multiple mounting holes 31. The thermal insulation columns 4 pass through the mounting holes 31, and both ends of the thermal insulation columns 4 are fixedly connected to the outer skin assembly 1. Thus, the inner core assembly 3 is fixed to the interior of the outer skin assembly 1 via the thermal insulation columns 4. The thermal insulation layer 2 is fixed between the inner core assembly 3 and the outer skin assembly 1. The thermal insulation layer 2 is used to insulate the space between the inner core assembly 3 and the outer skin assembly 1, ensuring that the temperature of the liquid medium inside the inner core assembly 3 does not exceed 120°C, thus preventing the liquid medium in the inner core assembly 3 from vaporizing. This type of structure is applicable to wing and overall aircraft structural design.

[0027] The inner core assembly 3 consists of an upper skin and a lower skin, forming a closed fuel tank with an interface. The inner core assembly 3 is made of lightweight alloy materials such as aluminum alloy, magnesium alloy, and aluminum alloy composites. It can hold liquid media such as kerosene, fuel oil, liquid oxygen, and liquid hydrogen. The volume of the liquid media is adjusted according to the specifications of the outer skin assembly 1 and the thickness of the thermal insulation layer 2. An interface for transporting liquid media is formed through the connection area between the control wing and the fuselage. The projected shape of the inner core assembly 3 can be a reduced outline of the outer skin, a regular outline, or an irregular outline.

[0028] The outer skin assembly 1 consists of an upper skin, a lower skin, and a frame structure, forming a sealed structure. The frame primarily maintains the strength and rigidity of the entire rudder, and the upper and lower skins are fixed to the frame. The outer skin assembly 1 is made of high-temperature resistant lightweight materials such as high-temperature titanium alloy, high-temperature alloy, and titanium-aluminum intermetallic compound, possessing excellent properties such as high-temperature strength, high-temperature toughness, and weldability. The overall size of the outer contour is set according to the overall aircraft design requirements.

[0029] The thermal insulation layer 2 is placed between the inner core component 3 and the outer skin, and the three are tightly bonded together at room temperature. The thermal insulation layer 2 is attached to the outer surface of the inner core component 3. The thermal insulation layer 2 is made of thermal insulation materials such as aerogel, hydrogel, and thermal insulation adhesive, and also has a certain strength. When subjected to temperature deformation due to high temperature and room temperature cycling, the material will not be damaged due to the thermal expansion and contraction deformation of the outer skin component 1 or the pressure during service.

[0030] The heat insulation pillars 4 are mainly used to stabilize the inner core assembly 3 within the rudder wing. The surface of the outer skin assembly 1 is the rudder wing plane. The relative position and number of the heat insulation pillars 4 within the rudder wing are adjusted according to the force analysis of the rudder wing plane during service. They are positioned either perpendicular to the rudder wing plane or at a certain angle to it. The angle between the heat insulation pillars 4 and the rudder wing plane ranges from 0-90°, and different heat insulation pillars 4 have different tilt directions. This allows the inner core assembly 3 to be stably fixed within the outer skin assembly 1. The specific tilt angle is determined based on the service condition. For example, when the rudder wing is horizontal, it mainly experiences greater forward and backward inertial forces; in this case, the angle between the heat insulation pillars and the rudder wing plane is 45°. Figure 5 As shown.

[0031] In this embodiment, two implementation forms of the heat insulation column 4 are provided. The first implementation form of the heat insulation column 4 is as follows: Figure 3 As shown, the heat insulation column 4 includes an inner core 41 and a heat insulation component 42 sleeved on the inner core 41. The heat insulation component 42 is a heat insulation layer 422. The inner core 4 is fixed to the outer skin component 1. When connected to the outer component, through welding can be used to ensure that the outer surface of the outer skin component 1 is a whole, thereby increasing the overall thermal protection. The heat insulation layer 422 is a heat insulation material such as hydrogel or aerogel. The heat insulation layer 422 is located inside the mounting hole 31 to separate the inner core 41 and the inner core component 3, thereby avoiding the formation of a thermal bridge between the inner core 41 and the inner core component 3.

[0032] The second type of insulation column 4 is implemented as follows: Figure 4 As shown, the thermal insulation component 42 includes an inner connecting layer 421, a thermal insulation layer 422, and an outer connecting layer 423 arranged sequentially from the inside to the outside. Both the inner connecting layer 421 and the outer connecting layer 423 are cylindrical. The outer diameter of the top and bottom of the inner connecting layer 421 increases, while the inner diameter of the top and bottom of the outer connecting layer 423 decreases. When forming the thermal insulation column 4, the thermal insulation component 42 is formed first, then the thermal insulation component 42 is fitted onto the outside of the inner core 41 of the column, and finally the thermal insulation component 42 is connected to the inner core 41 and the inner core component 3 of the column, respectively. The forming of the thermal insulation component 42 includes pressing multiple annular thermal insulation rings sequentially between the inner connecting layer 421 and the outer connecting layer 423 to finally obtain the thermal insulation component 42. The inner connecting layer 421 is connected to the inner core 41 of the column. The connection between the inner connecting layer 421 and the inner core 41 of the column is achieved by welding to increase the strength of the connection. The outer connecting layer 423 is connected to the inner core assembly 3. The connection between the outer connecting layer 423 and the inner core assembly 3 is achieved by welding to increase the strength of the connection.

[0033] When assembling the rudder structure, the following assembly method is adopted to address the inconsistent tilt direction of the inner core 41 of the column: the inner core 41 of the column passes through the inner core assembly 3, the heat insulation assembly 42 is sleeved on the outside of the inner core 41 of the column, and the heat insulation assembly 42 is located inside the mounting hole 31. Then, the heat insulation layer 2 is laid above and below the inner core assembly 3. Finally, the bottom part and the top part of the outer skin assembly 1 are formed on the outside of the heat insulation layer 2. Finally, the two ends of the inner core 41 of the column are welded and fixed to the outer skin assembly 1 by through welding.

[0034] When assembling the rudder structure, for cases where the tilt direction of the inner core 41 of the cylinder is consistent, the following assembly method can also be adopted: First, form the bottom part of the outer skin assembly 1, then weld the bottom of the inner core 41 of the cylinder to the bottom of the bottom part of the outer skin assembly 1, and then lay the heat insulation layer 2 upwards on the bottom part of the outer skin assembly 1. Then, fit the inner core assembly 3 from top to bottom onto the outside of the inner core 41 of the cylinder, and fit the heat insulation assembly 42 onto the outside of the inner core 41 of the cylinder, with the heat insulation assembly 42 located inside the mounting hole 31. After that, continue to lay the heat insulation layer 2 upwards above the inner core assembly 3. Finally, form the top part of the outer skin assembly 1 and weld the top part of the outer skin assembly 1 to the inner core 41 of the cylinder.

[0035] The height of the insulation component 42 is equal to the thickness of the inner core component 3, facilitating the connection between the insulation column 4 and the inner core component 3. The insulation interlayer 2 only needs to have insertion holes to mate with the inner core 41 of the column, without the need for forming steps. The resulting insulation interlayer 2 fits snugly against the end of the insulation component 42, avoiding thermal bridges. The cross-section of the insulation column 4 can be designed as a regular cross-section such as square, triangle, pentagon, circle, or ellipse, or an irregular closed contour shape, depending on the actual process characteristics. The insulation column 4 can also be designed as a straight column, cone, curved, bulging, or lantern shape, depending on the stress characteristics.

[0036] The outer skin assembly 1 is made of TiAl alloy, the thermal insulation layer 2 is made of hydrogel, the inner core assembly 3 is made of AlLi alloy, the cylindrical inner core 41 is made of TiAl alloy, and the thermal insulation layer 422 is made of hydrogel. The outer skin assembly 1 uses a high-temperature resistant TiAl intermetallic compound alloy to meet the requirements of a high-temperature wind-driven surface, the thermal insulation layer 2 meets the requirements of a high thermal insulation temperature, and the inner core assembly 3 realizes the storage tank function.

[0037] A specific embodiment of the present invention provides a multi-functional rudder structure. Taking a rudder component of a large aircraft as an example, its shape is as follows: Figure 1 As shown, the outer skin assembly 1 (made of TiAl intermetallic compound) has a plate wall thickness of 1.2mm, an overall trapezoidal projected surface, a pentagonal cross-section in the middle of the rudder wing, and a temperature resistance up to 640℃. An example of a heat insulation column 4 is provided in the embodiment. Figure 3As shown, the insulation layer 422 of the insulation column 4 can be well assembled with the sandwich insulation layer 422. This method has an overall density 20% lower than the existing structural method, with an overall structural density of up to 1.4 g / m3, solving the problem that the existing rudder cannot meet the fuel carrying requirements.

[0038] In another embodiment, a multi-functional rudder structure is described. Figure 2 This is a schematic diagram of a circular cross-section rudder wing structure for the inner core component 3 provided in this embodiment of the invention. Using the schematic diagram of the circular inner core rudder wing structure of this embodiment, the prepared multifunctional rudder wing can meet the requirements of lightweight, oil storage, high temperature resistance, and heat insulation.

[0039] In some embodiments, the insulation columns 4 can be positioned arbitrarily, such as in a single row, double row, random arrangement, or topology optimization.

[0040] This invention discloses a multi-functional rudder structure that sequentially stacks various materials with different properties to efficiently meet the different functional requirements of different positions. The internal layer stores oil in a low-temperature environment, the middle layer provides thermal insulation, and the outer layer is heat-resistant. The inner core and outer layer have no contact, and are completely separated into independent components by the middle layer and the thermal insulation pillar 4. During service, the force exerted by the inner core component 3 is transmitted to the outer skin component 1 through the thermal insulation pillar 4, keeping the inner core component 3 in a mechanically stable state. Simultaneously, because the thermal insulation layer 422 adheres to the inner core, and because the thermal insulation material is mostly lightweight thermal insulation materials such as aerogel and thermal adhesive, the inner core forms a thermally insulated space. This provides some insulation for the internal oil temperature or other fuel, preventing the temperature from becoming too high and increasing internal pressure, or even posing a risk of leakage.

[0041] The present application has been described in detail above with reference to specific embodiments and exemplary examples; however, these descriptions should not be construed as limiting the present application. Those skilled in the art will understand that various equivalent substitutions, modifications, or improvements can be made to the technical solutions and implementation methods of the present application without departing from the spirit and scope of the present application, and all such modifications and improvements fall within the scope of the present application. The scope of protection of the present application is determined by the appended claims.

[0042] The contents not described in detail in this application specification are common knowledge to those skilled in the art.

Claims

1. A multi-function vane wing structure, characterized by: The assembly includes an outer skin assembly (1), a heat insulation interlayer (2), an inner core assembly (3), and a heat insulation column (4). The inner core assembly (3) is located inside the outer skin assembly (1) and is used to hold liquid media. The inner core assembly (3) is provided with multiple mounting holes (31). The heat insulation column (4) passes through the mounting holes (31) and both ends of the heat insulation column (4) are fixedly connected to the outer skin assembly (1) so that the inner core assembly (3) is fixed to the inside of the outer skin assembly (1) through the heat insulation column (4). The heat insulation interlayer (2) is fixed between the inner core assembly (3) and the outer skin assembly (1) and is used to provide heat insulation between the inner core assembly (3) and the outer skin assembly (1). The heat insulation column (4) includes a core (41) and a heat insulation component (42) sleeved outside the core (41). The heat insulation component (42) is located inside the mounting hole (31) to separate the core (41) and the core component (3) and avoid the formation of a thermal bridge between the core (41) and the core component (3). The surface of the outer skin assembly (1) is a rudder plane, the angle between the heat insulation column (4) and the rudder plane is 0-90°, and the mounting hole (31) matches the tilt angle of the heat insulation column (4).

2. A multi-function vane wing structure according to claim 1, characterized by: The outer skin assembly (1) includes an upper skin, a lower skin, and a skeleton. The upper skin and the lower skin are fixed to the skeleton to form a sealed structure.

3. The multi-functionailty wing structure according to claim 1, wherein: The inner core component (3) is made of lightweight alloy material; the outer skin component (1) is made of high-temperature resistant lightweight material; the heat insulation layer (2) is a strong heat insulation material, and the heat insulation layer (2) will not be damaged due to the thermal expansion and contraction deformation of the outer skin component (1) when the temperature is cyclically deformed at high temperature and room temperature; the heat insulation layer (2) is made of aerogel, hydrogel or heat insulation adhesive.

4. The multi-functionailty wing structure according to claim 1, wherein: The heat insulation component (42) is a heat insulation layer (422), the inner core (41) of the column is fixed to the outer skin component (1), and the heat insulation layer (422) is a heat insulation material.

5. The multi-functionailty wing structure according to claim 1, wherein: The heat insulation component (42) includes an inner connecting layer (421), a heat insulation layer (422), and an outer connecting layer (423) arranged sequentially from the inside to the outside. Both the inner connecting layer (421) and the outer connecting layer (423) are cylindrical. The heat insulation layer (422) is fixed between the inner connecting layer (421) and the outer connecting layer (423). The inner connecting layer (421) is fixedly connected to the inner core (41) of the cylinder, and the outer connecting layer (423) is fixedly connected to the inner core component (3).

6. A multi-function vane wing structure according to claim 5, wherein: Both the inner connecting layer (421) and the outer connecting layer (423) are cylindrical with varying diameters. The outer diameter of the top and bottom of the inner connecting layer (421) increases, while the inner diameter of the top and bottom of the outer connecting layer (423) decreases.

7. A multi-function vane wing structure according to claim 5, wherein: The molding method of the heat insulation component (42) includes: pressing multiple annular heat insulation rings sequentially between the inner connecting layer (421) and the outer connecting layer (423), and the resulting heat insulation layer (422) forms an integral whole with the inner connecting layer (421) and the outer connecting layer (423).

8. The multi-functional wing structure according to claim 1, wherein: The height of the heat insulation component (42) is equal to the thickness of the inner core component (3).

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