A lightweight heat-insulating load-bearing composite structure for wings and rudder wings

Abstract

A lightweight, heat-insulating, load-bearing composite structure for wings and rudders. The present invention belongs to the field of aerospace and marine manufacturing technology. It solves the problem that existing heat-insulating, load-bearing pipe structures cannot simultaneously meet the requirements of heat protection, load bearing, and heat-free short-circuit connection. Structure: The middle part of the outer circumference of the inner metal tube is covered with a core layer tube, the middle part of the outer circumference of the core layer tube is covered with a ring layer tube, and the middle part of the outer circumference of the ring layer tube is covered with an outer metal tube; a load-bearing base and a heat-insulating interlayer are provided between the core layer tube and the ring layer tube. The present invention is a lightweight, heat-insulating, load-bearing composite structure for wings and rudders.

Description

Technical Field

[0001] The invention belongs to the technical field of aerospace and marine manufacturing. Background Art

[0002] The new generation of hypersonic aircraft has extremely stringent requirements for heat insulation and weight reduction. The wing and rudder structures must not only have strong shape-keeping capabilities, but also require internal oil storage to effectively utilize space and reduce the size of the main fuselage's fuel tanks. At the same time, they must also have good heat insulation performance. To meet the combined requirements of oil storage, structural strength, and heat insulation, the wings and rudders must have sufficiently strong internal support structures that cannot transfer heat to the interior and must be lightweight. Currently, the main support structures for rudders and wings include: 1. Sheet reinforcement ribs; 2. Support columns; 3. Honeycomb structures. These structures are mostly connected to the outer skin through welding and other methods, which are prone to thermal short circuits. They can ensure strength, but the heat insulation performance is poor.

[0003] When the inner and outer layers of the wing and rudder structures of an aircraft are connected by support columns, the existing connection method generally adopts a contact connection method, which will form a more obvious thermal short circuit phenomenon and it is difficult to achieve the effect of thermal insulation. If thermal insulation tiles are used to connect and thermally protect the inner and outer layers without thermal short circuit, the required insulation space will be further increased, which will reduce the effective oil storage space, make it difficult to bear stress such as bending moment, and may also cause the overall weight to be overweight. The use of traditional multi-layer thermal insulation materials such as foam plastics for thermal short circuit connection and thermal protection of the inner and outer layers can maintain extremely low thermal conductivity in a vacuum environment, but it cannot bear stress at all and cannot achieve the effect of connection. Therefore, the design of this "heat protection-load bearing-no thermal short circuit connection" thermal insulation load-bearing pipe structure urgently needs further innovation. Summary of the Invention

[0004] The present invention aims to solve the problem that the existing heat-insulating load-bearing pipe structure cannot simultaneously meet the requirements of heat protection, load bearing and thermal short-circuit-free connection, and further provide a lightweight heat-insulating load-bearing composite structure for wings and rudder wings.

[0005] A lightweight heat-insulating load-bearing composite structure for wings and rudder wings, which consists of a core layer tube, a ring layer tube, a load-bearing base, a heat-insulating interlayer, an outer metal tube and an inner metal tube;

[0006] The middle part of the outer circumference of the inner metal tube is covered with a core layer tube, the middle part of the outer circumference of the core layer tube is covered with a ring layer tube, and the middle part of the outer circumference of the ring layer tube is covered with an outer metal tube; the core layer tube and the ring layer tube have the same height, and a bearing base and a heat-insulating interlayer are provided between the core layer tube and the ring layer tube;

[0007] The bearing base is composed of a top bearing base and a bottom bearing base, which are respectively located at the upper and lower ends of the thermal insulation interlayer, and are respectively flush with the upper and lower end surfaces of the core layer tube and the ring layer tube.

[0008] The beneficial effects of the present invention are:

[0009] The lightweight, heat-insulating, load-bearing composite structure for wings and rudder wings of the present invention can meet the requirement that the outer metal tubes and the inner metal tubes will not be deformed due to heat when serving in a complex high-temperature environment; at the same time, it can better meet the stress transfer of the outer metal tubes and the inner metal tubes, so that the overall structure obtains better strength and rigidity, and maintains relatively excellent overall performance.

[0010] The lightweight heat-insulating load-bearing composite structure used for wings and rudder wings of the present invention can effectively achieve complete isolation between the low temperature of the inner metal tube and the outer metal tube, and between the high temperature of the inner metal tube and the low temperature of the outer metal tube, without the need for additional thermal insulation tiles and other thermal protection measures, thereby achieving the requirements of weight reduction, high temperature resistance, heat insulation and high strength.

[0011] The present invention forms a composite sandwich design by combining the advantages of multiple materials and structural characteristics. Different layers of materials meet different functional requirements. At the same time, different components are rationally integrated into a structure to achieve lightweight, heat-resistant, heat-insulating and stress-bearing structural design and manufacturing of the insulated load-bearing pipe structure. BRIEF DESCRIPTION OF THE DRAWINGS

[0012] Figure 1 It is a cross-sectional view of a lightweight heat-insulating load-bearing composite structure for wings and rudder wings of the present invention;

[0013] Figure 2 A perspective view of a lightweight, heat-insulating, load-bearing composite structure for wings and rudder wings according to the present invention;

[0014] Figure 3 Schematic diagram of the angles between the central axes of the outer metal tube and the inner metal tube and the lower surface of the hollow skeleton structure of the wing or rudder wing of the present invention;

[0015] Figure 4 Schematic diagram of the traditional support column reinforcement structure used for rudder wings for comparative experiments;

[0016] Figure 5 This is a schematic diagram of a lightweight, heat-insulating, load-bearing composite structure for a rudder wing according to Example 1;

[0017] Figure 6 This is a mechanical simulation stress distribution diagram of a lightweight heat-insulating load-bearing composite structure for a rudder wing in Example 1;

[0018] Figure 7This is a temperature distribution diagram of heat transfer simulation of a lightweight heat-insulating load-bearing composite structure for a rudder wing in Example 1;

[0019] Figure 8 This is a top view of a lightweight, heat-insulating, load-bearing composite structure for a rudder wing according to Example 2;

[0020] Figure 9 This is a three-dimensional diagram of a lightweight, heat-insulating, load-bearing composite structure for a rudder wing according to Example 2;

[0021] Figure 10 Temperature distribution diagram of the enhanced heat transfer simulation of the traditional support column used for the rudder wing for comparative experiments. DETAILED DESCRIPTION

[0022] Specific implementation method 1: Combination Figures 1 to 3 Specifically, the embodiment of the present invention is a lightweight heat-insulating load-bearing composite structure for wings and rudder wings, which is composed of a core layer tube 1, a ring layer tube 2, a load-bearing base, a heat-insulating interlayer 4, an outer metal tube 5 and an inner metal tube 6;

[0023] The middle part of the outer circumference of the inner metal tube 6 is covered with a core layer tube 1, the middle part of the outer circumference of the core layer tube 1 is covered with a ring layer tube 2, and the middle part of the outer circumference of the ring layer tube 2 is covered with an outer metal tube 5; the core layer tube 1 and the ring layer tube 2 have the same height, and a bearing base and a heat-insulating interlayer 4 are provided between the core layer tube 1 and the ring layer tube 2;

[0024] The load-bearing base is composed of a top load-bearing base 31 and a bottom load-bearing base 32. The top load-bearing base 31 and the bottom load-bearing base 32 are respectively located at the upper and lower ends of the thermal insulation interlayer 4, and the top load-bearing base 31 and the bottom load-bearing base 32 are respectively flush with the upper and lower end surfaces of the core layer tube 1 and the ring layer tube 2.

[0025] The shape, dimensions, and materials of the outer metal tube 5 and inner metal tube 6 are determined by the wing or rudder, enabling mutual stress transfer between the outer metal tube 5 and inner metal tube 6, thereby ensuring coordinated deformation and stability of the wing or rudder. Based on actual process characteristics, the outer metal tube 5 and inner metal tube 6 are rectangular, with cross-sections of one or a combination of square, triangular, pentagonal, circular, and elliptical shapes. The core tube 1 and ring tube 2 are rectangular, conical, curved, bulging, or lantern-shaped.

[0026] The heat insulation effect of the load-bearing base is much smaller than that of the heat-insulating interlayer 4, which prevents most of the heat from being transferred from the load-bearing base. The height of the inner metal tube 6 is increased to keep the load-bearing base away from the outer metal tube 5. The outer metal tube 5 and the inner metal tube 6 are in the shape of straight columns, and the central axis of the outer metal tube 5 and the inner metal tube 6 are the same. The angle between the central axis of the outer metal tube 5 and the inner metal tube 6 and the lower surface of the hollow skeleton structure of the wing or rudder is 10° to 90°. The specific angle is determined according to the service status, such as a completely vertical angle or a 45° angle with the lower surface of the hollow skeleton structure of the wing or rudder.

[0027] A variety of materials with different properties are stacked in sequence to efficiently meet the different functional requirements of different positions. The inner metal tube 6 has no contact connection with the outer metal tube 5, and is completely separated into independent components by the core layer tube 1, the ring layer tube 2, the load-bearing base, and the thermal insulation interlayer 4. During service, the force of the inner metal tube 6 is transmitted to the load-bearing base through the core layer tube 1, and then to the ring layer tube 2, and finally to the outer metal tube 5 by the ring layer tube 2, so that the lightweight thermal insulation load-bearing composite structure is in a mechanically stable state as a whole. At the same time, since the thermal insulation material is mostly lightweight thermal insulation material such as aerogel and thermal insulation adhesive, the thermal insulation interlayer 4 adheres to the ring layer tube 2, so that the ring layer tube 2 forms a space that can be insulated and heat-insulated, so that the heat of the inner metal tube 6 cannot be transferred to the outer metal tube 5, ensuring the low temperature environment of the outer metal tube 5.

[0028] The core layer tube 1 , the ring layer tube 2 , the load-bearing base, and the heat-insulating interlayer 4 are matched according to the shapes of the outer layer metal tube 5 and the inner layer metal tube 6 .

[0029] The top bearing base 31, the bottom bearing base 32, and the thermal insulation interlayer 4 completely separate the core tube 1 and the ring tube 2, preventing the formation of a thermal bridge between the outer metal tube 5 and the inner metal tube 6. The thermal insulation interlayer 4 is fixed between the top bearing base 31 and the bottom bearing base 32 to provide thermal insulation between the core tube 1 and the ring tube 2. The core tube 1 and the ring tube 2 are made of the same material and thickness, and their shapes and dimensions are coordinated with the shapes and dimensions of the outer metal tube 5 and the inner metal tube 6. The core tube 1 is in close contact with the inner metal tube 6, and the ring tube 2 is in close contact with the outer metal tube 5, both of which can achieve mutual transfer of stress and heat. The core tube 1 and the ring tube 2 are made of high-temperature resistant titanium alloy, high-temperature alloy, or titanium-aluminum intermetallic compound, which has excellent properties such as high-temperature strength and high-temperature toughness, and can withstand large stress loads at high temperatures without deformation. The core tube 1 and the inner metal tube 6 are only in simple contact and are not fixed, allowing them to slide, thereby completing the coordinated deformation of the wing or rudder as a whole. The annular layer tube 2 and the outer metal tube 5 are connected by a mortise and tenon structure so as to be completely fixed.

[0030] The bearing base is placed between the core tube 1 and the ring tube 2. Its shape and dimensions match those of the core tube 1 and the ring tube 2, ensuring a tight fit between them at room temperature. The bearing base is adhered to the outer surface of the core tube 1 and the inner surface of the ring tube 2. The bearing base is typically a high-temperature fire-resistant insulation tile. When deformed by cycling between high and room temperature, it will not be damaged by the thermal expansion and contraction of the core tube 1 and the ring tube 2. The height of the top bearing base 31 and the bottom bearing base 32 are both 4% to 21% of the height of the inner metal tube 6, ensuring that the bearing base can transfer stress without causing stress concentration in the core tube 1 and the ring tube 2, which could lead to deformation. The bearing base includes a top bearing base 31 located at the upper ends of the core tube 1 and the ring tube 2, with its top surface completely overlapping with the top surfaces of the core tube 1 and the ring tube 2; and a bottom bearing base 32 located at the lower ends of the core tube 1 and the ring tube 2, with its bottom surface completely overlapping with the bottom surfaces of the core tube 1 and the ring tube 2. The load-bearing base is a strong insulating material that can bear stress. When deformed in a high-temperature and room-temperature cycle, the load-bearing base will not be damaged due to the thermal expansion and contraction of the core layer tube 1 and the ring layer tube 2. The material of the load-bearing base is high-temperature refractory insulating bricks.

[0031] The thermal insulation interlayer 4 is a strong thermal insulation material, such as aerogel, hydrogel, thermal insulation adhesive and other thermal insulation materials, which has a certain strength while ensuring lightweight. When deformed in a high temperature and room temperature cycle, the thermal insulation interlayer 4 will not be damaged due to the thermal expansion and contraction deformation of the core layer tube 1 and the ring layer tube 2.

[0032] The heat-insulating interlayer 4 meets a higher heat-insulating temperature, and the load-bearing base and the core layer tube 1 and the ring layer tube 2 meet a higher stress transfer, thereby avoiding the formation of a heat bridge between the outer metal tube 5 and the inner metal tube 6 while being able to deform cooperatively.

[0033] The beneficial effects of this specific embodiment are:

[0034] The lightweight, heat-insulating, load-bearing composite structure used for wings and rudder wings in this specific embodiment can meet the requirement that the outer metal tube 5 and the inner metal tube 6 will not be deformed due to heat when serving in a complex high-temperature environment; at the same time, it can better meet the stress transfer of the outer metal tube 5 and the inner metal tube 6, so that the overall structure obtains better strength and rigidity, and maintains relatively excellent overall performance.

[0035] The lightweight heat-insulating load-bearing composite structure used for wings and rudder wings in this specific embodiment can effectively achieve complete isolation between the low temperature of the inner metal tube 6 and the outer metal tube 5, and between the high temperature of the inner metal tube 6 and the low temperature of the outer metal tube 5. There is no need for other thermal protection measures such as additional insulation tiles, thereby achieving the requirements of weight reduction, high temperature resistance, heat insulation and high strength.

[0036] This specific implementation method forms a composite sandwich design by combining the advantages of multiple materials and structural characteristics. Different layers of materials meet different functional requirements. At the same time, different components are rationally integrated into a structure to achieve lightweight, heat-resistant, heat-insulating and stress-bearing structural design and manufacturing of the insulated load-bearing pipe structure.

[0037] Specific embodiment 2: This embodiment differs from specific embodiment 1 in that the core tube 1 and the ring tube 2 are made of high-temperature resistant titanium alloy, high-temperature alloy, or titanium-aluminum intermetallic compound; the bearing base is made of high-temperature refractory insulating bricks; the insulating interlayer 4 is made of aerogel, hydrogel, or insulating adhesive; the outer metal tube 5 is made of lightweight aluminum alloy; and the inner metal tube 6 is made of high-temperature Ti alloy or Ti-based alloy. Other features are the same as specific embodiment 1.

[0038] Specific embodiment 3: This embodiment differs from specific embodiment 1 or 2 in that the annular tube 2 and the outer metal tube 5 are connected by a mortise and tenon structure. Other aspects are the same as specific embodiment 1 or 2.

[0039] Specific embodiment 4: This embodiment differs from specific embodiments 1 to 3 in that the core layer tube 1 and the ring layer tube 2 are shaped like a straight column, a cone, a curve, a bulge or a lantern. Other aspects are the same as specific embodiments 1 to 3.

[0040] Specific Embodiment 5: This embodiment differs from Specific Embodiments 1 to 4 in that: the outer metal tube 5 and inner metal tube 6 are rectangular, with a square, triangular, pentagonal, circular, or elliptical cross-section; the outer metal tube 5 and inner metal tube 6 have the same central axis; and the angle between the central axis of the outer metal tube 5 and inner metal tube 6 and the lower surface of the hollow wing or rudder frame structure is 10° to 90°. Other aspects are the same as Specific Embodiments 1 to 4.

[0041] Specific embodiment 6: This embodiment differs from specific embodiments 1 to 5 in that the height of the core layer tube 1 and the ring layer tube 2 is 50% to 75% of the height of the inner metal tube 6. Other aspects are the same as specific embodiments 1 to 5.

[0042] Specific embodiment 7: This embodiment differs from specific embodiments 1 to 6 in that the height of the top bearing base 31 and the bottom bearing base 32 are both 4% to 21% of the height of the inner metal tube 6. Other aspects are the same as specific embodiments 1 to 6.

[0043] Specific embodiment 8: This embodiment differs from Specific embodiments 1 to 7 in that the vertical distance between the lower surface of the top bearing base 31 and the upper surface of the outer metal tube 5 is 6% to 20% of the height of the inner metal tube 6; the vertical distance between the upper surface of the bottom bearing base 32 and the lower surface of the outer metal tube 5 is 6% to 20% of the height of the inner metal tube 6. Other aspects are the same as Specific embodiments 1 to 7.

[0044] Specific embodiment 9: This embodiment differs from specific embodiments 1 to 8 in that the core tube 1 and the ring tube 2 have equal thicknesses, both 1 mm to 3 mm; the bearing base and the thermal insulation interlayer 4 have equal thicknesses, both 5 mm to 50 mm; and the outer metal tube 5 has a thickness of 1 mm to 3 mm. Other aspects are the same as specific embodiments 1 to 8.

[0045] Specific embodiment 10: This embodiment differs from specific embodiments 1 to 9 in that the top bearing base 31 and the bottom bearing base 32 are fixedly connected to the insulation layer 4, the core layer tube 1, and the ring layer tube 2 to form an integrated structure. Other aspects are the same as specific embodiments 1 to 9.

[0046] The following examples are used to verify the beneficial effects of the present invention:

[0047] Example 1, combined with Figure 5 Specifically, take the structure of the rudder of a large aircraft as an example:

[0048] A lightweight heat-insulating load-bearing composite structure for a rudder wing, comprising a core tube 1, a ring tube 2, a load-bearing base, a heat-insulating interlayer 4, an outer metal tube 5, and an inner metal tube 6;

[0049] The middle part of the outer circumference of the inner metal tube 6 is covered with a core layer tube 1, the middle part of the outer circumference of the core layer tube 1 is covered with a ring layer tube 2, and the middle part of the outer circumference of the ring layer tube 2 is covered with an outer metal tube 5; the core layer tube 1 and the ring layer tube 2 have the same height, and a bearing base and a heat-insulating interlayer 4 are provided between the core layer tube 1 and the ring layer tube 2;

[0050] The load-bearing base is composed of a top load-bearing base 31 and a bottom load-bearing base 32. The top load-bearing base 31 and the bottom load-bearing base 32 are respectively located at the upper and lower ends of the thermal insulation interlayer 4, and the top load-bearing base 31 and the bottom load-bearing base 32 are respectively flush with the upper and lower end surfaces of the core layer tube 1 and the ring layer tube 2.

[0051] The material of the core layer tube 1 and the ring layer tube 2 is TC4 alloy; the material of the load-bearing base is asbestos cement tile; the material of the thermal insulation interlayer 4 is SiO2 hydrogel; the material of the outer metal tube 5 is AlLi alloy; the material of the inner metal tube 6 is Ti2AlNb alloy.

[0052] The annular layer tube 2 and the outer metal tube 5 are connected by a mortise and tenon structure.

[0053] The core layer tube 1 and the ring layer tube 2 are in the shape of a straight column and have a circular cross section.

[0054] The outer metal tube 5 and the inner metal tube 6 are in the shape of a straight column with a circular cross-section; the central axis of the outer metal tube 5 and the inner metal tube 6 are the same; the angle between the central axis of the outer metal tube 5 and the inner metal tube 6 and the lower surface of the hollow skeleton structure of the wing or rudder is 90°.

[0055] The inner metal tube 6 has a height of 80 mm and a diameter of 5 mm;

[0056] The height of the core layer tube 1 and the ring layer tube 2 are both 60 mm.

[0057] The height of the top bearing base 31 and the bottom bearing base 32 are both 5 mm.

[0058] The height of the thermal insulation interlayer 4 is 50 mm.

[0059] The height of the outer metal tube 5 is 40 mm.

[0060] Calculation shows that the vertical distance between the lower surface of the top bearing base 31 and the upper surface of the outer metal tube 5 is 5 mm, and the vertical distance between the upper surface of the bottom bearing base 32 and the lower surface of the outer metal tube 5 is 5 mm.

[0061] The core layer tube 1 and the ring layer tube 2 have the same thickness, both 1.5 mm.

[0062] The thickness of the load-bearing base and the heat-insulating interlayer 4 is equal, both 10 mm; the thickness of the outer metal tube 5 is 1 mm.

[0063] The top and bottom bearing bases 31 and 32 are fixedly connected to the insulation layer 4, the core tube 1, and the ring tube 2 using SINWE high-temperature resistant inorganic adhesive to form an integrated structure. The core tube 1 and the inner metal tube 6 are only in simple contact and are not fixed to allow them to slide.

[0064] The ends of the inner metal tube 6 pass through the inner structure of the rudder wing and the rudder wing heat insulation layer, and are welded to the outer structure of the rudder wing; the ends of the core layer tube 1 and the ring layer tube 2 pass through the inner structure of the rudder wing, and are only in simple contact with the rudder wing heat insulation layer, and are not fixed to allow them to slide; the ends of the outer metal tube 5 are welded to the inner structure of the rudder wing;

[0065] In the first embodiment, the annular tube 2 is fitted with the insulation layer and the outer metal tube 5 in the rudder wing to form a mortise and tenon structure, thereby fixing the annular tube 2 and the outer metal tube 5. The insulation interlayer 4 meets the higher insulation temperature and can be well assembled with the load-bearing base.

[0066] Example 2, combined with Figure 8 and Figure 9 Specific description: This embodiment differs from the first embodiment in that the inner metal tube 6 has a square cross-section, while the core tube 1, the ring tube 2, the bearing base, the thermal insulation interlayer 4, and the outer metal tube 5 have circular cross-sections. Other features are the same as the first embodiment.

[0067] The inner metal tube 6 provided in the second embodiment has a square cross section, and the outer metal tube 5 has a circular cross section. Using the lightweight heat-insulating load-bearing tube structure of this embodiment, the prepared lightweight heat-insulating load-bearing tube can meet the requirements of lightweight, stress transfer, high temperature resistance, heat insulation and other properties.

[0068] Comparative experiment: Combination Figure 4 Specifically, this comparative experiment differs from Example 1 in that, taking the traditional support column-reinforced inner and outer rudder wing structures of a large aircraft as an example, an outer metal tube 5 is sleeved onto an inner metal tube 6 wrapped in asbestos cement tiles and fixedly connected, and both ends of the outer metal tube 5 are welded to the inner structure of the rudder wing. The outer metal tube 5 (made of AlLi intermetallic compound) has a tube height of 40 mm, a diameter of 30 mm, a circular cross-section, and a temperature resistance of 120°C. The inner metal tube 6 (made of TiAl intermetallic compound) has a tube height of 80 mm, a diameter of 10 mm, a circular cross-section, and a temperature resistance of up to 640°C. Other aspects are the same as Example 1.

[0069] In both Example 1 and the comparative experiment, the structure of the inner and outer rudder wings (600mm×1000mm×80mm) of a large aircraft is used as an example to perform mechanical simulation on the composite structure to observe its stress distribution.

[0070] Figure 6 This is a stress distribution diagram of a mechanical simulation of a lightweight heat-insulating load-bearing composite structure for a rudder wing in Example 1; Figure 7This is a temperature distribution diagram of the heat transfer simulation of the lightweight heat-insulating load-bearing composite structure used for the rudder wing in Example 1. It is not difficult to see from the simulation results that this lightweight heat-insulating load-bearing composite structure used for the rudder wing structure can better meet the stress transfer between the inner and outer tubes, making the connection more stable, and the overall structure obtains better strength and rigidity, maintaining relatively excellent overall performance. Thermal short circuit is metal contact heat transfer, that is, there is a thermal bridge. Although the traditional structure does not have metal contact, the thermal insulation cannot reach the thermal conductivity of non-contact heat transfer. The improved composite structure of this embodiment can achieve this, so it is equivalent to blocking the thermal short circuit. Therefore, the connection of this composite structure obviously does not produce a thermal short circuit, and the complete thermal insulation function of the inner column and the outer tube is achieved.

[0071] Figure 10 The temperature distribution diagram of the heat transfer simulation is shown for the comparison experiment of the traditional support column reinforced rudder wing. It can be clearly seen that the structure of the inner and outer layers of the rudder wing reinforced by the traditional support column has greatly reduced the heat insulation performance due to the existence of thermal bridges, making it difficult for the inner layer of the rudder wing to meet the service conditions of the current high-speed aircraft.

[0072] The lightweight heat-insulating load-bearing composite structure for the rudder wing of embodiment 1 has a lower overall density than the inner and outer rudder wing reinforced with traditional support columns, solving the problem that the existing rudder wing cannot meet the requirements of tubular columnar structure connection without thermal short circuit.

Claims

1. A lightweight heat-insulating load-bearing composite structure for wings and rudder wings, characterized by It consists of a core layer tube (1), a ring layer tube (2), a load-bearing base, a heat-insulating interlayer (4), an outer metal tube (5) and an inner metal tube (6); The middle part of the outer circumference of the inner metal tube (6) is covered with a core tube (1), the middle part of the outer circumference of the core tube (1) is covered with a ring tube (2), and the middle part of the outer circumference of the ring tube (2) is covered with an outer metal tube (5); the core tube (1) and the ring tube (2) have the same height, and a load-bearing base and a heat-insulating interlayer (4) are provided between the core tube (1) and the ring tube (2); The load-bearing base is composed of a top load-bearing base (31) and a bottom load-bearing base (32), the top load-bearing base (31) and the bottom load-bearing base (32) are respectively located at the upper and lower ends of the thermal insulation interlayer (4), and the top load-bearing base (31) and the bottom load-bearing base (32) are respectively flush with the upper and lower end surfaces of the core layer tube (1) and the ring layer tube (2); The outer metal tube (5) and the inner metal tube (6) are in the shape of a straight column, and their cross-sections are square, triangular, pentagonal, circular or elliptical; the central axis of the outer metal tube (5) and the inner metal tube (6) are the same; and the angle between the central axis of the outer metal tube (5) and the inner metal tube (6) and the lower surface of the hollow skeleton structure of the wing or rudder wing is 10° to 90°.

2. A lightweight heat-insulating load-bearing composite structure for wing and rudder wing structures according to claim 1, characterized in that The core layer tube (1) and the ring layer tube (2) are made of high-temperature resistant titanium alloy, high-temperature alloy or titanium-aluminum intermetallic compound; the material of the load-bearing base is high-temperature refractory insulation brick; the material of the insulation interlayer (4) is aerogel, hydrogel or insulation adhesive; the material of the outer metal tube (5) is lightweight aluminum alloy; the material of the inner metal tube (6) is high-temperature Ti alloy or Ti-based alloy.

3. A lightweight heat-insulating load-bearing composite structure for wing and rudder wing structures according to claim 1, characterized in that The annular layer tube (2) and the outer metal tube (5) are connected by a mortise and tenon structure.

4. A lightweight heat-insulating load-bearing composite structure for wing and rudder wing structures according to claim 1, characterized in that The core layer tube (1) and the ring layer tube (2) are in the shape of a straight column, a cone, a curve, a bulge or a lantern.

5. A lightweight heat-insulating load-bearing composite structure for wing and rudder wing structures according to claim 1, characterized in that The height of the core layer tube (1) and the ring layer tube (2) is 50% to 75% of the height of the inner layer metal tube (6).

6. A lightweight heat-insulating load-bearing composite structure for wing and rudder wing structures according to claim 1, characterized in that The heights of the top bearing base (31) and the bottom bearing base (32) are both 4% to 21% of the height of the inner metal tube (6).

7. A lightweight heat-insulating load-bearing composite structure for wing and rudder wing structures according to claim 1, characterized in that The vertical distance between the lower surface of the top bearing base (31) and the upper surface of the outer metal tube (5) is 6% to 20% of the height of the inner metal tube (6); the vertical distance between the upper surface of the bottom bearing base (32) and the lower surface of the outer metal tube (5) is 6% to 20% of the height of the inner metal tube (6).

8. A lightweight heat-insulating load-bearing composite structure for wing and rudder wing structures according to claim 1, characterized in that The core layer tube (1) and the ring layer tube (2) have the same thickness, both ranging from 1 mm to 3 mm; the load-bearing base and the heat-insulating interlayer (4) have the same thickness, both ranging from 5 mm to 50 mm; and the outer metal tube (5) has a thickness of 1 mm to 3 mm.

9. A lightweight heat-insulating load-bearing composite structure for wing and rudder wing structures according to claim 1, characterized in that The top load-bearing base (31) and the bottom load-bearing base (32) are fixedly connected to the heat-insulating interlayer (4), the core layer tube (1), and the ring layer tube (2) to form an integrated structure.

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