An oil storage wing / rudder wing supported by a combination of plate columns and trusses

Abstract

The present invention relates to an oil storage wing / rudder wing supported by a combination of plate columns and trusses, and belongs to the field of aerospace manufacturing technology. The present invention aims to solve the problems of insufficient high-stress bearing capacity and poor heat insulation ability at high temperatures in existing oil storage wings and rudder wings in complex aerospace environments. The oil storage wing / rudder wing supported by a combination of plate columns and trusses consists of vertical thick plates, multiple rows of side trusses, a perforated oil tank, multiple intermediate oblique columns, a wing shell, and heat insulation filling. The present invention is used for oil storage wings / rudder wings supported by a combination of plate columns and trusses.

Description

Technical Field

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

[0002] With the rapid development of aerospace technology, hypersonic vehicles have become a key research topic in the modern aerospace field. However, hypersonic vehicles face extreme challenges in terms of aerodynamic loads, thermal environments, and structural stresses. Wings and rudders are key control components of hypersonic vehicles, primarily responsible for adjusting flight attitude and heading. Furthermore, due to the aircraft's extreme lightweight and high fuel consumption requirements, fuel-storage wings and rudders are often required to maximize space utilization. Therefore, the structural design and optimization of these fuel-storage wings and rudders are particularly critical.

[0003] Existing fuel storage wings and rudder wings include honeycomb structures, columnar skeletal structures, and multi-layer composite panels. Each of these structures has its own drawbacks. Honeycomb structures are excessively heavy, columnar skeletal structures have weak stress-bearing capacity, and multi-layer composite panels offer poor thermal insulation. Therefore, a rudder wing structure that combines high load-bearing capacity with strong thermal insulation is urgently needed to meet the increasingly complex service environments of high-speed aircraft. Summary of the Invention

[0004] The present invention aims to solve the problems of insufficient high stress bearing capacity and poor heat insulation ability under high temperature of existing oil storage wings and rudder wings in complex aerospace environments, and provides an oil storage wing / rudder wing with a hybrid support of plate columns and trusses.

[0005] An oil storage wing / rudder wing with a hybrid support of plates, columns and trusses, which consists of vertical thick plates, multiple rows of side trusses, a perforated oil tank, multiple intermediate oblique columns, a wing shell and thermal insulation filling;

[0006] The perforated fuel tank is provided with a plurality of holes in the middle; the gaps around the perforated fuel tank and between the upper and lower surfaces and the wing shell, as well as the holes in the perforated fuel tank, are filled with thermal insulation fillings, and the vertical thick plates, multiple rows of side trusses and multiple middle oblique columns are all arranged in the thermal insulation fillings;

[0007] The vertical thick plate is composed of a long thick plate and a plurality of short thick plates, and the long thick plate is arranged between the connection end of the wing / rudder wing and the fuselage and the perforated fuel tank, and is arranged along the length direction of the wing / rudder wing. Assuming that the length of the wing / rudder wing is L and the width is D, the length of the long thick plate is l, and the distance between the long thick plate and the connection end of the wing / rudder wing and the fuselage is d1, l=L, d1=(0.1-0.25)D; the plurality of short thick plates are distributed between the long thick plate and the perforated fuel tank along the length direction of the wing / rudder wing, and are arranged in a row symmetrically along the center line of the length direction of the wing / rudder wing.

[0008] The multiple rows of side trusses are distributed on both sides of the perforated fuel tank along the width direction of the wing / rudder wing and are arranged symmetrically along the centerline of the length direction of the wing / rudder wing; each row of side trusses is composed of multiple vertical rods and multiple diagonal rods; the long thick plate is provided with multiple vertical grooves, and the vertical rods at one end of each row of side trusses are embedded in the vertical grooves of the long thick plate, and the other end is located at the tail streamline end of the wing / rudder wing;

[0009] The plurality of intermediate oblique columns are arranged in the holes of the perforated fuel tank and are arranged symmetrically along the centerline of the wing / rudder wing length direction;

[0010] The vertical thick plates and vertical rods are vertically connected to the upper and lower panels of the wing shell, and the oblique rods and middle oblique columns are connected to the upper and lower panels of the wing shell at an inclined angle.

[0011] The beneficial effects of the present invention are:

[0012] This invention provides a structural design for an oil storage wing and rudder that utilizes a hybrid support structure of plates, columns, and trusses. This design combines existing plate-rib structures with a multi-column structure to create a novel wing and rudder structure. Thick plates are used in critical locations with high stresses to preserve the high stress-bearing capacity of the plate-rib structure. Multiple columns and trusses are used in areas with significant deformation to significantly reduce density. This design also provides a certain degree of deformation tolerance and improves the structure's thermal insulation properties, achieving multifunctional optimization of the wing and rudder.

[0013] By introducing a truss structure into the bridge, the present invention, on the one hand, enables the trusses and thick plates to form a cross tenon, thereby greatly improving the overall stability of the structure and better transmitting stress; on the other hand, in areas with large deformation and stress, the truss structure has greater stress bearing capacity and strain coordination ability, and also achieves weight reduction, which is a highly creative breakthrough.

[0014] The present invention is used for an oil storage wing / rudder wing supported by a combination of plate columns and trusses. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 This is a schematic structural diagram of the oil storage wing / rudder wing supported by a combination of plate columns and trusses according to the present invention;

[0016] Figure 2 A schematic diagram showing the positions of the vertical thick plates, side truss connections and perforated fuel tanks in the wing shell of the present invention;

[0017] Figure 3 It is a structural schematic diagram of the side truss beam of the present invention;

[0018] Figure 4 This is a schematic structural diagram of the middle inclined column of the present invention;

[0019] Figure 5 This is a schematic diagram of the combination of the perforated oil tank and the vertical thick plate of the present invention;

[0020] Figure 6 The mechanical simulation results of the oil storage rudder wing with mixed support of plate columns and trusses in Example 1 are shown;

[0021] Figure 7 The thermal simulation results of the oil storage rudder wing with mixed support of plate columns and trusses in Example 1 are shown. DETAILED DESCRIPTION

[0022] The technical solution of the present invention is not limited to the specific implementation methods listed below, but also includes any combination of the specific implementation methods.

[0023] Specific implementation method 1, combined with Figures 1 to 5 Specific description: This embodiment is a fuel storage wing / rudder wing with a hybrid support of plate columns and trusses, which consists of a vertical thick plate 1, multiple rows of side trusses 2, a perforated fuel tank 3, multiple intermediate inclined columns 4, a wing shell 5 and a thermal insulation filling 6;

[0024] The perforated fuel tank 3 is provided with a plurality of holes in the middle thereof; the gaps around the perforated fuel tank 3 and between the upper and lower surfaces and the wing shell 5, as well as the holes of the perforated fuel tank 3, are filled with a heat-insulating filler 6, and the vertical thick plate 1, the plurality of rows of side trusses 2 and the plurality of middle oblique columns 4 are all arranged in the heat-insulating filler 6;

[0025] The vertical thick plate 1 is composed of a long thick plate 11 and a plurality of short thick plates 12, and the long thick plate 11 is arranged between the connection end of the wing / rudder wing and the fuselage and the perforated fuel tank 3, and is arranged along the length direction of the wing / rudder wing. Assuming that the length of the wing / rudder wing is L and the width is D, the length of the long thick plate 11 is l, and the distance between the long thick plate 11 and the connection end of the wing / rudder wing and the fuselage is d1, l = L, d1 = (0.1-0.25) D; the plurality of short thick plates 12 are distributed between the long thick plate 11 and the perforated fuel tank 3 along the length direction of the wing / rudder wing, and are arranged in a row symmetrically along the center line of the length direction of the wing / rudder wing;

[0026] The multiple rows of side trusses 2 are distributed on both sides of the perforated fuel tank 3 along the width direction of the wing / rudder wing and are arranged symmetrically along the centerline of the length direction of the wing / rudder wing; each row of side trusses 2 is composed of multiple vertical rods 21 and multiple diagonal rods 22; the long thick plate 11 is provided with multiple vertical grooves, and the vertical rods 21 at one end of each row of side trusses 2 are embedded in the vertical grooves of the long thick plate 11, and the other end is located at the tail streamline end of the wing / rudder wing;

[0027] The plurality of intermediate oblique columns 4 are arranged in the holes of the perforated fuel tank 3 and are arranged symmetrically along the center line of the wing / rudder wing length direction;

[0028] The vertical thick plates 1 and the vertical rods 21 are vertically connected to the upper and lower panels of the wing shell 5 , and the oblique rods 22 and the middle oblique columns 4 are connected to the upper and lower panels of the wing shell 5 at an inclined angle.

[0029] The shape and size of the perforated fuel tank 3 described in this embodiment are determined according to the specific requirements of the aircraft, and the position and size of the perforations are determined by the position and size of the middle inclined column.

[0030] The shape and dimensions of the wing shell 5 described in this embodiment are determined by the specific requirements of the aircraft. It is made of a high-temperature, high-strength alloy to ensure stress-bearing capacity in high-temperature environments. It is connected to the vertical thick plates 1, side girders 2, and central diagonal columns 4 through welding to ensure structural integrity and sealing.

[0031] In this embodiment, vertical thick plates 1, side girders 2, and central diagonal columns 4 connect the upper and lower panels of the wing shell 5, forming the wing and rudder fins as a single unit. The perforated fuel tank 3 and wing shell 5 are both sealed structures, with the gap between them filled with thermal insulation 6 to isolate the perforated fuel tank and achieve a thermal insulation effect.

[0032] In this embodiment, the vertical slabs 1, side girders 2, and central diagonal columns 4 are the primary components that bear stress on the wings and rudder, maintaining overall structural stability. The vertical slabs 1 are composed of multiple long, thick sections perpendicular to the wing shell 5, consisting of long slabs 11 and short slabs 12. The short slabs 12 are primarily designed to match the shape of the fuel tank, maximizing the structure's stress-bearing capacity.

[0033] In this embodiment, the vertical rod 21 at one end of the side truss beam 2 is embedded in the vertical groove of the long thick plate 11 to form a stable cross-tenon structure, thereby greatly improving the overall stability of the structure.

[0034] In this embodiment, the middle oblique columns 4 are all oblique columns that pass through the perforated fuel tank 3 and are inclined at a certain angle to the upper and lower panels of the wing shell 5. The middle oblique columns 4 in two adjacent rows are staggered to form a cross, which facilitates coordinated strain and deformation control.

[0035] In this embodiment, the main material of the heat insulating filler 6 is aerogel, which is filled artificially to fill all gaps to obtain the maximum heat insulating performance.

[0036] The tail of a wing is generally a streamlined curved surface, which is mostly a semicircle. In this specific embodiment, the streamlined end of the tail is the starting point of the curved surface of the wing.

[0037] The beneficial effects of this embodiment are:

[0038] This embodiment provides a structural design for an oil storage wing and rudder using a hybrid support structure of plates, columns, and trusses. This design combines existing plate-ribbed structures with a multi-column structure to create a novel wing and rudder structure. Thick plates are used in critical locations with high stresses to preserve the high stress-bearing capacity of the plate-ribbed structure. Multiple columns and trusses are used in areas with high deformation to significantly reduce density, while maintaining a certain degree of deformation tolerance and improving the structure's thermal insulation properties, achieving multifunctional optimization of the wing and rudder.

[0039] This implementation introduces a truss structure into the bridge. On the one hand, it forms a cross-tenon between the truss and the thick plate, thereby greatly improving the overall stability of the structure and better transferring stress. On the other hand, in areas with large deformation and stress, the truss structure has greater stress bearing capacity and strain coordination ability, and also achieves weight reduction, which is a highly creative breakthrough.

[0040] Specific embodiment 2: This embodiment differs from specific embodiment 1 in that the thickness of the vertical thick plate 1 is b, b≥0.015D. Other aspects are the same as specific embodiment 1.

[0041] Specific embodiment 3: This embodiment differs from specific embodiments 1 or 2 in that the distance between the short thick plate 12 and the perforated oil tank 3 is c, c ≥ 15 mm, and the short thick plate 12 and the adjacent side surfaces of the perforated oil tank 3 are parallel. Other aspects are the same as specific embodiments 1 or 2.

[0042] Specific embodiment 4: This embodiment differs from specific embodiments 1 to 3 in that the upper and lower ends of adjacent vertical rods 21 in each row of side trusses 2 are connected by an oblique rod 22, and the oblique rods 22 on both sides of the vertical rod 21 are arranged symmetrically along the vertical rod 21. Other aspects are the same as specific embodiments 1 to 3.

[0043] Specific embodiment 5: This embodiment differs from specific embodiments 1 to 4 in that: the width of the vertical rod 21 and the oblique rod 22 are both d, d ≥ 4mm; the distance between adjacent vertical rods 21 is f, 125mm ≥ f ≥ 75mm; the number of vertical rods 21 is k, Assume that the angle between the oblique rod 22 and the adjacent vertical rod 21 is θ, 30°≥θ≥70°. Other aspects are the same as those of the first to fourth embodiments.

[0044] In this embodiment, the number k of the vertical rods 21 is calculated by rounding down:

[0045] Specific embodiment 6: This embodiment differs from specific embodiments 1 to 5 in that, among the multiple rows of side trusses 2, the lateral distance between the outermost side trusses 2 and the wing shell 5 along the width direction is d2, where d2 = (1 to 2) d1; and, among the multiple rows of side trusses 2, the spacing between two adjacent rows of side trusses 2 is d3, where d3 = (1 to 1.5) d2. Other aspects are the same as specific embodiments 1 to 5.

[0046] Specific Embodiment 7: This embodiment differs from any one of Specific Embodiments 1 to 6 in that the plurality of intermediate inclined columns 4 are disposed within the holes of the perforated fuel tank 3. Within each hole, the intermediate inclined columns 4 are arranged in n rows by m columns, where n is an even number and n ≥ 2 and m ≥ 2. The rows are arranged along the length of the wing / rudder, and the columns are arranged along the width of the wing / rudder. The intermediate inclined columns 4 in adjacent rows are staggered. The inclination angle of the intermediate inclined columns 4 is α, 40° ≤ α ≤ 80°. Other aspects are the same as Specific Embodiments 1 to 6.

[0047] Specific embodiment 8: This embodiment differs from Specific embodiments 1 to 7 in that the cross-sectional shapes of the plurality of intermediate inclined columns 4 are all circular, square, or polygonal; and the distance between the two farthest points of the cross-sectional shape of the intermediate inclined columns 4 is f1, where f1 = (0.2% to 1.2%) L. Other aspects are the same as Specific embodiments 1 to 7.

[0048] Specific embodiment 9: This embodiment differs from specific embodiments 1 to 8 in that the maximum height of the wing / rudder wing is H, the minimum thickness of the heat insulation filling 6 is g, and g ≥ 0.18 H. Other aspects are the same as specific embodiments 1 to 8.

[0049] Specific Embodiment 10: This embodiment differs from Specific Embodiments 1 to 9 in that the vertical thick plates 1, multiple rows of side trusses 2, and multiple intermediate inclined columns 4 are all made of the same material as the wing shell 5; and the final service environment temperature of the oil storage wing / rudder wing is T, 700°C ≥ T ≥ 350°C. Other aspects are the same as Specific Embodiments 1 to 9.

[0050] The following examples are used to verify the beneficial effects of the present invention:

[0051] In Example 1, a large aircraft rudder wing component is taken as an example, which has a length of 1000 mm, a width of 600 mm, and a maximum height of 100 mm:

[0052] An oil storage rudder wing with a mixed support of plate columns and trusses, which consists of a vertical thick plate 1, four rows of side trusses 2, a perforated oil tank 3, a plurality of intermediate inclined columns 4, a wing shell 5 and a heat insulation filling 6;

[0053] Three rectangular holes are arranged in parallel in the middle of the perforated fuel tank 3 along the length direction of the rudder wing; the gaps around the perforated fuel tank 3 and between the upper and lower surfaces and the wing shell 5, as well as the holes of the perforated fuel tank 3, are filled with thermal insulation filling 6, and the vertical thick plate 1, the four rows of side trusses 2 and the multiple middle inclined columns 4 are all arranged in the thermal insulation filling 6;

[0054] The vertical thick plate 1 is composed of a long thick plate 11 and three short thick plates 12, and the long thick plate 11 is arranged between the connection end between the rudder wing and the fuselage and the perforated fuel tank 3, and is arranged along the length direction of the rudder wing. Assuming that the length of the rudder wing is L and the width is D, the length of the long thick plate 11 is l, and the distance between the long thick plate 11 and the connection end between the rudder wing and the fuselage is d1, L = 1000mm, D = 600mm, l = L, d1 = 60mm; the three short thick plates 12 are distributed between the long thick plate 11 and the perforated fuel tank 3 along the length direction of the rudder wing and are arranged in a row symmetrically along the center line of the length direction of the rudder wing;

[0055] The four rows of side trusses 2 are distributed on both sides of the perforated fuel tank 3 along the width direction of the rudder wing and are arranged symmetrically along the centerline of the length direction of the rudder wing; each row of side trusses 2 is composed of multiple vertical rods 21 and multiple diagonal rods 22; the long thick plate 11 is provided with multiple vertical grooves, and the vertical rods 21 at one end of each row of side trusses 2 are embedded in the vertical grooves of the long thick plate 11, and the other end is located at the tail streamline end of the rudder wing;

[0056] The plurality of intermediate oblique columns 4 are arranged in the holes of the perforated oil tank 3 and are arranged symmetrically along the center line of the rudder wing length direction;

[0057] The vertical thick plates 1 and the vertical rods 21 are vertically connected to the upper and lower panels of the wing shell 5 , and the oblique rods 22 and the middle oblique columns 4 are connected to the upper and lower panels of the wing shell 5 at an inclined angle.

[0058] The thickness of the vertical thick plate 1 is b, b = 10 mm;

[0059] Assume that the distance between the short thick plate 12 and the perforated fuel tank 3 is c, c = 20 mm, the distance between the short thick plate 12 and the connection between the rudder wing and the fuselage is 80 mm, and the adjacent side of the short thick plate 12 and the perforated fuel tank 3 is parallel;

[0060] The upper and lower ends of adjacent vertical rods 21 in each row of side trusses 2 are connected by an oblique rod 22, and the oblique rods 22 on both sides of the vertical rod 21 are symmetrically arranged along the vertical rod 21;

[0061] Assume that the width of the vertical rod 21 and the diagonal rod 22 are both d, d = 5mm; Assume that the distance between adjacent vertical rods 21 is f, f = 75mm; Assume that the number of vertical rods 21 is k, Assume that the angle between the diagonal rod 22 and the adjacent vertical rod 21 is θ, θ = 42°;

[0062] Assume that the side distance between the outermost side truss 2 and the wing shell 5 in the width direction of the four rows of side trusses 2 is d2, d2 = 80 mm; and assume that the spacing between two adjacent rows of side trusses 2 in the four rows of side trusses 2 is d3, d3 = 100 mm.

[0063] The plurality of intermediate oblique columns 4 are disposed in the holes of the perforated fuel tank 3. Within a single hole, the intermediate oblique columns 4 are arranged in n rows × m columns, where n is an even number and n=2, wherein rows are arranged along the length of the rudder wing and columns are arranged along the width of the rudder wing. The intermediate oblique columns 4 in two adjacent rows are staggered. The inclination angle of the intermediate oblique columns 4 is α. Starting from the end closest to the wing connection, the inclination angle α of the intermediate oblique columns 4 in each hole is 75°, 60°, and 45°, respectively. The number m is 12 columns, 8 columns, and 8 columns, respectively.

[0064] The cross-sections of the plurality of intermediate oblique columns 4 are all circular. Assume that the distance between the two farthest points of the cross-section of a single intermediate oblique column 4 is f1, that is, the radius of the circle is f1, and f1 = 4 mm.

[0065] Assume that the maximum height of the rudder wing is H, H = 100 mm, and the minimum thickness of the thermal insulation filling 6 is g, g = 18 mm;

[0066] The vertical thick plates 1, the four rows of side trusses 2, the multiple middle oblique columns 4 and the wing shells 5 are all made of Ti2AlNb;

[0067] The final service environment temperature of the oil storage rudder wing is T, T = 520 ° C;

[0068] The perforated fuel tank 3 is made of AlLi alloy and can be loaded with fuel; the thermal insulation filler 6 is SiO2 aerogel.

[0069] Figure 6 The mechanical simulation results of the oil storage rudder wing with a hybrid support of plates, columns and trusses in Example 1 are shown. It can be clearly seen from the results that under normal flight stress, the maximum internal stress of this structure is 148.52 MPa, with no obvious stress concentration points, which meets the service environment requirements of high-temperature and high-strength materials for most aircraft.

[0070] Figure 7 The thermal simulation results of the oil storage rudder wing with mixed support of plate columns and trusses in Example 1 can be seen from the results. When the external temperature environment is 520°C, the rudder wing with this structure can still ensure that the temperature of the internal oil tank does not exceed 90°C for a long time.

[0071] The density of the oil storage rudder wing supported by the plate column and truss beam is 1.35g / mm 3 , slightly reducing the mass of the rudder wing.

Claims

1. An oil storage wing with mixed support of plate columns and trusses, characterized in that: The fuel storage wing is composed of a vertical thick plate (1), multiple rows of side trusses (2), a perforated fuel tank (3), multiple intermediate inclined columns (4), a wing shell (5) and a heat insulation filling (6); The perforated fuel tank (3) is provided with a plurality of holes in the middle; the gaps around the perforated fuel tank (3) and between the upper and lower surfaces and the wing shell (5), and the holes of the perforated fuel tank (3) are all filled with heat-insulating filling (6), and the vertical thick plate (1), the plurality of side trusses (2) and the plurality of middle inclined columns (4) are all arranged in the heat-insulating filling (6); The vertical thick plate (1) is composed of a long thick plate (11) and a plurality of short thick plates (12), and the long thick plate (11) is arranged between the wing and fuselage connection end and the perforated fuel tank (3), and is arranged along the length direction of the wing; assuming that the length of the wing is L, the width is D, the length of the long thick plate (11) is l, and the distance between the long thick plate (11) and the wing and fuselage connection end is d1, l=L, d1=(0.1~0.25)D; the plurality of short thick plates (12) are distributed between the long thick plate (11) and the perforated fuel tank (3) along the length direction of the wing, and are arranged in a row symmetrically along the center line of the wing length direction; The plurality of side trusses (2) are distributed on both sides of the perforated fuel tank (3) along the width direction of the wing and are arranged symmetrically along the center line of the length direction of the wing; each row of side trusses (2) is composed of a plurality of vertical rods (21) and a plurality of diagonal rods (22); a plurality of vertical grooves are provided on the long thick plate (11), and the vertical rods (21) at one end of each row of side trusses (2) are embedded in the vertical groove of the long thick plate (11), and the other end is located at the tail streamline end of the wing; The plurality of intermediate oblique columns (4) are arranged in the holes of the perforated fuel tank (3) and are arranged symmetrically along the center line of the wing length direction; The vertical thick plate (1) and the vertical rod (21) are vertically connected to the upper and lower panels of the wing shell (5), and the inclined rod (22) and the middle inclined column (4) are connected to the upper and lower panels of the wing shell (5) at an inclined angle.

2. The oil storage wing with hybrid support of plate columns and trusses according to claim 1, characterized in that: The thickness of the vertical thick plate (1) is b, b≥0.015D.

3. The oil storage wing with hybrid support of plate columns and trusses according to claim 1, characterized in that: Assume that the distance between the short thick plate (12) and the perforated oil tank (3) is c, c ≥ 15 mm, and the short thick plate (12) is adjacent to and parallel to one side surface of the perforated oil tank (3).

4. The oil storage wing with hybrid support of plate columns and trusses according to claim 1, characterized in that: The upper and lower ends of adjacent vertical bars (21) in each row of side trusses (2) are connected by an oblique bar (22), and the oblique bars (22) on both sides of the vertical bars (21) are symmetrically arranged along the vertical bars (21).

5. The oil storage wing with hybrid support of plate columns and trusses according to claim 1, characterized in that: Assume that the width of the vertical rod (21) and the diagonal rod (22) are both d, d ≥ 4mm; Assume that the distance between adjacent vertical rods (21) is f, 125mm ≥ f ≥ 75mm; Assume that the number of vertical rods (21) is k, ; Assume that the angle between the diagonal rod (22) and the adjacent vertical rod (21) is θ, 30°≥θ≥70°.

6. The oil storage wing with hybrid support of plate columns and trusses according to claim 1, characterized in that: Assume that among the multiple rows of side trusses (2), the side distance between the outermost side trusses (2) and the wing shell (5) along the width direction is d2, d2=(1~2)d1; and assume that among the multiple rows of side trusses (2), the spacing between two adjacent rows of side trusses (2) is d3, d3=(1~1.5)d2.

7. The oil storage wing with hybrid support of plate columns and trusses according to claim 1, characterized in that: The plurality of intermediate oblique columns (4) are arranged in holes of the perforated fuel tank (3), and the intermediate oblique columns (4) in a single hole are arranged in n rows and m columns, where n is an even number, and n≥2, and m≥2, wherein the rows are arranged along the length direction of the wing, and the columns are arranged along the width direction of the wing, and the intermediate oblique columns (4) in two adjacent rows are staggered with each other; and the inclination angle of the intermediate oblique columns (4) is α, and 40°≤α≤80°.

8. The oil storage wing with hybrid support of plate columns and trusses according to claim 1, characterized in that: The cross-sectional shapes of the plurality of intermediate inclined columns (4) are all circular or polygonal; assuming that the distance between the two farthest points of the cross-sectional area of ​​the intermediate inclined column (4) is f1, f1=(0.2%~1.2%)L.

9. The oil storage wing with hybrid support of plate columns and trusses according to claim 1, characterized in that: Assume that the maximum height of the wing is H and the minimum thickness of the insulation filling (6) is g, g ≥ 0.18H.

10. The oil storage wing with hybrid support of plate columns and trusses according to claim 1, characterized in that: The vertical thick plates (1), multiple rows of side trusses (2) and multiple intermediate oblique columns (4) are all made of the same material as the wing shell (5); the final service environment temperature of the oil storage wing is T, 700°C ≥ T ≥ 350°C.

11. An oil storage rudder wing with mixed support of plate columns and trusses, characterized in that: The oil storage rudder wing is composed of a vertical thick plate (1), multiple rows of side trusses (2), a perforated oil tank (3), multiple intermediate inclined columns (4), a wing shell (5) and a heat insulation filling (6); The perforated fuel tank (3) is provided with a plurality of holes in the middle; the gaps around the perforated fuel tank (3) and between the upper and lower surfaces and the wing shell (5), and the holes of the perforated fuel tank (3) are all filled with heat-insulating filling (6), and the vertical thick plate (1), the plurality of side trusses (2) and the plurality of middle inclined columns (4) are all arranged in the heat-insulating filling (6); The vertical thick plate (1) is composed of a long thick plate (11) and a plurality of short thick plates (12), and the long thick plate (11) is arranged between the connecting end of the rudder wing and the fuselage and the perforated fuel tank (3), and is arranged along the length direction of the rudder wing; assuming that the length of the rudder wing is L, the width is D, the length of the long thick plate (11) is l, and the distance between the long thick plate (11) and the connecting end of the rudder wing and the fuselage is d1, l=L, d1=(0.1~0.25)D; the plurality of short thick plates (12) are distributed between the long thick plate (11) and the perforated fuel tank (3) along the length direction of the rudder wing, and are arranged in a row symmetrically along the center line of the length direction of the rudder wing; The plurality of side trusses (2) are distributed on both sides of the perforated fuel tank (3) along the width direction of the rudder wing and are arranged symmetrically along the center line of the length direction of the rudder wing; each row of side trusses (2) is composed of a plurality of vertical rods (21) and a plurality of diagonal rods (22); a plurality of vertical grooves are provided on the long thick plate (11), and the vertical rods (21) at one end of each row of side trusses (2) are embedded in the vertical groove of the long thick plate (11), and the other end is located at the tail streamline end of the rudder wing; The plurality of intermediate inclined columns (4) are arranged in the holes of the perforated oil tank (3) and are arranged symmetrically along the center line of the rudder wing length direction; The vertical thick plate (1) and the vertical rod (21) are vertically connected to the upper and lower panels of the wing shell (5), and the inclined rod (22) and the middle inclined column (4) are connected to the upper and lower panels of the wing shell (5) at an inclined angle.

12. The oil storage rudder wing with mixed support of plate columns and trusses according to claim 11, characterized in that: The thickness of the vertical thick plate (1) is b, b≥0.015D.

13. The oil storage rudder wing with mixed support of plate columns and trusses according to claim 11, characterized in that: Assume that the distance between the short thick plate (12) and the perforated oil tank (3) is c, c ≥ 15 mm, and the short thick plate (12) is adjacent to and parallel to one side surface of the perforated oil tank (3).

14. The oil storage rudder wing with mixed support of plate columns and trusses according to claim 11, characterized in that: The upper and lower ends of adjacent vertical bars (21) in each row of side trusses (2) are connected by an oblique bar (22), and the oblique bars (22) on both sides of the vertical bars (21) are symmetrically arranged along the vertical bars (21).

15. The oil storage rudder wing with mixed support of plate columns and trusses according to claim 11, characterized in that: Assume that the width of the vertical rod (21) and the diagonal rod (22) are both d, d ≥ 4mm; Assume that the distance between adjacent vertical rods (21) is f, 125mm ≥ f ≥ 75mm; Assume that the number of vertical rods (21) is k, ; Assume that the angle between the diagonal rod (22) and the adjacent vertical rod (21) is θ, 30°≥θ≥70°.

16. The oil storage rudder wing with hybrid support of plate columns and trusses according to claim 11, characterized in that: Assume that among the multiple rows of side trusses (2), the side distance between the outermost side trusses (2) and the wing shell (5) along the width direction is d2, d2=(1~2)d1; and assume that among the multiple rows of side trusses (2), the spacing between two adjacent rows of side trusses (2) is d3, d3=(1~1.5)d2.

17. The oil storage rudder wing with hybrid support of plate columns and trusses according to claim 11, characterized in that: The plurality of intermediate oblique columns (4) are arranged in holes of the perforated oil tank (3), and the intermediate oblique columns (4) in a single hole are arranged in n rows and m columns, where n is an even number, and n≥2, and m≥2, wherein the rows are arranged along the length direction of the rudder wing, and the columns are arranged along the width direction of the rudder wing, and the intermediate oblique columns (4) in two adjacent rows are staggered with each other; and the inclination angle of the intermediate oblique columns (4) is α, and 40°≤α≤80°.

18. The oil storage rudder wing with mixed support of plate columns and trusses according to claim 11, characterized in that: The cross-sectional shapes of the plurality of intermediate inclined columns (4) are all circular or polygonal; assuming that the distance between the two farthest points of the cross-sectional area of ​​the intermediate inclined column (4) is f1, f1=(0.2%~1.2%)L.

19. The oil storage rudder wing with mixed support of plate columns and trusses according to claim 11, characterized in that: Assume that the maximum height of the rudder wing is H, the minimum thickness of the thermal insulation filling (6) is g, and g ≥ 0.18H.

20. The oil storage rudder wing with hybrid support of plate columns and trusses according to claim 11, characterized in that: The vertical thick plates (1), multiple rows of side trusses (2) and multiple intermediate oblique columns (4) are all made of the same material as the wing shell (5); the final service environment temperature of the oil storage rudder wing is T, 700°C ≥ T ≥ 350°C.

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