Oil storage wing / rudder wing supported by plate columns and trussed beams in mixed mode

Abstract

The invention discloses an oil storage wing / rudder wing supported by plate columns and trussed beams in a mixed mode, and belongs to the technical field of aerospace manufacturing. The invention aims to solve the problems that the existing oil storage wing and rudder wing are insufficient in high-stress bearing capacity and poor in heat insulation capacity at high temperature in a complex aerospace environment. An oil storage wing / rudder wing supported by plate columns and trussed beams in a mixed mode is composed of a vertical thick plate, a plurality of columns of side trussed beams, a perforated oil tank, a plurality of middle inclined columns, a wing shell and heat insulation filler. The invention is used for the oil storage wing / rudder wing supported by the plate column and the trussed beam in a mixed manner.

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 aircraft have gradually become an important research object in the modern aerospace field. However, hypersonic aircraft face extreme aerodynamic loads, thermal environments, and structural stress challenges. Wings and rudders are important control components of hypersonic aircraft, mainly used to adjust flight attitude and heading. At the same time, due to the extreme lightweight and high fuel consumption requirements of aircraft, oil storage wings and rudders are often required to maximize the use of space in the aircraft. Therefore, the structural design and optimization of oil storage wings and rudders becomes particularly critical.

[0003] Existing oil storage wings and rudder wings have honeycomb structures, columnar skeleton connection structures and multi-layer composite plate structures. These structures all have their own defects. The honeycomb structure is too heavy, the columnar skeleton connection structure has weak stress bearing capacity, and the multi-layer composite plate structure has poor thermal insulation capacity. Therefore, there is an urgent need for a rudder wing structure that can simultaneously meet high bearing capacity and strong thermal insulation capacity to cope with the more complex service environment requirements 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 provide an oil storage wing / rudder wing with hybrid support of plate columns and trusses.

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

[0006] A plurality of holes are arranged in the middle of the perforated fuel tank; the gaps around the perforated fuel tank and between the upper and lower surfaces and the wing shell, and the holes of the perforated fuel tank are filled with heat insulation filling, and the vertical thick plates, multiple rows of side trusses and multiple middle oblique columns are all arranged in the heat insulation filling;

[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 between 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, 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 between 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 axis of the length direction of the wing / rudder wing;

[0008] The multiple rows of side girder beams 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 axis of the length direction of the wing / rudder wing; each row of side girder beams is composed of multiple vertical bars and multiple oblique bars; multiple vertical grooves are arranged on the long thick plate, and the vertical bars at one end of each row of side girder beams are embedded in the vertical groove 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 inclined columns are arranged in the holes of the perforated fuel tank and are arranged symmetrically along the center line 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] The present invention provides a structural design of oil storage wing and rudder wing with mixed support of plate column and truss beam, which combines the existing plate reinforcement structure and multi-column structure to form a new type of wing and rudder wing structure. It uses thick plates at key positions with large stress to retain the strong stress bearing capacity of the plate reinforcement structure, and uses multi-column and truss beam structures in areas with large deformation to greatly reduce the density. At the same time, it has a certain deformation coordination ability and improves the anti-heat insulation performance of the structure, realizing the multi-functional optimization of the wing and rudder wing.

[0013] The present invention introduces a truss structure into the bridge. On the one hand, the truss and the thick plate 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 invention is used for an oil storage wing / rudder wing supported by a combination of a plate column and a truss beam. BRIEF DESCRIPTION OF THE DRAWINGS

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

[0016] Figure 2 It is a schematic diagram of the positions of the vertical thick plates, the side truss connections and the 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 It is a structural schematic diagram of the middle inclined column of the present invention;

[0019] Figure 5 It 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 column and truss beam in Example 1;

[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 modes listed below, but also includes any combination of the specific implementation modes.

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

[0024] 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 filled with heat insulation filling 6, and the vertical thick plate 1, multiple rows of side trusses 2 and multiple middle oblique columns 4 are all arranged in the heat insulation filling 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 between 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, 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 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 girder beams 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 center line of the length direction of the wing / rudder wing; each row of side girder beams 2 is composed of multiple vertical rods 21 and multiple oblique rods 22; multiple vertical grooves are arranged on the long thick plate 11, and the vertical rods 21 at one end of each row of side girder beams 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 / rudder wing;

[0027] 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 length direction of the wing / rudder wing;

[0028] 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 oblique rod 22 and the middle oblique column 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 size of the wing shell 5 described in this embodiment are determined according to the specific requirements of the aircraft, and its material is a high-temperature high-strength alloy to ensure the stress bearing capacity in a high temperature environment. It is connected to the vertical thick plate 1, the side truss 2 and the middle oblique column 4 by welding to ensure the integrity and sealing of the structure.

[0031] In this embodiment, the vertical thick plate 1, the side truss beam 2 and the middle oblique column 4 are connected together with the upper and lower panels of the wing shell 5, so that the wing and the rudder wing form a whole. The perforated oil tank 3 and the wing shell 5 are both sealed structures, and the gap between the two is filled with a heat insulation filler 6 to isolate the perforated oil tank and achieve a heat insulation effect.

[0032] In this embodiment, the vertical thick plate 1, the side truss beam 2 and the middle oblique column 4 are the main components for bearing stress of the wing and the rudder wing and maintaining the stability of the overall structure. The vertical thick plate 1 is a long thick plate with multiple sections perpendicular to the wing shell 5, which includes a long thick plate 11 and a short thick plate 12. The short thick plate 12 is mainly used to match the shape of the fuel tank to maximize the ability of the structure to bear stress.

[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 passing through the perforated oil tank 3, and they are inclined at a certain angle to the upper and lower panels of the wing shell 5. The middle oblique columns 4 of two adjacent rows are staggered to form a cross, which is convenient for coordinated deformation control of strain.

[0035] The main material of the heat insulating filler 6 in this embodiment is aerogel, which is filled in all gaps in an artificial manner 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 of oil storage wing and rudder wing with mixed support of plate column and truss beam, which combines the existing plate reinforcement structure and multi-column structure to form a new type of wing and rudder wing structure. It uses thick plates at key locations with large stress to retain the strong stress bearing capacity of the plate reinforcement structure, and uses multi-column and truss beam structures in areas with large deformation to greatly reduce the density. At the same time, it has a certain deformation coordination ability and improves the anti-heat insulation performance of the structure, realizing the multi-functional optimization of the wing and rudder wing.

[0039] This implementation method introduces a truss structure into the bridge. On the one hand, the truss and the thick plate form a cross joint, 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 a greater stress bearing capacity and strain coordination ability, and also achieves weight reduction, which is a very creative breakthrough.

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

[0041] Specific embodiment 3: This embodiment is different from specific embodiment 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 is parallel to the adjacent side of the perforated oil tank 3. Others are the same as specific embodiment 1 or 2.

[0042] Specific embodiment 4: This embodiment is different 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 symmetrically arranged along the vertical rod 21. Other aspects are the same as specific embodiments 1 to 3.

[0043] Specific implementation mode 5: This implementation mode is different from the specific implementation modes 1 to 4 in that: the width of the vertical rod 21 and the oblique rod 22 is 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°. The rest is the same as the first to fourth embodiments.

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

[0045] Specific embodiment 6: This embodiment is different from specific embodiments 1 to 5 in 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 to 2) d1; among the multiple rows of side trusses 2, the distance between two adjacent rows of side trusses 2 is d3, d3 = (1 to 1.5) d2. Other aspects are the same as specific embodiments 1 to 5.

[0046] Specific embodiment 7: This embodiment is different from any one of specific embodiments 1 to 6 in that: the plurality of intermediate oblique columns 4 are arranged in the holes of the perforated oil tank 3, and the intermediate oblique columns 4 in a single hole are arranged in n rows × m columns, n is an even number, and n≥2, m≥2, wherein the rows are arranged along the length direction of the wing / rudder wing, and the columns are arranged along the width direction of the wing / rudder wing, and the intermediate oblique columns 4 in two adjacent rows are staggered; the inclination angle of the intermediate oblique columns 4 is α, 40°≤α≤80°. The rest is the same as specific embodiments 1 to 6.

[0047] Specific embodiment 8: This embodiment is different from specific embodiments 1 to 7 in that the cross-sections of the plurality of intermediate inclined columns 4 are all circular, square or polygonal; the distance between the two farthest points of the cross-section of the intermediate inclined column 4 is f1, f1 = (0.2% to 1.2%) L. The rest is the same as specific embodiments 1 to 7.

[0048] Specific embodiment 9: This embodiment is different 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≥0.18H. Other aspects are the same as specific embodiments 1 to 8.

[0049] Specific embodiment 10: This embodiment is different from specific embodiments 1 to 9 in that: the vertical thick plate 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 / rudder wing is T, 700℃≥T≥350℃. Others 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] Example 1, taking a large aircraft rudder wing component as an example, the length is 1000mm, the width is 600mm, and the maximum height is 100mm:

[0052] An oil storage rudder wing with mixed support of plate columns and trusses, which is composed of a vertical thick plate 1, four rows of side trusses 2, a perforated oil tank 3, a plurality of middle oblique 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 oil tank 3 along the length direction of the rudder wing; the gaps around the perforated oil tank 3 and between the upper and lower surfaces and the wing shell 5, and the holes of the perforated oil tank 3 are filled with heat insulation filling 6, and the vertical thick plate 1, the four rows of side trusses 2 and the multiple middle oblique columns 4 are all arranged in the heat 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 connecting end of the rudder wing and the fuselage and the perforated oil 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=1000mm, D=600mm, l=L, d1=60mm; the three short thick plates 12 are distributed between the long thick plate 11 and the perforated oil 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 girder beams 2 are distributed on both sides of the perforated oil 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 girder beams 2 is composed of a plurality of vertical rods 21 and a plurality of diagonal rods 22; a plurality of vertical grooves are arranged on the long thick plate 11, and the vertical rods 21 at one end of each row of side girder beams 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;

[0056] 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;

[0057] 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 oblique rod 22 and the middle oblique column 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 connecting end of the rudder wing and the fuselage is 80 mm, and the side surfaces adjacent to the short thick plate 12 and the perforated fuel tank 3 are parallel;

[0060] 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 arranged symmetrically along the vertical bars 21;

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

[0062] Assume that among the four rows of side girders 2, the side distance between the outermost side girders 2 and the wing shell 5 along the width direction is d2, d2 = 80 mm; Assume that among the four rows of side girders 2, the distance between two adjacent rows of side girders 2 is d3, d3 = 100 mm;

[0063] The plurality of intermediate oblique columns 4 are arranged in the holes of the perforated oil tank 3. The intermediate oblique columns 4 in a single hole are arranged in n rows × m columns, n is an even number, and n=2, wherein the rows are arranged along the length direction of the rudder wing, 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; assuming that the inclination angle of the intermediate oblique column 4 is α, the inclination angle α of the intermediate oblique column 4 in each hole starting from the end close to the wing connection is 75°, 60° and 45°, respectively, and m is 12 columns, 8 columns and 8 columns, respectively;

[0064] The cross-sectional shapes of the plurality of intermediate inclined columns 4 are all circular; assuming that the distance between the two farthest points of the cross-sectional area of ​​a single intermediate inclined 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 heat insulation filling 6 is g, g = 18 mm;

[0066] The materials of the vertical thick plate 1, the four rows of side trusses 2, the multiple middle oblique columns 4 and the wing shell 5 are all Ti 2 AlNb;

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

[0068] The material of the perforated fuel tank 3 is AlLi alloy, and the fuel tank can be loaded with fuel; the thermal insulation filler 6 is SiO 2 Aerogel.

[0069] 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; it can be clearly seen from the results that under normal flight stress, the maximum internal stress of this structure is 148.52MPa, and there is no obvious stress concentration point, which meets the service environment of high-temperature and high-strength materials of 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 are shown; it can be seen from the results that when the external temperature environment is 520°C, the rudder wing of this structure can still ensure that the temperature of the internal oil tank is not higher than 90°C for a long time.

[0071] Example 1 The density of the oil storage rudder wing supported by the plate column and the truss beam is 1.35g / mm 3 , slightly reducing the mass of the rudder wing.

Claims

1. An oil storage wing / rudder wing supported by a combination of plate columns and trusses, characterized in that It consists of a vertical thick plate (1), multiple rows of side girders (2), a perforated fuel tank (3), multiple intermediate inclined columns (4), a wing shell (5) and a heat insulation filling (6); The perforated oil tank (3) is provided with a plurality of holes in the middle; the gaps around the perforated oil tank (3) and between the upper and lower surfaces and the wing shell (5), and the holes of the perforated oil tank (3) are all filled with heat insulation 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 insulation 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 connection end between 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, 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 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; The multiple rows of side girder beams (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 center line of the length direction of the wing / rudder wing; each row of side girder beams (2) is composed of multiple vertical rods (21) and multiple oblique rods (22); multiple vertical grooves are arranged on the long thick plate (11), and the vertical rods (21) at one end of each row of side girder beams (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 / 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 length direction of the wing / rudder wing; 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 / rudder wing supported by a combination 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 / rudder wing supported by a combination 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 adjacent sides of the short thick plate (12) and the perforated oil tank (3) are parallel.

4. The oil storage wing / rudder wing supported by a combination 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 / rudder wing supported by a combination of plate columns and trusses according to claim 1, characterized in that The widths of the vertical rods (21) and the diagonal rods (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, Assuming that the angle between the oblique rod (22) and the adjacent vertical rod (21) is θ, 30°≥θ≥70°.

6. The oil storage wing / rudder wing supported by a combination of plate columns and trusses according to claim 1, characterized in that In the plurality of rows of side girders (2), the side distance between the outermost side girders (2) and the wing shell (5) along the width direction is d2, d2=(1-2)d1; in the plurality of rows of side girders (2), the distance between two adjacent rows of side girders (2) is d3, d3=(1-1.5)d2.

7. The oil storage wing / rudder wing supported by a combination of plate columns and trusses according to claim 1, characterized in that The plurality of intermediate inclined columns (4) are arranged in holes of the perforated oil tank (3), and the intermediate inclined columns (4) in a single hole are arranged in n rows×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 / rudder wing, and the columns are arranged along the width direction of the wing / rudder wing, and the intermediate inclined columns (4) in two adjacent rows are staggered and distributed with each other; the inclination angle of the intermediate inclined columns (4) is α, and 40°≤α≤80°.

8. The oil storage wing / rudder wing supported by a combination 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, square 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% to 1.2%) L.

9. The oil storage wing / rudder wing supported by a combination of plate columns and trusses according to claim 1, characterized in that The maximum height of the wing / rudder wing is H, and the minimum thickness of the insulation filling (6) is g, g ≥ 0.18H.

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

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