A columnar support with a suspended fuel tank wing / rudder wing with a stress coordination platform

Abstract

A columnar support with a suspended fuel tank wing / rudder with a stress coordination platform, the present invention belongs to the field of aerospace manufacturing technology. The present invention aims to solve the problems faced by existing fuel storage wing and rudder wing structures in terms of lightweight, high stress coordination, and strong thermal insulation requirements. The columnar support with a suspended fuel tank wing / rudder with a stress coordination platform is composed of an outer skin, a middle thermal insulation layer, a perforated suspended fuel tank, multiple vertical support columns, multiple side coordination columns, and multiple perforated coordination columns. The present invention is used for columnar support with a suspended fuel tank wing / rudder with a stress coordination platform.

Description

Technical Field

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

[0002] As the aerospace industry continues to demand ever-increasing speeds for hypersonic aircraft, these vehicles are also required to become thinner, lighter, and more compact. To address the severe fuel shortages associated with weight reduction, innovative designs are often employed that integrate fuel storage with the wing and rudder structures. This design effectively utilizes the space within the rudder, reducing overall weight while optimizing fuel distribution and improving vehicle stability and range. It is a key optimization and design direction for today's hypersonic aircraft.

[0003] Unlike traditional aircraft, the wings and rudders of hypersonic vehicles face even greater heat and enormous aerodynamic loads. These high temperatures create material thermal expansion, strength degradation, and heat transfer to the fuel tank, placing high demands on the structural strength and thermal insulation performance of the rudder and wing structures. Existing thermal insulation structures often utilize honeycomb panels, ribbed panels, and columnar structures. However, these structures all suffer from poor insulation, unavoidable thermal bridges, and excessive weight. There is still significant room for optimization and improvement in the lightweighting and thermal insulation performance of fuel-storage wings and rudders. Summary of the Invention

[0004] The present invention aims to solve the problems faced by existing oil storage wing and rudder wing structures in terms of light weight, high stress coordination and strong thermal insulation requirements, and further provides a columnar support and suspended oil tank wing / rudder wing with a stress coordination platform.

[0005] A columnar support wing / rudder wing with a suspension tank and a stress coordination platform, comprising an outer skin, a middle thermal insulation layer, a perforated suspension tank, a plurality of supporting vertical columns, a plurality of side coordination columns, and a plurality of perforated coordination columns; the outer skin is a sealed structure consisting of an upper outer skin, a lower outer skin, and a side outer skin;

[0006] The perforated suspension oil tank is provided with a plurality of holes in the middle; the gaps around the perforated suspension oil tank and between the upper and lower surfaces and the outer skin, as well as the holes of the perforated suspension oil tank are filled with a middle insulation layer, and a plurality of supporting vertical columns, a plurality of side coordination columns and a plurality of perforated coordination columns are all provided in the middle insulation layer;

[0007] The plurality of vertical support columns are distributed along the length of the wing / rudder wing between the connection end between the wing / rudder wing and the fuselage and the perforated suspension fuel tank, and are arranged in a row symmetrically along the centerline of the length of the wing / rudder wing; the vertical support columns are composed of a top vertical column stress coordination platform, a bottom vertical column stress coordination platform, and an intermediate vertical column, with the top vertical column stress coordination platform and the bottom vertical column stress coordination platform respectively provided at both ends of the intermediate vertical column, and the cross-sectional centers of the top vertical column stress coordination platform, the bottom vertical column stress coordination platform, and the intermediate vertical column coincide with each other;

[0008] The plurality of side coordination columns are distributed on both sides of the perforated suspension oil tank 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;

[0009] The plurality of perforated coordination columns are arranged in the holes of the perforated suspension oil tank and are arranged symmetrically along the center line of the wing / rudder wing length direction;

[0010] The plurality of supporting vertical columns are vertically connected to the upper outer skin and the lower outer skin, and the plurality of side coordination columns and the plurality of perforated coordination columns are connected to the upper outer skin and the lower outer skin at an inclined angle.

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

[0012] This invention provides a columnar support structure with a suspended fuel tank / rudder wing and a stress-coordinating platform. By drilling holes in the fuel tank, the connecting column passes through the holes. This effectively prevents thermal contact between the wing / rudder outer skin and the fuel tank, minimizing heat transfer and significantly improving the structure's thermal insulation capabilities.

[0013] This invention leverages the structure of a perforated fuel tank to divide different areas, allowing them to perform different functions. Perforations in critical stress-bearing areas avoid the fuel tank, effectively ensuring overall structural stability and significantly improving the stress-bearing capacity of the wings and rudders. Furthermore, a more rational distribution reduces the number of columns, further reducing the mass of the wings and rudders, achieving lightweighting while further improving their load-bearing capacity.

[0014] The present invention is used for a columnar support wing / rudder wing with a suspension oil tank and a stress coordination platform. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 This is a schematic structural diagram of a columnar support with a stress coordination platform and a suspended fuel tank wing / rudder wing according to the present invention;

[0016] Figure 2 Schematic diagram of the structure of the outer skin of the present invention;

[0017] Figure 3 This is an exploded view of the structure of the outer skin of the present invention;

[0018] Figure 4 This is a schematic structural diagram of the perforated suspension oil tank of the present invention;

[0019] Figure 5 This is a schematic structural diagram of a supporting vertical column of the present invention;

[0020] Figure 6 is a schematic cross-sectional view of a supporting vertical column of the present invention;

[0021] Figure 7 This is a schematic structural diagram of a perforated coordination column according to the present invention;

[0022] Figure 8 This is a schematic structural diagram of the side coordination column of the present invention;

[0023] Figure 9 is a schematic cross-sectional view of a side coordination column of the present invention;

[0024] Figure 10 Schematic diagram of the distribution of supporting vertical columns, side coordination columns and perforated coordination columns of the present invention;

[0025] Figure 11 Schematic diagram of the top view of the supporting vertical columns, side coordination columns and perforated coordination columns of the present invention;

[0026] Figure 12 The overall mechanical simulation results of the columnar support with a suspended oil tank rudder wing with a stress coordination platform in Example 1 are shown;

[0027] Figure 13 The results of mechanical simulation of the internal longitudinal section of the columnar support and suspended oil tank rudder wing with stress coordination platform in Example 1 are shown;

[0028] Figure 14 The overall thermal simulation results of the columnar support with a stress coordination platform and a suspended oil tank rudder wing in Example 1 are shown. DETAILED DESCRIPTION

[0029] 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.

[0030] Specific implementation method 1, combined with Figures 1 to 11 Specifically, this embodiment provides a columnar support wing / rudder wing with a stress coordination platform and a suspension tank. It consists of an outer skin 1, a middle thermal insulation layer 2, a perforated suspension tank 3, multiple vertical support columns 4, multiple side coordination columns 5, and multiple perforated coordination columns 6. The outer skin 1 is a sealed structure composed of an upper outer skin 11, a lower outer skin 12, and a side outer skin 13.

[0031] The perforated suspension oil tank 3 is provided with a plurality of holes in the middle; the gaps around the perforated suspension oil tank 3 and between the upper and lower surfaces and the outer skin 1, as well as the holes of the perforated suspension oil tank 3 are filled with the middle insulation layer 2, and the plurality of supporting vertical columns 4, the plurality of side coordination columns 5 and the plurality of perforated coordination columns 6 are all provided in the middle insulation layer 2;

[0032] The plurality of vertical support columns 4 are distributed along the length of the wing / rudder wing between the connection end between the wing / rudder wing and the fuselage and the perforated suspension oil tank 3, and are arranged in a row axially symmetrically along the centerline of the length of the wing / rudder wing. The vertical support columns 4 are composed of a top vertical column stress coordination platform 41, a bottom vertical column stress coordination platform 42, and an intermediate vertical column 43. The top vertical column stress coordination platform 41 and the bottom vertical column stress coordination platform 42 are respectively provided at the ends of the intermediate vertical column 43, and the cross-sectional centers of the top vertical column stress coordination platform 41, the bottom vertical column stress coordination platform 42, and the intermediate vertical column 43 coincide.

[0033] The plurality of side coordination columns 5 are distributed on both sides of the perforated suspension oil 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;

[0034] The plurality of perforated coordination columns 6 are arranged in the holes of the perforated suspension oil tank 3 and are arranged symmetrically along the center line of the wing / rudder wing length direction;

[0035] The plurality of supporting vertical columns 4 are vertically connected to the upper outer skin 11 and the lower outer skin 12 , and the plurality of side coordination columns 5 and the plurality of perforated coordination columns 6 are connected to the upper outer skin 11 and the lower outer skin 12 at an inclined angle.

[0036] The shape and dimensions of the outer skin 1 described in this embodiment are determined based on 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. The upper outer skin 11, lower outer skin 12, and side outer skins 13 are connected by welding to ensure sealing. The upper outer skin 11 is the top structure of the outer skin 1. Together with the lower outer skin 12, the bottom structure of the outer skin 1, it forms the primary component of the wing / rudder that rubs against air and bears stress and heat. The side outer skins 13 form the sides of the wing / rudder, providing connections to the fuselage and the streamlined structure of the flange.

[0037] The overall structure of the wing / rudder wing in this embodiment is, from top to bottom, an upper outer skin 11 , a middle thermal insulation layer 2 , a perforated suspension oil tank 3 , a middle thermal insulation layer 2 and a lower outer skin 1 .

[0038] The middle insulation layer 2 described in this embodiment is filled with aerogel, which is artificially stuffed between the outer skin 1 and the perforated suspension oil tank 3, removing all the space supporting the vertical columns 4, the side coordination columns 5 and the perforated coordination columns 6, thereby completely isolating the perforated suspension oil tank 3 and avoiding the formation of thermal bridges.

[0039] In this embodiment, the perforated suspension oil tank 3 has a large hole in the middle, which is convenient for the perforated coordination column 6 to pass through, and does not come into contact with any components except the middle insulation layer 2, and is in a state of floating up and down according to the force conditions of the wings / rudder wings.

[0040] In this embodiment, the vertical support columns 4 are a row of vertical columns, each comprising a top vertical column stress coordination platform 41 and a bottom vertical column stress coordination platform 42 on its upper and lower sides, which are used to alleviate stress concentration. The vertical support columns 4 are located closest to the fuselage connection and do not pass through the perforated suspension fuel tank 3, making them the largest load-bearing components.

[0041] In this embodiment, the side coordinating column 5 is an inclined column that does not penetrate the perforated suspension oil tank 3. When the side coordinating column 5 is tilted at an angle of 60° to 80°, it includes a top coordinating column stress coordination platform 51 and a bottom coordinating column stress coordination platform 52 on its upper and lower sides to alleviate stress concentration. Furthermore, when the side coordinating column 5 is tilted at an angle less than 60°, the upper and lower stress coordination platforms are not required.

[0042] In this embodiment, perforated coordination columns 6 connect the upper and lower outer skins 11 and 12 and are inserted between the intermediate insulation layer 2 and the perforated suspension oil tank 3 to maintain the structural strength of the rudder and wing. The perforated coordination columns 6 are inclined at a predetermined angle to the outer skins. Adjacent rows of coordination columns are staggered to form a cross, facilitating coordinated strain and deformation control.

[0043] In this embodiment, the supporting vertical columns 4 , the side coordination columns 5 and the perforated coordination columns 6 are connected to the outer skin 1 by welding.

[0044] The shape and size of the perforated suspension 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 shape and size of the outer skin. The material of the perforated suspension tank 3 is a lightweight aluminum-lithium alloy.

[0045] The beneficial effects of this embodiment are:

[0046] This embodiment provides a columnar support structure with a suspended fuel tank / rudder wing and a stress-coordinating platform. By drilling holes in the fuel tank, the connecting column passes through the holes. This effectively prevents thermal contact between the wing / rudder outer skin and the fuel tank, minimizing heat transfer and significantly improving the structure's thermal insulation capabilities.

[0047] This implementation leverages the perforated fuel tank structure to compartmentalize different areas, allowing them to fulfill distinct functions. Perforations in critical stress-bearing areas bypass the fuel tank, effectively ensuring overall structural stability and significantly improving the stress-bearing capacity of the wings and rudders. Furthermore, a more rational distribution reduces the number of columns, further reducing the weight of the wings and rudders, achieving both lightweighting and increased load-bearing capacity.

[0048] Specific embodiment 2: This embodiment differs from specific embodiment 1 in that: the maximum height of the wing / rudder wing is H, the thickness of the thinnest position of the middle insulation layer 2 is b, and b≥0.18H. Other aspects are the same as specific embodiment 1.

[0049] Specific embodiment 3: This embodiment differs from specific embodiment 1 or 2 in that the distance between the edge of the hole of the perforated suspension oil tank 3 and the adjacent perforated coordination column 6 is c, c ≥ 10 mm. Other aspects are the same as specific embodiment 1 or 2.

[0050] Specific embodiment 4: This embodiment differs from any one of specific embodiments 1 to 3 in that the cross-sectional shape of the middle vertical column 43 is circular, square, or polygonal; the cross-sectional shapes of the top vertical column stress coordination platform 41 and the bottom vertical column stress coordination platform 42 are circular; and the cross-sectional areas of the top vertical column stress coordination platform 41 and the bottom vertical column stress coordination platform 42 are 4 to 6 times the cross-sectional area of ​​the middle vertical column 43. Other aspects are the same as specific embodiments 1 to 3.

[0051] Specific embodiment 5: This embodiment differs from the first embodiment of specific embodiments 1 to 4 in that: assuming the distance between the two farthest points of the cross section of the intermediate vertical column 43 is d1, assuming the length of the wing / rudder is L, d1 = (0.01-0.02) L; assuming the distance between the intermediate vertical column 43 and the side outer skin 13 where the wing / rudder connects to the fuselage is d2, assuming the width of the wing / rudder is D, d2 = (0.1-0.25) D; assuming the center distance between adjacent intermediate vertical columns 43 is d3, d3 = (5-15) d1. Other aspects are the same as specific embodiments 1 to 4.

[0052] Specific embodiment 6: This embodiment differs from any one of specific embodiments 1 to 5 in that: multiple perforated coordination columns 6 are disposed within the holes of the perforated suspension oil tank 3. Within each hole, the perforated coordination columns 6 are arranged in n rows x 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 perforated coordination columns 6 in two adjacent rows are staggered. The perforated coordination columns 6 have an inclination angle of 40° to 80°. The cross-section of the perforated coordination columns 6 is circular, square, or polygonal. The distance between the two farthest points of the cross-section of the perforated coordination column 6 is f1, and f1 = (0.2 to 0.6) d1. Other aspects are the same as specific embodiments 1 to 5.

[0053] Specific embodiment 7: This embodiment differs from Embodiments 1 to 6 in that the side coordinating posts 5 and perforated coordinating posts 6 are arranged in the same number of rows, the side coordinating posts 5 and perforated coordinating posts 6 in the same row have the same inclination angle, and the side coordinating posts 5 are arranged along the length of the perforated coordinating posts 6 along the wing / rudder. Other aspects are the same as Embodiments 1 to 6.

[0054] Specific Embodiment 8: This embodiment differs from any one of Specific Embodiments 1 to 7 in that, when the inclination angle of the side coordinating column 5 is 60° to 80°, the side coordinating column 5 comprises a top coordinating column stress coordination platform 51, a bottom coordinating column stress coordination platform 52, and an intermediate inclined column 53. The top coordinating column stress coordination platform 51 and the bottom coordinating column stress coordination platform 52 are respectively provided at both ends of the intermediate inclined column 53. The center distance between the contact surface of the top coordinating column stress coordination platform 51 or the bottom coordinating column stress coordination platform 52 and the intermediate inclined column 53 is d4, where d4 = (0.1-1)d1. The cross-sectional shape and cross-sectional dimensions of the top coordinating column stress coordination platform 51, the bottom coordinating column stress coordination platform 52, and the intermediate inclined column 53 are the same as those of the top vertical column stress coordination platform 41, the bottom vertical column stress coordination platform 42, and the intermediate vertical column 43, respectively. Other aspects are the same as Specific Embodiments 1 to 7.

[0055] Specific embodiment 9: This embodiment differs from specific embodiments 1 to 8 in that when the inclination angle of the side coordinating column 5 is 40° to 60°, the side coordinating column 5 is a middle oblique column 53; the cross-sectional shape and cross-sectional dimensions of the middle oblique column 53 are the same as those of the middle vertical column 43. Other aspects are the same as specific embodiments 1 to 8.

[0056] Specific Embodiment 10: This embodiment differs from any one of Specific Embodiments 1 to 9 in that the multiple vertical support columns 4, multiple side coordination columns 5, and multiple perforated coordination columns 6 are all made of the same material as the outer skin 1. The final service environment temperature of the columnar support with a suspension tank and wing / rudder with a stress coordination platform is T, 750°C ≥ T ≥ 400°C. Other aspects are the same as Specific Embodiments 1 to 9.

[0057] The following examples are used to verify the beneficial effects of the present invention:

[0058] 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:

[0059] A columnar support rudder wing with a suspension oil tank and a stress coordination platform, comprising an outer skin 1, a middle thermal insulation layer 2, a perforated suspension oil tank 3, a plurality of supporting vertical columns 4, a plurality of side coordination columns 5, and a plurality of perforated coordination columns 6; the outer skin 1 is a sealed structure consisting of an upper outer skin 11, a lower outer skin 12, and a side outer skin 13;

[0060] Three rectangular holes are arranged in parallel in the middle of the perforated suspension oil tank 3; the gaps around the perforated suspension oil tank 3 and between the upper and lower surfaces and the outer skin 1, as well as the holes of the perforated suspension oil tank 3, are filled with the middle insulation layer 2, and multiple supporting vertical columns 4, multiple side coordination columns 5 and multiple perforated coordination columns 6 are all arranged in the middle insulation layer 2;

[0061] The plurality of vertical support columns 4 are distributed along the length of the rudder wing between the connection end of the rudder wing and the fuselage and the perforated suspension oil tank 3, and are arranged in a row axially symmetrically along the centerline of the length of the rudder wing; the vertical support columns 4 are composed of a top vertical column stress coordination platform 41, a bottom vertical column stress coordination platform 42, and an intermediate vertical column 43. The top vertical column stress coordination platform 41 and the bottom vertical column stress coordination platform 42 are respectively provided at both ends of the intermediate vertical column 43, and the cross-sectional centers of the top vertical column stress coordination platform 41, the bottom vertical column stress coordination platform 42, and the intermediate vertical column 43 coincide.

[0062] The plurality of side coordination columns 5 are distributed on both sides of the perforated suspension 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;

[0063] The plurality of perforated coordination columns 6 are arranged in the holes of the perforated suspension oil tank 3 and are arranged symmetrically along the center line of the rudder wing length direction;

[0064] The plurality of supporting vertical columns 4 are vertically connected to the upper outer skin 11 and the lower outer skin 12 , and the plurality of side coordination columns 5 and the plurality of perforated coordination columns 6 are connected to the upper outer skin 11 and the lower outer skin 12 at an inclined angle.

[0065] Assume that the maximum height of the rudder wing is H, H = 100 mm, and the thickness of the thinnest position of the middle insulation layer 2 is b, b = 18 mm;

[0066] The distance between the edge of the hole of the perforated suspension oil tank 3 and the adjacent perforated coordination column 6 is c, c = 15 mm;

[0067] The cross-sectional shape of the middle vertical column 43 is circular; the cross-sectional shape of the top vertical column stress coordination platform 41 and the bottom vertical column stress coordination platform 42 are also circular; the cross-sectional area of ​​the top vertical column stress coordination platform 41 and the bottom vertical column stress coordination platform 42 is four times the cross-sectional area of ​​the middle vertical column 43;

[0068] Assume that the distance between the two farthest points of the cross section of the intermediate vertical column 43 is d1, the length of the rudder wing is L, L = 1000mm, d1 = 10mm; the distance between the intermediate vertical column 43 and the side outer skin 13 where the rudder wing connects to the fuselage is d2, the width of the rudder wing is D, D = 600mm, d2 = 80mm; the center distance between adjacent intermediate vertical columns 43 is d3, d3 = 70mm;

[0069] Multiple perforated coordination posts 6 are disposed within the holes of the perforated suspension oil tank 3. Within each hole, the perforated coordination posts 6 are arranged in n rows x m columns, where n is an even number and n=2. The rows are arranged along the length of the rudder wing, and the columns are arranged along the width of the rudder wing. The perforated coordination posts 6 in two adjacent rows are staggered. Starting from the end closest to the wing connection, the inclination angles of the perforated coordination posts 6 within each hole are 78.7°, 63.4°, and 51.3°, respectively. m is 12, 8, and 8, respectively. The cross-section of the perforated coordination posts 6 is circular. The distance between the two farthest points of the cross-section of the perforated coordination posts 6 is f1, and f1=4 mm.

[0070] The side coordination columns 5 and the perforated coordination columns 6 have the same number of rows, the side coordination columns 5 and the perforated coordination columns 6 in the same row have the same inclination angle, and the side coordination columns 5 are arranged along the length direction of the perforated coordination columns 6 along the rudder wing;

[0071] When the inclination angle of the side coordinating column 5 is 78.7° or 63.4°, the side coordinating column 5 is composed of a top coordinating column stress coordination platform 51, a bottom coordinating column stress coordination platform 52, and an intermediate oblique column 53. The top coordinating column stress coordination platform 51 and the bottom coordinating column stress coordination platform 52 are respectively provided at both ends of the intermediate oblique column 53. The center distance between the contact surface of the top coordinating column stress coordination platform 51 or the bottom coordinating column stress coordination platform 52 and the intermediate oblique column 53 is d4, where d4 = 10 mm. The cross-sectional shape and cross-sectional size of the top coordinating column stress coordination platform 51, the bottom coordinating column stress coordination platform 52, and the intermediate oblique column 53 are respectively the same as those of the top vertical column stress coordination platform 41, the bottom vertical column stress coordination platform 42, and the intermediate vertical column 43.

[0072] When the inclination angle of the side coordination column 5 is 51.3°, the side coordination column 5 is a middle oblique column 53; the cross-sectional shape and cross-sectional size of the middle oblique column 53 are the same as those of the middle vertical column 43;

[0073] The material of the plurality of supporting vertical columns 4, the plurality of side coordination columns 5, the plurality of perforated coordination columns 6 and the outer skin 1 is Ti2AlNb;

[0074] The ultimate service environment temperature of the columnar support and suspended oil tank rudder wing with stress coordination platform is T, T=650℃.

[0075] The material of the perforated suspension oil tank 3 is AlLi alloy, and the oil tank can be loaded with fuel; the middle thermal insulation layer 2 is SiO2 aerogel.

[0076] Figure 12 The overall mechanical simulation results of the columnar support with a suspended oil tank rudder wing with a stress coordination platform in Example 1 are shown.

[0077] Figure 13 The following are the mechanical simulation results for the internal longitudinal section of a columnar support with a suspended fuel tank rudder wing and a stress coordination platform in Example 1. The results clearly show that under normal flight stress, the maximum internal stress of this structure is 202.68 MPa, meeting the service requirements of most high-temperature, high-strength materials and offering a wider range of applications.

[0078] Figure 14 The overall thermal simulation results for the columnar support with a stress-coordinating platform and a suspended fuel tank rudder in Example 1 are shown. The results show that even at an external temperature of 650°C, this rudder structure can still maintain a safe internal fuel tank temperature.

[0079] Example 1: The density of the columnar support with a stress coordination platform and the suspended oil tank rudder wing is only 1.22g / mm 3 , further reducing the mass of the rudder.

Claims

1. A columnar support with a suspended fuel tank wing / rudder wing with a stress coordination platform, characterized in that: It consists of an outer skin (1), a middle thermal insulation layer (2), a perforated suspension oil tank (3), a plurality of supporting vertical columns (4), a plurality of side coordination columns (5) and a plurality of perforated coordination columns (6); the outer skin (1) is a sealed structure consisting of an upper outer skin (11), a lower outer skin (12) and a side outer skin (13); The perforated suspension oil tank (3) is provided with a plurality of holes in the middle; the gaps around the perforated suspension oil tank (3) and between the upper and lower surfaces and the outer skin (1), and the holes of the perforated suspension oil tank (3) are all filled with the middle insulation layer (2), and the plurality of supporting vertical columns (4), the plurality of side coordination columns (5) and the plurality of perforated coordination columns (6) are all provided in the middle insulation layer (2); The plurality of supporting vertical columns (4) are distributed along the length direction of the wing / rudder wing between the connection end of the wing / rudder wing and the fuselage and the perforated suspension oil tank (3), and are arranged in a row along the center line of the length direction of the wing / rudder wing in an axisymmetric manner; the supporting vertical columns (4) are composed of a top vertical column stress coordination platform (41), a bottom vertical column stress coordination platform (42) and an intermediate vertical column (43), and the top vertical column stress coordination platform (41) and the bottom vertical column stress coordination platform (42) are respectively provided at both ends of the intermediate vertical column (43), and the cross-sectional centers of the top vertical column stress coordination platform (41), the bottom vertical column stress coordination platform (42) and the intermediate vertical column (43) coincide with each other; The plurality of side coordination columns (5) are distributed on both sides of the perforated suspension oil 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; The plurality of perforated coordination columns (6) are arranged in the holes of the perforated suspension oil tank (3) and are arranged symmetrically along the center line of the wing / rudder wing length direction; The plurality of supporting vertical columns (4) are vertically connected to the upper outer skin (11) and the lower outer skin (12), and the plurality of side coordination columns (5) and the plurality of perforated coordination columns (6) are connected to the upper outer skin (11) and the lower outer skin (12) at an inclined angle.

2. A columnar support with a suspended fuel tank wing / rudder wing with a stress coordination platform according to claim 1, characterized in that: Assume that the maximum height of the wing / rudder wing is H, the thickness of the thinnest position of the middle thermal insulation layer (2) is b, and b≥0.18H.

3. A columnar support with a suspended fuel tank wing / rudder wing with a stress coordination platform according to claim 1, characterized in that: The distance between the edge of the hole of the perforated suspension oil tank (3) and the adjacent perforated coordination column (6) is c, and c is ≥ 10 mm.

4. A columnar support with a suspended fuel tank wing / rudder wing with a stress coordination platform according to claim 1, characterized in that: The cross-sectional shape of the middle vertical column (43) is circular, square or polygonal; the cross-sectional shape of the top vertical column stress coordination platform (41) and the bottom vertical column stress coordination platform (42) is circular; the cross-sectional area of ​​the top vertical column stress coordination platform (41) and the bottom vertical column stress coordination platform (42) is 4 to 6 times the cross-sectional area of ​​the middle vertical column (43).

5. A columnar support with a suspended fuel tank wing / rudder wing with a stress coordination platform according to claim 1, characterized in that: Assume that the distance between the two farthest points of the cross section of the intermediate vertical column (43) is d1, and the length of the wing / rudder wing is L, d1=(0.01~0.02)L; Assume that the length of the intermediate vertical column (43) from the side outer skin (13) at the connection end of the wing / rudder wing and the fuselage is d2, and the width of the wing / rudder wing is D, d2=(0.1~0.25)D; Assume that the center distance between adjacent intermediate vertical columns (43) is d3, d3=(5~15)d1.

6. A columnar support with a suspended fuel tank wing / rudder wing with a stress coordination platform according to claim 5, characterized in that: A plurality of perforated coordination columns (6) are arranged in holes of a perforated suspension oil tank (3), and the perforated coordination columns (6) in a single hole are arranged in n rows and m columns, where 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 perforated coordination columns (6) in two adjacent rows are staggered. The inclination angle of the perforated coordination columns (6) is 40°~80°; the cross section of the perforated coordination columns (6) is circular, square or polygonal; and the distance between the two farthest points of the cross section of the perforated coordination columns (6) is f1, and f1=(0.2~0.6)d1.

7. A columnar support with a suspended fuel tank wing / rudder wing with a stress coordination platform according to claim 6, characterized in that: The side coordination columns (5) and the perforated coordination columns (6) have the same number of rows, the side coordination columns (5) and the perforated coordination columns (6) in the same row have the same inclination angle, and the side coordination columns (5) are arranged on the perforated coordination columns (6) along the length direction of the wing / rudder wing.

8. A columnar support with a suspended fuel tank wing / rudder wing with a stress coordination platform according to claim 6, characterized in that: When the inclination angle of the side coordination column (5) is 60°~80°, the side coordination column (5) is composed of a top coordination column stress coordination platform (51), a bottom coordination column stress coordination platform (52) and an intermediate inclined column (53), and a top coordination column stress coordination platform (51) and a bottom coordination column stress coordination platform (52) are respectively provided at both ends of the intermediate inclined column (53), and the center distance between the contact surface of the top coordination column stress coordination platform (51) or the bottom coordination column stress coordination platform (52) and the intermediate inclined column (53) is d4, d4=(0.1~1)d1; the cross-sectional shape and cross-sectional size of the top coordination column stress coordination platform (51), the bottom coordination column stress coordination platform (52) and the intermediate inclined column (53) are respectively the same as those of the top vertical column stress coordination platform (41), the bottom vertical column stress coordination platform (42) and the intermediate vertical column (43).

9. A columnar support with a suspended fuel tank wing / rudder wing with a stress coordination platform according to claim 6, characterized in that: When the inclination angle of the side coordination column (5) is 40° to 60°, the side coordination column (5) is an intermediate oblique column (53); the cross-sectional shape and cross-sectional dimensions of the intermediate oblique column (53) are the same as those of the intermediate vertical column (43).

10. A columnar support with a suspended fuel tank wing / rudder wing with a stress coordination platform according to claim 1, characterized in that: The materials of the plurality of supporting vertical columns (4), the plurality of side coordination columns (5) and the plurality of perforated coordination columns (6) are all the same as that of the outer skin (1); The ultimate service environment temperature of the columnar support equipped with suspension fuel tank wing / rudder wing with stress coordination platform is T, 750℃≥T≥400℃.

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