Columnar supporting wing / rudder wing with stress coordination table and suspension oil tank

Abstract

The invention discloses a columnar supporting wing / rudder wing with a stress coordination table and a suspension oil tank, and belongs to the technical field of aerospace manufacturing. The invention aims to solve the problems of light weight, high stress coordination and strong heat insulation requirements of the existing oil storage wing and rudder wing structure. The invention discloses a columnar supporting wing / rudder wing with a stress coordination table and a suspension oil tank. The columnar supporting wing / rudder wing is composed of an outer skin, a middle heat insulation layer, the perforated suspension oil tank, a plurality of supporting vertical columns, a plurality of side edge coordination columns and a plurality of perforated coordination columns. The method is used for the columnar supporting wing / rudder wing with the stress coordination table and the suspension oil tank.

Description

Technical Field

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

[0002] As the demand for the flight speed of hypersonic aircraft in the aerospace field increases, the hypersonic aircraft manufactured also need to become lighter and more compact. In order to solve the problem of severe lack of fuel storage during the weight loss of aircraft, an innovative design that integrates fuel storage function with wing and rudder wing structure function is often adopted. This design can effectively utilize the internal space of the rudder wing, reduce the overall weight, optimize the fuel distribution, and improve the stability and range of the aircraft. It is the main optimization and design direction of today's hypersonic aircraft.

[0003] Unlike traditional aircraft, the wings and rudders of hypersonic aircraft will face greater heat environments and huge aerodynamic loads. These high-temperature thermal environments bring about problems such as material thermal expansion, strength attenuation, and heat transfer to the fuel tank, which puts higher demands on the structural strength and thermal insulation performance of the rudder and wing structures. Existing thermal insulation structures often use honeycomb panel insulation structures, plate rib insulation structures, columnar insulation structures, etc., but these thermal insulation structures have the limitations of poor thermal insulation capabilities, unavoidable thermal bridges, and excessive weight. There is still a lot of room for optimization and improvement in the lightweight and anti-thermal insulation performance of oil storage wings and rudder wings. Summary of the invention

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

[0005] A columnar support with a suspension tank wing / rudder wing with a stress coordination platform, which is composed of 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 sealing structure composed of an upper outer skin, a lower outer skin and a side outer skin;

[0006] A plurality of holes are arranged in the middle of the perforated suspension oil tank; the gaps around the perforated suspension oil tank and between the upper and lower surfaces and the outer skin, and 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 arranged in the middle insulation layer;

[0007] The plurality of supporting vertical columns are distributed along the length direction of the wing / rudder wing between the connecting end of the wing / rudder wing and the fuselage and the perforated suspension oil tank, and are arranged in a row along the axis of the center line of the length direction of the wing / rudder wing in a symmetrical manner; the supporting vertical columns are composed of a top vertical column stress coordination platform, a bottom vertical column stress coordination platform and an intermediate vertical column, and the top vertical column stress coordination platform and the bottom vertical column stress coordination platform are respectively arranged 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;

[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] The present invention provides a columnar support with a suspended fuel tank / rudder wing structure design with a stress coordination platform, and the connected column is passed through the fuel tank by digging a hole. The thermal connection between the wing / rudder wing outer skin and the fuel tank can be effectively avoided, the heat propagation is blocked to the greatest extent, and the heat insulation ability of the structure is greatly improved.

[0013] The present invention relies on the structure of the perforated fuel tank to divide different areas to achieve different functions. The key stress-bearing area can avoid the fuel tank through perforations, thereby effectively ensuring the stability of the overall structure and greatly improving the stress bearing capacity of the wing / rudder wing. At the same time, a more reasonable distribution reduces the number of columns, further reduces the mass of the wing and rudder wing, and further improves the load resistance of the wing and rudder wing while achieving lightweight.

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

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

[0016] Figure 2 It is a 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 It is a structural schematic diagram of the perforated suspension oil tank of the present invention;

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

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

[0021] Figure 7 It is a schematic diagram of the structure of the perforated coordination column of the present invention;

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

[0023] Fig. 9 It is a cross-sectional schematic diagram of the side coordination column of the present invention;

[0024] Fig.10 It is a schematic diagram of the distribution of the supporting vertical columns, the side coordination columns and the perforated coordination columns of the present invention;

[0025] Fig.11 It is a top view distribution diagram of the supporting vertical columns, side coordination columns and perforated coordination columns of the present invention;

[0026] Fig.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;

[0027] Fig.13 The results of mechanical simulation of the internal longitudinal section of the columnar support equipped with a suspension oil tank rudder wing with a stress coordination platform in Example 1;

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

[0029] 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.

[0030] Specific implementation method 1, combined with Figures 1 to 11 Specific description: This embodiment is a columnar support with a suspension tank wing / rudder wing with a stress coordination platform, which is composed of an outer skin 1, a middle thermal insulation layer 2, a perforated suspension 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 sealing structure composed of an upper outer skin 11, a lower outer skin 12 and a side outer skin 13;

[0031] A plurality of holes are arranged 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, and the holes of the perforated suspension oil tank 3 are filled with the middle insulation layer 2, and a plurality of supporting vertical columns 4, a plurality of side coordination columns 5 and a plurality of perforated coordination columns 6 are arranged in the middle insulation layer 2;

[0032] The plurality of supporting vertical columns 4 are distributed along the length direction of the wing / rudder wing between the connecting end of the wing / rudder wing and the fuselage and the perforated suspension oil tank 3, and are arranged in a row along the axis of the center line of the length direction of the wing / rudder wing in a symmetrical 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 arranged 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;

[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 size of the outer skin 1 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. The upper outer skin 11, the lower outer skin 12 and the side outer skin 13 are connected by welding to ensure sealing. The upper outer skin 11 is the top structure of the outer skin 1, and it and the lower outer skin 12 of the bottom structure of the outer skin 1 together constitute the main component of the wing / rudder wing that rubs against the air and bears stress and heat, while the side outer skin 13 is the structure on both sides of the wing / rudder wing, the connection structure around the fuselage and the streamlined structure of the wing edge.

[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 contact any components except the middle insulation layer 2, so it is in a state of floating up and down according to the force conditions of the wing / rudder wing.

[0040] The supporting vertical column 4 of this embodiment is a row of vertical column structures, and its upper and lower sides include two parts: a top vertical column stress coordination platform 41 and a bottom vertical column stress coordination platform 42, which are used to relieve stress concentration. The supporting vertical column 4 is located closest to the fuselage connection and does not pass through the perforated suspension oil tank 3. It is the largest load-bearing component.

[0041] The side coordination column 5 of this embodiment is an inclined column that does not pass through the perforated suspension oil tank 3. When the inclination angle of the side coordination column 5 is 60° to 80°, the top coordination column stress coordination platform 51 and the bottom coordination column stress coordination platform 52 are included on the upper and lower sides of the side coordination column 5 to relieve stress concentration. When the inclination angle of the side coordination column 5 is less than 60°, the side coordination column 5 does not need the upper and lower stress coordination platforms.

[0042] In this embodiment, the perforated coordination column 6 connects the upper outer skin 11 and the lower outer skin 12 and is inserted in the middle insulation layer 2 and the perforated suspension oil tank 3 to maintain the structural strength of the rudder wing. The perforated coordination column 6 is an inclined column with a certain inclination angle with the outer skin, and two adjacent rows of coordination columns are staggered to form a cross, which is convenient for coordinated deformation control of strain.

[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 oil tank 3 described in this embodiment are determined according to the specific requirements of the aircraft, and the perforation position and size are determined by the shape and size of the outer skin. The material of the perforated suspension oil tank 3 is a lightweight aluminum-lithium alloy.

[0045] The beneficial effects of this embodiment are:

[0046] This embodiment provides a columnar support with a suspended fuel tank / rudder wing structure design with a stress coordination platform, and the connected column passes through the hole by digging a hole in the fuel tank. It can effectively avoid the thermal connection between the wing / rudder wing outer skin and the fuel tank, block the heat propagation to the greatest extent, and greatly improve the heat insulation ability of the structure.

[0047] This implementation method relies on the structure of the perforated fuel tank to divide different areas to achieve different functions. In the key stress-bearing area, the fuel tank can be avoided by perforation, thereby effectively ensuring the stability of the overall structure and greatly improving the stress bearing capacity of the wing / rudder wing. At the same time, a more reasonable distribution reduces the number of columns, further reducing the mass of the wing and rudder wing, achieving lightweight while further improving the load resistance of the wing and rudder wing.

[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 heat insulation layer 2 is b, and b≥0.18H. The rest is the same as specific embodiment 1.

[0049] Specific embodiment 3: This embodiment is different 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. Others are the same as specific embodiment 1 or 2.

[0050] Specific embodiment 4: This embodiment is different from 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 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. Others are the same as specific embodiments 1 to 3.

[0051] Specific embodiment 5: This embodiment is different from the first embodiment of specific embodiments 1 to 4 in that: let the distance between the two farthest points of the cross section of the middle vertical column 43 be d1, let the length of the wing / rudder wing be L, d1 = (0.01-0.02) L; let the length of the middle vertical column 43 from the side outer skin 13 of the connection end of the wing / rudder wing and the fuselage be d2, let the width of the wing / rudder wing be D, d2 = (0.1-0.25) D; let the center distance of adjacent middle vertical columns 43 be d3, d3 = (5-15) d1. The rest is the same as the first embodiment of specific embodiments 1 to 4.

[0052] Specific embodiment 6: This embodiment is different from any one of specific embodiments 1 to 5 in that: a plurality of perforated coordination columns 6 are arranged in the holes of the perforated suspension oil tank 3, and the perforated coordination columns 6 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 perforated coordination columns 6 in two adjacent rows are staggered; the inclination angle of the perforated coordination columns 6 is 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. The rest is the same as specific embodiments 1 to 5.

[0053] Specific embodiment 7: This embodiment is different from specific embodiments 1 to 6 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 along the length direction of the perforated coordination columns 6 along the wing / rudder wing. Other aspects are the same as specific embodiments 1 to 6.

[0054] Specific implementation eight: This implementation is different from any one of specific implementations one to seven in that: when the inclination angle of the side coordination column 5 is 60° to 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 a middle inclined column 53, and the top coordination column stress coordination platform 51 and the bottom coordination column stress coordination platform 52 are respectively arranged at both ends of the middle 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 middle 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 middle inclined column 53 are respectively the same as the top vertical column stress coordination platform 41, the bottom vertical column stress coordination platform 42 and the middle vertical column 43. Others are the same as specific implementations one to seven.

[0055] Specific embodiment 9: This embodiment is different from specific embodiments 1 to 8 in that: when the inclination angle of the side coordination column 5 is 40° to 60°, 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. Other aspects are the same as specific embodiments 1 to 8.

[0056] Specific embodiment 10: This embodiment is different from specific embodiments 1 to 9 in that the material of the plurality of supporting vertical columns 4, the plurality of side coordination columns 5 and the plurality of perforated coordination columns 6 are the same as the outer skin 1; the final service environment temperature of the columnar support with suspension tank wing / rudder wing with stress coordination platform is T, 750℃≥T≥400℃. Others 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] 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:

[0059] A columnar support with a suspension oil tank rudder wing with a stress coordination platform, which is composed of an outer skin 1, a middle heat 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 sealing structure composed of an upper outer skin 11, a lower outer skin 12 and a side outer skin 13;

[0060] The perforated suspension oil tank 3 has three rectangular holes arranged in parallel 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 filled with the middle insulation layer 2, and a plurality of supporting vertical columns 4, a plurality of side coordination columns 5 and a plurality of perforated coordination columns 6 are arranged in the middle insulation layer 2;

[0061] The plurality of supporting vertical columns 4 are distributed between the connecting end of the rudder wing and the fuselage and the perforated suspension 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; 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 arranged 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 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 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 middle vertical column 43 is d1, and the length of the rudder wing is L, L=1000mm, d1=10mm; Assume that the length of the middle vertical column 43 from the side outer skin 13 at the connection end of the rudder wing and the fuselage is d2, and the width of the rudder wing is D, D=600mm, d2=80mm; Assume that the center distance between adjacent middle vertical columns 43 is d3, d3=70mm;

[0069] A plurality of perforated coordination columns 6 are arranged in the holes of the perforated suspension oil tank 3. The perforated coordination columns 6 in a single hole are arranged in n rows × m columns, where 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 perforated coordination columns 6 in two adjacent rows are staggered with each other; the perforated coordination columns 6 start from the end close to the wing connection, and the inclination angles in each hole are 78.7°, 63.4° and 51.3°, respectively, and m is 12, 8, and 8, respectively; the cross section of the perforated coordination column 6 is circular; the distance between the two farthest points of the cross section of the perforated coordination column 6 is f1, and f1=4mm;

[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 coordination column 5 is 78.7° and 63.4°, 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 a middle oblique column 53, and the top coordination column stress coordination platform 51 and the bottom coordination column stress coordination platform 52 are respectively arranged at both ends of the middle oblique 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 middle oblique column 53 is d4, d4=10mm; 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 middle 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 middle vertical column 43;

[0072] When the inclination angle of the side coordination column 5 is 51.3°, the side coordination column 5 is an intermediate oblique column 53; the cross-sectional shape and cross-sectional size of the intermediate oblique column 53 are the same as those of the intermediate 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 Ti 2 AlNb;

[0074] The final 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 tank 3 is AlLi alloy, and the tank can be loaded with fuel; the middle insulation layer 2 is SiO 2 Aerogel.

[0076] Fig.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.

[0077] Fig.13 The results of the mechanical simulation of the internal longitudinal section of the columnar support with a suspended oil tank rudder wing with a stress coordination platform in Example 1 are shown in the figure. It can be clearly seen from the results that the maximum internal stress of this structure under normal flight stress is 202.68MPa, which meets the service environment of most high-temperature and high-strength materials and has a wider range of applications.

[0078] Fig.14 The overall thermal simulation results of the columnar support with a suspended oil tank rudder with a stress coordination platform in Example 1. From the results, it can be seen that when the external temperature environment is 650°C, the rudder wing of this structure can still ensure that the temperature of the internal oil tank is in a safe temperature environment.

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

Claims

1. A columnar support with a suspended oil tank wing / rudder wing with a stress coordination platform, characterized in that It is composed of an outer skin (1), a middle heat 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 sealing structure composed 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 arranged 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 connecting end of the wing / rudder wing and the fuselage and the perforated suspension oil tank (3), and are arranged in a row along the axis of the center line of the length direction of the wing / rudder wing in a symmetrical 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 arranged 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 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 suspension tank wing / rudder wing with a stress coordination platform according to claim 1, characterized in that The maximum height of the wing / rudder wing is H, and the thickness of the middle thermal insulation layer (2) at the thinnest position is b, b≥0.18H.

3. A columnar support with a suspension 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 suspension 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 suspension tank wing / rudder wing with a stress coordination platform according to claim 1, characterized in that The distance between the two farthest points of the cross section of the middle vertical column (43) is d1, and the length of the wing / rudder wing is L, d1=(0.01-0.02)L; the length of the middle 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; the center distance between adjacent middle vertical columns (43) is d3, d3=(5-15)d1.

6. A columnar support with a suspension tank wing / rudder wing with a stress coordination platform according to claim 1, 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, 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 perforated coordination columns (6) in two adjacent rows are staggered and distributed with each other; the inclination angle of the perforated coordination columns (6) is 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 columns (6) is f1, and f1=(0.2 to 0.6)d1.

7. A columnar support with a suspension 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 suspension 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° to 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 the top coordination column stress coordination platform (51) and the bottom coordination column stress coordination platform (52) are respectively arranged 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 suspension 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 inclined column (53); the cross-sectional shape and cross-sectional size of the intermediate inclined column (53) are the same as those of the intermediate vertical column (43).

10. A columnar support with a suspension tank wing / rudder wing with a stress coordination platform according to claim 1, characterized in that The material of the plurality of supporting vertical columns (4), the plurality of side coordination columns (5) and the plurality of perforated coordination columns (6) is the same as that of the outer skin (1); the final service environment temperature of the columnar support with suspension tank wing / rudder wing with stress coordination platform is T, 750°C ≥ T ≥ 400°C.

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