A multi-module series tank for light-weight insulated oil storage wings / ailers

Abstract

A kind of multi-module series oil tank for light heat-insulated oil storage wing / aileron, the present application belongs to the technical field of aerospace manufacturing.The present application solves the problem that the high-temperature service environment of the existing light-weight hypersonic aircraft wing / aileron fuel tank is prone to overheating, stress concentration, and some fuel tanks belong to flow dead zone, which causes the region to break through the thermal protection to form a thermal bridge, seriously affecting the service life of the fuel tank.The multi-module series oil tank is composed of n oil tanks connected by oil pipeline, and is left-right symmetrical structure along the center line L;The side of the oil tank along the height direction is composed of two symmetrical inclined planes.The present application is a multi-module series oil tank for light heat-insulated oil storage wing / aileron.

Description

Technical Field

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

[0002] As hypersonic aircraft fly faster and faster, the aerodynamic loads and thermal environment they face in the atmosphere become more extreme. Consequently, the demand for lightweight, high-strength, thermally stable, and multifunctional integration in aircraft structural design is increasing. This requires that the rudder and wing fuel tanks of new hypersonic aircraft be effectively reduced in weight and have greater fuel layout flexibility, thereby improving the aircraft's speed, range, maneuverability, and overall performance.

[0003] The wings and rudders of today's hypersonic aircraft are mainly based on plate rib structures ( Figure 1 ), its oil storage tanks mostly use multiple tank boxes connected to the oil pipeline. However, as the speed of the aircraft increases, the wings and rudder wings become thinner. This traditional multiple fuel tank faces many problems such as a significant decrease in heat insulation ability, difficulty in controlling the oil temperature, and stress concentration in the tanks. Instead, it becomes a burden that restricts the speed of the aircraft. At the same time, there is no reasonable oil circuit design. Some fuel tanks belong to the flow dead zone, causing the thermal protection in this area to break through the thermal protection to form a thermal bridge, which seriously affects the service life of the fuel tank. Therefore, it is necessary to conduct research on the fuel tanks of the circulating oil rudder wings of high-speed aircraft, and find a new integrated rudder wing tank structure with better thermal insulation performance while maintaining the lightweight of the fuel tank. Summary of the Invention

[0004] The present invention aims to solve the problem that the wing / rudder fuel tanks of hypersonic aircraft with existing lightweight requirements are prone to overheating and stress concentration in a high-temperature service environment, and some tanks have flow dead zones, which cause the thermal protection in this area to break through and form thermal bridges, seriously affecting the service life of the tanks. The present invention provides a multi-module series fuel tank for lightweight insulated oil storage wings / rudder wings.

[0005] A multi-module series oil tank for a lightweight heat-insulated oil storage wing / rudder wing, wherein the multi-module series oil tank for a lightweight heat-insulated oil storage wing / rudder wing is composed of n oil reservoirs connected in series via oil pipelines and has a bilaterally symmetrical structure along a center line L; wherein n is an even number and n≥4;

[0006] The side surface of the oil depot along the height direction is composed of two symmetrical inclined surfaces, and the inclination angle between the inclined surface and the vertical direction is α, 60°≥α≥30°;

[0007] Assume that the length of the oil depot is Ln, the width is Dn, and the height is Hn. 150mm≥Ln≥50mm, 100mm≥Dn≥50mm, 80mm≥Hn≥10mm;

[0008] Assume the cross-sectional area of ​​the oil pipeline is S, S ≥ 10mm 2 ;

[0009] The head and tail of the multi-module series oil tank are respectively provided with an oil inlet and an oil outlet.

[0010] The beneficial effects of the present invention are:

[0011] This invention provides a multi-module, serially connected fuel tank structure for lightweight, thermally insulated, and oil-storage wings / rudders. By replacing conventional large fuel tanks with modular fuel storage modules, this design not only effectively reduces tank weight but also provides a larger heat dissipation area, facilitating the tank's multifunctional requirements of both lightweighting and thermal insulation. The one-way oil flow design ensures that heat is removed from every location, achieving temperature balance within the tank and significantly improving its thermal insulation performance.

[0012] The present invention's serial modular structure reduces weight while isolating the fuel tank from the complex structures within the wing / rudder. The integrated design of the fuel piping and reservoir provides ample space for the various load-bearing and thermal insulation structures within the wing / rudder, significantly reducing the risk of the fuel tank contacting the load-bearing structures, causing additional stress, or thermal bridges due to insulation failure. Furthermore, the fuel tank's integrated rigid structure offers significant stress resistance, ensuring a long service life even in demanding environments.

[0013] The invention is used for a multi-module serial oil tank for a lightweight heat-insulating oil-storage wing / rudder wing. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 This is a schematic diagram of the wing structure of an existing plate-rib structure hypersonic aircraft;

[0015] Figure 2 This is a schematic structural diagram of a multi-module series oil tank for a lightweight heat-insulating oil storage wing / rudder wing according to the present invention;

[0016] Figure 3 It is a structural schematic diagram of the oil depot of the present invention;

[0017] Figure 4 It is a longitudinal cross-sectional schematic diagram of the oil depot of the present invention;

[0018] Figure 5 Schematic cross-section of the oil pipeline of the present invention;

[0019] Figure 6 This is a physical picture of a multi-module series oil tank for a lightweight thermally insulated oil storage wing / rudder wing according to Example 1;

[0020] Figure 7 Schematic diagram of stress simulation results of multi-module series oil tanks for lightweight thermal insulation oil storage wings / rudder wings in Example 1

[0021] Figure 8 This is a schematic diagram of the simulation results of the heat insulation effect of the multi-module series oil tank for lightweight heat-insulating oil storage wings / rudder wings in Example 1. DETAILED DESCRIPTION

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

[0023] Specific implementation method 1, combined with Figures 2 to 5 Specifically, this embodiment provides a multi-module series oil tank for a lightweight insulated oil storage wing / rudder wing. The multi-module series oil tank for a lightweight insulated oil storage wing / rudder wing is composed of n oil reservoirs 1 connected in series via oil pipelines 2, and has a bilaterally symmetrical structure along a center line L. The aforementioned n is an even number, and n ≥ 4;

[0024] The side surface of the oil depot 1 along the height direction is composed of two symmetrical inclined surfaces, and the inclination angle between the inclined surface and the vertical direction is α, 60°≥α≥30°;

[0025] Assume that the length of oil depot 1 is Ln, the width is Dn, and the height is Hn. 150mm≥Ln≥50mm, 100mm≥Dn≥50mm, and 80mm≥Hn≥10mm.

[0026] Assume that the cross-sectional area of ​​the oil pipeline 2 is S, S ≥ 10mm 2 ;

[0027] The head and tail of the multi-module series oil tank are respectively provided with an oil inlet 3-1 and an oil outlet 3-2.

[0028] The shapes and sizes of the oil depots 1 described in this embodiment are determined by the structure of the aircraft and the rudder wing, and can be consistent or different. The oil depots 1 are independent of each other and are only connected by the oil pipeline 2, so that the final oil tank has a serial module structure.

[0029] In this embodiment, the oil pipeline 2 is a component that interconnects the various oil depots 1. It passes through each depot 1 once, forming a single oil circuit with all the depots 1 in series. The total length of the oil pipeline 2 connecting all the depots 1 to the left of the centerline L is the same as the total length of the oil pipeline 2 connecting all the depots 1 to the right of the centerline L, ensuring a stable center of gravity for the fuel tank.

[0030] In this specific embodiment, the oil inlet 3-1 and the oil outlet 3-2 are components for fuel to flow into and out of the fuel tank. The shape and size of the oil inlet 3-1 and the oil outlet 3-2 are exactly the same. They are connected to the two oil tanks 1 at the starting point of the oil pipeline 2 in series, and are connected to the rigid fuel flow pipeline connected to the aircraft fuselage.

[0031] In this embodiment, the cross-sectional shape and size of each section of the oil pipeline 2 are the same.

[0032] In this embodiment, the connection positions of the oil inlet 3-1 and the oil outlet 3-2 with the oil reservoir 1 are based on the principle of not contacting other structures of the rudder wing. Their positions can be adjusted arbitrarily and connected to the oil reservoir 1, and the oil circuit can be changed synchronously to keep them in series.

[0033] In this specific embodiment, the path design of the multi-module series oil tank oil circuit is determined according to the structure of the rudder wing. There is only one fixed route, and this route flows into the oil inlet 3-1, passes through all oil depots 1, and finally flows out from the oil outlet 3-2.

[0034] The oil reservoir 1 and oil pipeline 2 described in this embodiment are rigid structures, their connection positions adjusted to the wing / rudder structure, and are integrally formed. The shape, size, and structure of the oil inlet 3-1 and oil outlet 3-2 are adjusted to other parts of the aircraft to ensure sealing and fluidity.

[0035] In this specific embodiment, since the multi-module series oil tank is a left-right symmetrical structure, the oil depot 1 connected on the left side of the center line L and the oil depot 1 connected on the right side can be formed into a single-side oil tank, such as by forging, and then the oil tanks on both sides that are formed integrally are combined and welded and sealed, such as by argon arc welding.

[0036] The beneficial effects of this embodiment are:

[0037] This embodiment provides a multi-module, serially connected fuel tank structure for lightweight, thermally insulated, fuel-storage wings / rudders. By replacing conventional large fuel tanks with modular fuel storage modules, this design not only effectively reduces tank weight but also provides a larger heat dissipation area, facilitating the tank's multifunctionality, both in terms of weight reduction and thermal insulation. The unidirectional oil flow design ensures that heat is removed from every location, achieving temperature balance within the tank and significantly improving its thermal insulation performance.

[0038] The tandem modular structure of this embodiment reduces weight while isolating the fuel tank from the complex structures within the wing / rudder. The combined design of the oil pipeline 2 and the oil reservoir 1 provides ample space for the various load-bearing and thermal insulation structures within the wing / rudder, significantly reducing the risk of the fuel tank contacting the load-bearing structures, causing additional stress, or thermal bridges due to insulation failure. Furthermore, the fuel tank's integrated rigid structure offers significant stress resistance, ensuring a long service life even in demanding environments.

[0039] Specific embodiment 2: This embodiment differs from specific embodiment 1 in that the interval between adjacent oil depots 1 is greater than 10 mm. Other aspects are the same as specific embodiment 1.

[0040] Specific implementation three: the difference between this embodiment and one or two of the specific implementations is that the material of the multi-module series oil tank for the lightweight heat-insulating oil storage wing / aileron wing is aluminum lithium alloy. The others are the same as in specific implementation one or two.

[0041] Specific implementation four: the difference between this embodiment and one to three of the specific implementations is that the cross section of the oil tank 1 is square, circular or polygonal; the cross section of the oil pipeline 2 is square, circular or polygonal. The others are the same as in specific implementation one to three.

[0042] Specific implementation five: the difference between this embodiment and one to four of the specific implementations is that the inner wall corners of the oil tank 1 are all rounded with a radius R1, R1≥5mm; the inner wall corners of the oil pipeline 2 are all rounded with a radius R2, R2≥4mm. The others are the same as in specific implementation one to four.

[0043] Specific implementation six: the difference between this embodiment and one to five of the specific implementations is that the height of the oil pipeline 2 is h, h=0.8×min{H1,…,Hn}; the length of the oil pipeline 2 is l, l∈(0.1~0.3)×min{L1,…,Ln}. The others are the same as in specific implementation one to five.

[0044] Specific implementation seven: the difference between this embodiment and one to six of the specific implementations is that the oil inlet 3-1 and the oil outlet 3-2 are connected to the fuel flow pipeline of the aircraft through a hose or a rigid hard pipe. The others are the same as in specific implementation one to six.

[0045] The hose or rigid hard pipe connected to the oil inlet 3-1 and the oil outlet 3-2 is consistent with the pipeline connected to the aircraft.

[0046] Specific implementation eight: the difference between this embodiment and one to seven of the specific implementations is that only one section of the oil pipeline 2 in the multi-module series oil tank for the lightweight heat-insulating oil storage wing / aileron wing is divided by the center line L. The others are the same as in specific implementation one to seven.

[0047] Only one section of the oil pipeline 2 is divided by the center line L into two identical parts, and the other oil pipelines 2 are not in contact with the center line L.

[0048] Specific implementation nine: the difference between this embodiment and one to eight of the specific implementations is that the thickness of the skin of the oil tank 1 is b, 3mm≥b≥1mm. The others are the same as in specific implementation one to eight.

[0049] Specific embodiment 10: This embodiment differs from any one of specific embodiments 1 to 9 in that the multi-module series oil tank for a lightweight, thermally insulated, oil-storage wing / rudder is used within an oil-storage wing / rudder having an external temperature of H, where H is ≤ 800°C. Other aspects are the same as specific embodiments 1 to 9.

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

[0051] Example 1, combined with Figure 6 Specific instructions:

[0052] A multi-module series oil tank for a lightweight, heat-insulated, oil-storage wing / rudder wing, comprising n oil depots 1 connected in series via oil pipelines 2, and forming a bilaterally symmetrical structure along a centerline L; n being an even number, and n=12; and the oil depots 11, 2, 3, 4, 5, 6, 7, 8, 9, 10, 110, 111, and 12 in the order of oil flow.

[0053] The side surface of the oil depot 1 along the height direction is composed of two symmetrical inclined surfaces, and the inclination angle between the inclined surface and the vertical direction is α, α = 45°;

[0054] Assume that the length of oil depot 1 is Ln, the width is Dn, and the height is Hn;

[0055] Among them, the length Ln of No. 4 oil depot 14, No. 5 oil depot 15, No. 6 oil depot 16, No. 7 oil depot 17, No. 8 oil depot 18 and No. 9 oil depot 19 is 120mm; the length Ln of No. 1 oil depot 11, No. 2 oil depot 12, No. 3 oil depot 13, No. 10 oil depot 110, No. 11 oil depot 111 and No. 12 oil depot 112 is 100mm;

[0056] The width Dn of oil depot No. 2 12, oil depot No. 3 13, oil depot No. 4 14, oil depot No. 5 15, oil depot No. 8 18, oil depot No. 9 19, oil depot No. 10 110, and oil depot No. 11 111 is 60 mm; the width Dn of oil depot No. 1 11, oil depot No. 6 16, oil depot No. 7 17, and oil depot No. 12 112 is 80 mm.

[0057] The height Hn of oil depot No. 11, oil depot No. 6, oil depot No. 7, oil depot No. 17, and oil depot No. 12 is 60 mm; the height Hn of oil depot No. 2, oil depot No. 12, oil depot No. 5, oil depot No. 8, oil depot No. 18, and oil depot No. 11 is 40 mm; the height Hn of oil depot No. 3, oil depot No. 13, oil depot No. 4, oil depot No. 9, oil depot No. 19, and oil depot No. 10 is 25 mm.

[0058] Assume that the cross-sectional area of ​​the oil pipe 2 is S, S = 10mm 2 ;

[0059] The oil depot No. 1 11 is provided with an oil inlet 3 - 1 , and the oil depot No. 12 112 is provided with an oil outlet 3 - 2 .

[0060] The interval between adjacent oil tanks 1 is 20 mm.

[0061] The material of the multi-module series oil tank for the lightweight heat-insulating oil storage wing / rudder wing is 2A97 aluminum-lithium alloy.

[0062] The cross section of the oil depot 1 is square; the cross section of the oil pipeline 2 is hexagonal.

[0063] The inner wall corners of the oil depot 1 are all rounded R1, R1 = 15 mm. The inner wall corners of the oil pipeline 2 are all rounded R2, R2 = 4 mm.

[0064] Assume that the height of the oil pipeline 2 is h, h=20 mm; and assume that the length of the oil pipeline 2 is l, l=20 mm.

[0065] The oil inlet 3-1 and the oil outlet 3-2 are connected to the fuel flow pipeline of the aircraft through Ti2AlNb rigid hard pipes.

[0066] In the multi-module series oil tank for lightweight insulated oil storage wings / rudder wings, only one section of the oil pipeline 2 is divided by the center line L, that is, the oil pipeline 2 between the No. 6 oil depot 16 and the No. 7 oil depot 17 is divided by the center line L.

[0067] Assume that the thickness of the oil tank 1 skin is b, b = 1.5 mm.

[0068] In this embodiment, oil depot No. 1 112, oil depot No. 12, oil depot No. 3 13, oil depot No. 4 14, oil depot No. 5 15, and oil depot No. 6 16 are located on one side of the center line L and form a U shape; oil depot No. 7 17, oil depot No. 8 18, oil depot No. 9 19, oil depot No. 10 110, oil depot No. 11 11 and oil depot No. 12 112 are located on the other side of the center line L and form a U shape.

[0069] The multi-module serial oil tank for the lightweight heat-insulating oil storage wing / rudder wing is used in the oil storage wing / rudder wing with an external temperature of H, and H=650°C.

[0070] Figure 7 This is a schematic diagram of the stress simulation results of a multi-module series fuel tank for a lightweight insulated oil storage wing / rudder wing in Example 1. As can be seen from the figure, the maximum load that this type of fuel tank can withstand during flight is only 10.923 MPa, which is far less than the ultimate yield strength of the material. This shows that this type of fuel tank has an excellent ability to disperse stress loads within the aircraft's internal structure.

[0071] Figure 8This is a schematic diagram of the simulation results of the heat-insulating effect of a multi-module series fuel tank for a lightweight insulated oil storage wing / rudder wing in Example 1. As can be seen from the figure, the fuel tank with this structure can still maintain a low temperature environment of 26°C when the external temperature load is 640°C during the flight of the aircraft, which means that this type of fuel tank can have excellent heat-insulating capabilities when combined with a suitable insulation layer.

Claims

1. A multi-module series oil tank for lightweight thermal insulation oil storage wings / rudder wings, characterized in that A multi-module series oil tank for a lightweight heat-insulated oil storage wing / rudder wing is formed by connecting n oil reservoirs (1) in series via oil pipelines (2), and has a bilaterally symmetrical structure along a center line L; n is an even number, and n≥4; The side surface of the oil depot (1) along the height direction is composed of two symmetrical inclined surfaces, and the inclination angle between the inclined surface and the vertical direction is α, 60°≥α≥30°; Assume that the length of the oil depot (1) is Ln, the width is Dn, and the height is Hn, 150mm≥Ln≥50mm, 100mm≥Dn≥50mm, 80mm≥Hn≥10mm; Assume that the cross-sectional area of ​​the oil pipeline (2) is S, S≥10mm 2 ; The head and tail of the multi-module series oil tank are respectively provided with an oil inlet (3-1) and an oil outlet (3-2).

2. A multi-module series oil tank for lightweight thermal insulation oil storage wings / rudder wings according to claim 1, characterized in that The interval between adjacent oil depots (1) is greater than 10 mm.

3. A multi-module series oil tank for lightweight thermal insulation oil storage wings / rudder wings according to claim 1, characterized in that The material of the multi-module series oil tank for the lightweight heat-insulating oil storage wing / rudder wing is aluminum-lithium alloy.

4. A multi-module series oil tank for lightweight thermal insulation oil storage wings / rudder wings according to claim 1, characterized in that The cross section of the oil depot (1) is square, circular or polygonal; the cross section of the oil pipeline (2) is square, circular or polygonal.

5. The multi-module series oil tank for lightweight thermal insulation oil storage wing / rudder wing according to claim 1 is characterized in that The inner wall corners of the oil depot (1) are all rounded R1, R1≥5mm; the inner wall corners of the oil pipeline (2) are all rounded R2, R2≥4mm.

6. A multi-module series oil tank for lightweight heat-insulated oil storage wings / rudder wings according to claim 1, characterized in that The height of the oil pipeline (2) is h, h=0.8×min{H1, ..., Hn}; the length of the oil pipeline (2) is l, l∈(0.1~0.3)×min{L1, ..., Ln}.

7. The multi-module series oil tank for lightweight thermal insulation oil storage wing / rudder wing according to claim 1 is characterized in that The oil inlet (3-1) and the oil outlet (3-2) are connected to the fuel flow pipeline of the aircraft through a hose or a rigid hard pipe.

8. The multi-module series oil tank for lightweight thermal insulation oil storage wing / rudder wing according to claim 1 is characterized in that In the multi-module series oil tank for lightweight heat-insulated oil storage wings / rudder wings, only one section of the oil pipeline (2) is divided by the center line L.

9. A multi-module series oil tank for lightweight heat-insulated oil storage wings / rudder wings according to claim 1, characterized in that The thickness of the oil depot (1) skin is b, 3mm≥b≥1mm.

10. The multi-module series oil tank for lightweight thermal insulation oil storage wing / rudder wing according to claim 1, characterized in that The multi-module serial oil tank for the lightweight heat-insulating oil storage wing / rudder wing is used in the oil storage wing / rudder wing with an external temperature of H, and H≤800°C.

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