Aircraft pressure-bearing oil tank and using method thereof

Abstract

The invention discloses an aircraft pressure-bearing oil tank and a using method thereof, and belongs to the technical field of aircraft oil tanks. The aircraft pressure-bearing oil tank comprises an inner shell, the inner shell is arranged in an aircraft outer shell, a front end cover and a rear end cover are fixedly arranged at the two ends of the inner shell in a sealed mode respectively and are both fixed to the aircraft outer shell, an oil bag is arranged in the inner shell, the two ends of the oil bag are fixed to the front end cover and the rear end cover respectively, and an oil pipe is arranged in the oil bag. A plurality of oil holes are formed in the oil pipe, an oil inlet and outlet connector communicated with the oil pipe is arranged on the rear end cover, a breather pipe is arranged on the front end cover, an air inlet pipe is arranged on the rear end cover, an isolation section is arranged in the aircraft shell, and the isolation section makes contact with the inner shell and the aircraft shell. According to the aircraft pressure-bearing oil tank and the using method thereof, the structure of the oil tank is optimized, the space utilization rate of an aircraft is increased, the weight of the oil tank is reduced, and the oil carrying capacity of the oil tank is increased.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft fuel tanks, and in particular to an aircraft pressure fuel tank and a use method thereof. Background Art

[0002] Ramjet engines are the heart of hypersonic aircraft, rockets, missiles and other hypersonic vehicles. In order to increase the range and endurance of hypersonic vehicles, the capacity of the ramjet engine fuel tank must be as large as possible; in order to make the hypersonic vehicle fly faster and more maneuverable, the weight of the ramjet engine structural parts must be reduced as much as possible; in order to improve the space utilization of hypersonic vehicles, the fuel tank structure must be as compact as possible.

[0003] Aircraft such as rockets and missiles usually have a circular cross-section, and the fuel tanks of their engines are pressure vessels. Standard pressure-bearing vessels are usually designed as a rotating body structure. However, installing a rotating body structure fuel tank in an aircraft with a circular cross-section will lead to problems such as reduced space utilization and low fuel tank capacity. Since the fuel tank needs to withstand a certain pressure, while improving the space utilization of the aircraft, the weight of the fuel tank is relatively large, affecting the flight performance of the aircraft. How to reduce the weight of the fuel tank as much as possible while improving the space utilization of the aircraft is the key and difficulty in the design of the aircraft fuel tank structure. Summary of the invention

[0004] The purpose of the present invention is to provide an aircraft pressure fuel tank and a method for using the same, which can improve the space utilization of the aircraft, reduce the weight of the fuel tank, and increase the fuel capacity of the fuel tank by optimizing the structure of the fuel tank.

[0005] To achieve the above-mentioned purpose, the present invention provides an aircraft pressure oil tank, including an inner shell, which is arranged inside the aircraft outer shell, and the two ends of the inner shell are respectively and sealedly fixedly provided with a front cover and a rear cover, and the front cover and the rear cover are both fixed on the aircraft outer shell, an oil bladder is arranged inside the inner shell, and the two ends of the oil bladder are respectively fixed on the front cover and the rear cover, an oil pipe is arranged inside the oil bladder, and a plurality of oil holes are arranged on the oil pipe, an oil inlet and outlet joints connected with the oil pipe are arranged on the rear cover, a ventilation pipe is arranged on the front cover, and an air intake pipe is arranged on the rear cover, and an isolation section is arranged inside the aircraft outer shell, and the isolation section is in contact with both the inner shell and the aircraft outer shell.

[0006] Preferably, ear plates are provided at both ends of the isolation section, and the isolation section is fixedly connected to the front end cover and the rear end cover through the ear plates.

[0007] Preferably, the inner shell includes a main body, sealing baffles are fixedly provided at both ends of the main body, the thickness and width of the sealing baffles are not less than the thickness and width of the main body, reinforcing ribs are provided between the main body and the sealing baffles, and the main body is sealed and fixedly connected to the front cover and the rear cover through the sealing baffles.

[0008] Preferably, the main body comprises a cylindrical section, a corrugated section is provided at the lower portion of the cylindrical section, an outer surface of the cylindrical section fits with an inner surface of the aircraft outer shell, and a middle outer surface of the corrugated section fits with an outer surface of the isolation section.

[0009] Preferably, the corrugated section includes a convex arc section and a concave arc section, the convex arc section is located on both sides of the concave arc section, the concave arc section is connected to the cylindrical section through the convex arc section, and the outer surface of the isolation section is in contact with the outer surface of the concave arc section.

[0010] Preferably, the main body is an outer wall with uniform thickness.

[0011] Preferably, one end of the oil bag is fixed to the center of the front end cover through a fixed joint, the other end of the oil bag is fixed to the center of the rear end cover, and the oil inlet and outlet joints are located at the center of the rear end cover.

[0012] Preferably, a pipeline cavity for arranging pipelines is provided between the isolation section, the inner shell and the aircraft outer shell.

[0013] Preferably, the length of the oil pipe is greater than the length of the inner shell, the density of the oil pipe is not less than the density of the fuel, and the oil pipe is a hose.

[0014] The method for using the above-mentioned aircraft pressure oil tank comprises the following steps:

[0015] S1. Open the oil inlet valve on the oil inlet and outlet joints, open the vent pipe valve, close the air inlet pipe valve, inject fuel into the oil bag through the oil inlet and outlet joints and the oil pipe, the oil bag expands, and the gas in the inner shell is discharged from the inner shell through the vent pipe;

[0016] S2. After the fuel filling is completed, close the oil inlet valve on the oil inlet and outlet joints, close the exhaust pipe valve, open the oil outlet valve on the oil inlet and outlet joints, open the intake pipe valve, and introduce gas into the inner shell through the intake pipe. The gas exerts squeezing force on the oil bag, and the fuel in the oil bag is sent to the downstream pipeline through the oil pipe and the oil inlet and outlet joints.

[0017] The advantages and positive effects of the aircraft pressure oil tank and the method of using the same according to the present invention are:

[0018] 1. The present invention optimizes the structure of the inner shell to transfer the pressure of the inner shell to the outer shell of the aircraft as evenly as possible, thereby improving the strength of the inner shell and reducing the weight of the inner shell while meeting the strength and rigidity requirements.

[0019] 2. The present invention optimizes the structure of the inner shell, thereby increasing the space utilization rate of the pressure oil tank and improving the fuel carrying capacity while ensuring the strength and rigidity requirements of the inner shell.

[0020] The technical solution of the present invention is further described in detail below through the accompanying drawings and embodiments. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 A schematic diagram of the side structure of an oil tank according to an embodiment of the present invention;

[0022] Figure 2 for Figure 1 Cross-section of the fuel tank in the AA direction;

[0023] Figure 3 for Figure 2 Cross-section of the fuel tank in the BB direction;

[0024] Figure 4 This is a schematic diagram of the three-dimensional structure of the inner shell according to an embodiment of the present invention;

[0025] Figure 5 It is a schematic diagram of the side view structure of the inner shell of an embodiment of the present invention;

[0026] Figure 6 It is a schematic diagram of the isolation section structure of an embodiment of the present invention;

[0027] Figure 7 This is a force analysis diagram of the inner shell of an embodiment of the present invention;

[0028] Figure 8 This is a force analysis diagram of the isolation segment according to an embodiment of the present invention.

[0029] Reference numerals

[0030] 1. Aircraft outer shell; 2. Inner shell; 3. Oil bladder; 4. Oil pipe; 5. Front cover; 6. Rear cover; 7. Isolation section; 8. Fixed joint; 9. Oil inlet and outlet joints; 10. Ventilation pipe; 11. Inlet pipe; 12. Pipeline cavity; 13. Main body; 14. Sealing baffle; 15. Cylinder section; 16. Convex arc section; 17. Concave arc section; 18. Ear plate. DETAILED DESCRIPTION

[0031] In the description of the present invention, it should be noted that the terms "upper", "lower", "inside", "outside", etc. indicate positions or positional relationships based on the positions or positional relationships shown in the accompanying drawings, or the positions or positional relationships in which the invented product is usually placed when in use. They are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention. In the description of the present invention, it should also be noted that, unless otherwise clearly specified and limited, the terms "setting", "installation", and "connection" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be an indirect connection through an intermediate medium, or it can be a connection between the two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0032] The embodiments of the present invention are described in detail below in conjunction with the accompanying drawings.

[0033] like Figure 1 , Figure 2 , Figure 3 As shown. An aircraft pressure oil tank includes an inner shell 2, which is arranged inside an aircraft outer shell 1. The inner shell 2 is a sheet metal structure. A front cover 5 and a rear cover 6 are respectively and sealedly fixedly arranged at both ends of the inner shell 2, and the inner shell 2, the front cover 5 and the rear cover 6 are assembled into a sealed oil chamber. The front cover 5 and the rear cover 6 are both fixed to the aircraft outer shell 1 by bolts, so that the weight and load of the inner shell 2 are borne by the aircraft outer shell 1.

[0034] An oil bladder 3 is provided inside the inner shell 2, and the inside of the oil bladder 3 is used to hold fuel. The oil bladder 3 is a flexible, oil-proof structure, which facilitates the fuel to enter or be discharged from the oil bladder 3. One end of the oil bladder 3 is fixed to the center of the front cover 5 through a fixed joint 8, and the other end of the oil bladder 3 is fixed to the center of the rear cover 6. An oil pipe 4 is provided inside the oil bladder 3, and a plurality of oil holes are provided on the oil pipe 4. Fuel is injected into or discharged from the oil bladder 3 through the oil pipe 4. An oil inlet and outlet joint 9 connected to the oil pipe 4 is provided on the rear cover 6, and the oil inlet and outlet joint 9 is located in the center of the rear cover 6. A tee is provided on the oil inlet and outlet joint 9, and the oil inlet and outlet joint 9 is connected to the filling pipe 4 and the oil drain pipe 4 respectively through the tee.

[0035] The length of the oil pipe 4 is greater than that of the inner shell 2, so that the oil pipe 4 can contact the inner wall at the bottom of the inner shell 2, fully discharge the fuel in the inner shell 2, and reduce the residual rate of the fuel. The density of the oil pipe 4 is not less than the density of the fuel, ensuring that the gravity on the oil pipe 4 is greater than the buoyancy during normal operation and droops, so that the oil pipe 4 is always immersed in the fuel; when the aircraft is maneuvering, the oil pipe 4 has a good followability to the fuel and can closely follow the concentrated direction of the fuel, thereby ensuring that the oil pipe 4 can be immersed in the fuel in real time; it is conducive to improving the stability and continuity of the fuel supply. The oil pipe 4 is a hose, and a PVC steel wire hose is used to prevent the oil pipe 4 from being flattened and affecting the fluidity of the fuel.

[0036] like Figure 6 As shown. An isolation section 7 is provided inside the outer shell 1 of the aircraft, and the isolation section 7 is located below the inner shell 2. The isolation section 7 is in contact with both the inner shell 2 and the outer shell 1 of the aircraft. Ear plates 18 are fixedly provided at both ends of the isolation section 7, and the ear plates 18 are fixedly connected to the front cover 5 and the rear cover 6 by bolts. The isolation section 7 is fixed to the front cover 5 and the rear cover 6 through the ear plates 18, thereby indirectly fixed to the outer shell 1 of the aircraft, and the weight of the isolation section 7 is supported by the outer shell 1 of the aircraft.

[0037] like Figure 4 As shown. The inner shell 2 includes a main body 13, and sealing baffles 14 are fixedly provided at both ends of the main body 13 by welding. The thickness and width of the sealing baffle 14 are not less than the thickness and width of the main body 13, so as to facilitate the connection of the main body 13 and improve the stability of the connection of the main body 13. Reinforcing ribs are provided between the main body 13 and the sealing baffle 14 to improve the stability of the connection between the main body 13 and the sealing baffle 14. The sealing baffle 14 is fixedly connected to the front cover 5 and the rear cover 6 by bolts. Rubber sealing pads or sealing rings are provided between the sealing baffle 14 and the front cover 5 and the rear cover 6 to improve the sealing effect of the connection between the inner shell 2 and the front cover 5 and the rear cover 6. The main body 13 is sealed and fixedly connected to the front cover 5 and the rear cover 6 through the sealing baffle 14.

[0038] like Figure 5 As shown. The main body 13 includes a cylindrical section 15, and a corrugated section is provided at the lower part of the cylindrical section 15. The cylindrical section 15 and the corrugated section are an integral structure. The main body 13 is an outer wall with uniform thickness, which is convenient for processing the main body 13. The outer surface of the cylindrical section 15 fits with the inner surface of the aircraft shell 1, so that the cylindrical section 15 is supported by the aircraft shell 1, and the support strength of the cylindrical section 15 is improved.

[0039] The corrugated section includes a convex arc section 16 and a concave arc section 17, and the convex arc section 16 is located on both sides of the concave arc section 17. The concave arc section 17 is smoothly connected to the cylindrical section 15 through the convex arc section 16. The outer surface of the isolation section 7 is in contact with the outer surface of the concave arc section 17, and the bottom of the isolation section 7 is in contact with the inner surface of the aircraft shell 1.

[0040] like Figure 7 As shown. The inner wall of the inner shell 2 is subjected to the pressure P exerted by the gas inside it, the outer wall of the cylindrical section 15 is subjected to the support force f1 provided by the outer shell 1 of the aircraft, and the lower part of the concave arc section 17 is subjected to the support force f2 provided by the isolation section 7. Therefore, after comprehensive consideration, in fact, only the convex arc section 16 of the inner shell 2 is subjected to the effect of the air pressure P. This pressure will be converted into the pulling force of the convex arc section 16 on the concave arc section 17 and the pulling force of the cylindrical section 15, which is conducive to improving the stability of the inner shell 2, thereby helping to reduce the thickness of the inner shell 2 and reduce the weight of the inner shell 2.

[0041] The radius of the concave arc segment 17 is determined by the outer diameter of the engine isolation section 7, and the size of the center angle of the concave arc segment 17 is determined by the cross-sectional space utilization of the fuel tank. If the cross-sectional space utilization is required to be high, the center angle of the concave arc segment 17 should be larger. The thickness of the convex arc segment 16 is generally consistent with the thickness of the concave arc segment 17 to facilitate processing. The radius of the convex arc segment 16 is determined by the space utilization of the fuel tank and the design pressure of the pressure tank. If the cross-sectional space utilization is required to be high, the radius of the convex arc segment 16 should be a larger value; if the design pressure of the pressure tank is high, the radius of the convex arc segment 16 should be a smaller value.

[0042] like Figure 8 The isolation segment 7 is subjected to the pressure f2' applied by the concave arc segment 17 and the support force F provided by the front cover 5 and the rear cover 6. The isolation segment 7 converts the pressure to the aircraft shell 1, which is beneficial to improving the strength of the isolation segment 7 and also beneficial to the lightweight design of the isolation segment 7.

[0043] The front cover 5 is provided with a vent pipe 10, which is used to discharge the gas in the inner shell 2, so as to fill the fuel bag 3 with fuel. The rear cover 6 is provided with an air inlet pipe 11, which is convenient for introducing gas into the inner shell 2, applying a squeezing force to the fuel bag 3, and facilitating the discharge of fuel in the fuel bag 3.

[0044] A pipeline cavity 12 for arranging pipelines is provided between the isolation section 7, the inner shell 2 and the aircraft outer shell 1.

[0045] The method for using the above-mentioned aircraft pressure oil tank comprises the following steps:

[0046] S1. Open the oil inlet valve on the oil inlet and outlet joint 9, open the valve of the vent pipe 10, and close the valve of the air inlet pipe 11; inject fuel into the oil bag 3 through the oil inlet and outlet joint 9 and the oil pipe 4, the oil bag 3 expands, and the gas in the inner shell 2 is discharged from the inner shell 2 through the vent pipe 10.

[0047] S2. After the fuel filling is completed, the oil inlet valve on the oil inlet and outlet joint 9 is closed, the exhaust pipe valve is closed, the oil outlet valve on the oil inlet and outlet joint 9 is opened, and the valve of the air inlet pipe 11 is opened. Gas is introduced into the inner shell 2 through the air inlet pipe 11, and the gas exerts a squeezing force on the oil bag 3, and the fuel in the oil bag 3 is sent to the downstream pipeline through the oil pipe 4 and the oil inlet and outlet joint 9.

[0048] Therefore, by adopting the aircraft pressure fuel tank and the method of using the same as described in the present invention, the structure of the fuel tank is optimized, the space utilization of the aircraft is improved, the weight of the fuel tank is reduced, and the fuel capacity of the fuel tank is increased.

[0049] Finally, it should be noted that the above embodiments are only used to illustrate the technical solution of the present invention rather than to limit it. Although the present invention has been described in detail with reference to the preferred embodiments, those skilled in the art should understand that they can still modify or replace the technical solution of the present invention with equivalents, and these modifications or equivalent replacements cannot cause the modified technical solution to deviate from the spirit and scope of the technical solution of the present invention.

Claims

1. An aircraft pressure oil tank, characterized in that: It includes an inner shell, which is arranged inside the outer shell of the aircraft, and the two ends of the inner shell are respectively and sealedly fixed with a front cover and a rear cover, and the front cover and the rear cover are both fixed on the outer shell of the aircraft, an oil bag is arranged inside the inner shell, and the two ends of the oil bag are respectively fixed on the front cover and the rear cover, an oil pipe is arranged inside the oil bag, and a plurality of oil holes are arranged on the oil pipe, an oil inlet and outlet joints connected with the oil pipe are arranged on the rear cover, a ventilation pipe is arranged on the front cover, and an air intake pipe is arranged on the rear cover, and an isolation section is arranged inside the outer shell of the aircraft, and the isolation section is in contact with both the inner shell and the outer shell of the aircraft.

2. The aircraft pressure oil tank according to claim 1, characterized in that: Both ends of the isolation section are provided with ear plates, and the isolation section is fixedly connected to the front end cover and the rear end cover through the ear plates.

3. The aircraft pressure oil tank according to claim 1, characterized in that: The inner shell includes a main body, and sealing baffles are fixedly arranged at both ends of the main body. The thickness and width of the sealing baffles are not less than the thickness and width of the main body. Reinforcing ribs are arranged between the main body and the sealing baffles. The main body is sealed and fixedly connected with the front cover and the rear cover through the sealing baffles.

4. The aircraft pressure oil tank according to claim 3, characterized in that: The main body comprises a cylindrical section, a corrugated section is arranged at the lower part of the cylindrical section, the outer surface of the cylindrical section is fitted with the inner surface of the aircraft shell, and the middle outer surface of the corrugated section is fitted with the outer surface of the isolation section.

5. The aircraft pressure oil tank according to claim 4, characterized in that: The corrugated section includes a convex arc section and a concave arc section, the convex arc section is located on both sides of the concave arc section, the concave arc section is connected to the cylindrical section through the convex arc section, and the outer surface of the isolation section is in contact with the outer surface of the concave arc section.

6. The aircraft pressure oil tank according to claim 3, characterized in that: The main body is an outer wall with uniform thickness.

7. The aircraft pressure oil tank according to claim 1, characterized in that: One end of the oil bag is fixed to the center of the front end cover through a fixed joint, the other end of the oil bag is fixed to the center of the rear end cover, and the oil inlet and outlet joints are located at the center of the rear end cover.

8. The aircraft pressure oil tank according to claim 1, characterized in that: A pipeline cavity for arranging pipelines is arranged between the isolation section, the inner shell and the aircraft outer shell.

9. The aircraft pressure oil tank according to claim 1, characterized in that: The length of the oil pipe is greater than the length of the inner shell, the density of the oil pipe is not less than the density of the fuel, and the oil pipe is a hose.

10. A method for using an aircraft pressure oil tank according to any one of claims 1 to 9, characterized in that: The following steps are involved: S1. Open the oil inlet valve on the oil inlet and outlet joints, open the vent pipe valve, close the air inlet pipe valve, inject fuel into the oil bag through the oil inlet and outlet joints and the oil pipe, the oil bag expands, and the gas in the inner shell is discharged from the inner shell through the vent pipe; S2. After the fuel filling is completed, close the oil inlet valve on the oil inlet and outlet joints, close the exhaust pipe valve, open the oil outlet valve on the oil inlet and outlet joints, open the intake pipe valve, and introduce gas into the inner shell through the intake pipe. The gas exerts squeezing force on the oil bag, and the fuel in the oil bag is sent to the downstream pipeline through the oil pipe and the oil inlet and outlet joints.

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