Aircraft fuselage fuel tank and machining and assembling method thereof

Abstract

The invention belongs to the technical field of aircraft fuselage fuel tank design, and particularly relates to an aircraft fuselage fuel tank and a machining and assembling method thereof.The aircraft fuselage fuel tank mainly comprises a barrel, a first end socket, a second end socket and a maintenance opening cover, and the barrel, the first end socket, the second end socket and the maintenance opening cover are designed to be of an integrally-formed structure and are large-size components, so that the number of small components is reduced, and the cost is reduced. In addition, the bottom of the side wall of the cylinder is designed to be provided with a convex pump cabin used for arranging an oil suction pump, so that an inlet of the oil suction pump can be always kept lower than the liquid level in the oil tank, the utilization rate of oil in the oil tank can be increased, the residual oil amount is reduced, and the service life of the oil tank is prolonged. And the arrangement position of the convex pump cabin is close to the second sealing head, and after the maintenance opening cover is detached, the oil suction pump can be conveniently maintained through the maintenance window.

Description

Technical Field

[0001] The present application belongs to the technical field of aircraft fuselage fuel tank design, and specifically relates to an aircraft fuselage fuel tank and a processing and assembly method thereof. Background Art

[0002] At present, most aircraft fuselage fuel tanks are designed to be closed structures by connecting multiple small parts with fasteners or welding. This technical solution has the following defects: 1) There are many connection parts, and the sealing and reliability are poor; 2) The built-in oil suction pump design lacks obvious low points, resulting in low utilization of the oil in the tank and a large amount of residual oil.

[0003] This application is proposed in view of the above-mentioned technical defects. Summary of the invention

[0004] The purpose of the present application is to provide an aircraft fuselage fuel tank and a processing and assembly method thereof, so as to overcome or alleviate at least one aspect of the known technical defects.

[0005] The technical solution of this application is: On the one hand, an aircraft fuselage fuel tank is provided, comprising a cylinder, a first end cap, a second end cap, and a maintenance cover; The cylinder is an integrally formed structure, and the bottom of the side wall has an outward convex pump cabin for arranging the oil suction pump; The first end cap is an integrally formed structure, which is welded to one end of the cylinder to seal the end of the cylinder; The second end cap is an integrally formed structure with a maintenance window thereon, which is welded to the other end of the cylinder to seal the end of the cylinder, and the outward convex pump chamber is close to the end of the cylinder; The maintenance cover is an integrally formed structure, which is threadedly connected to the second head to seal the maintenance window.

[0006] Optionally, in the above-mentioned aircraft fuselage fuel tank, the cylinder, the first head and the second head are made of thick plates as raw materials, formed by a spinning process, and subjected to secondary processing to meet dimensional accuracy requirements.

[0007] Optionally, in the above-mentioned aircraft fuselage fuel tank, a plurality of full ring frames distributed along the axial direction are welded on the inner side of the cylinder body, and a plurality of circles of small arc frames distributed along the axial direction are welded.

[0008] Optionally, in the above-mentioned aircraft fuselage fuel tank, each full annular frame and each circle of small arc-shaped frames are spaced apart in the axial direction.

[0009] Optionally, in the above-mentioned aircraft fuselage fuel tank, the cross-sections of each full annular frame and each circle of small arc-shaped frames are in an I-shape.

[0010] Optionally, in the above-mentioned aircraft fuselage fuel tank, reinforcing ribs are provided on the inner sides of the first head and the second head.

[0011] Optionally, in the above-mentioned aircraft fuselage fuel tank, the first head, the second head and the inner reinforcing ribs are welded together.

[0012] Optionally, in the above-mentioned aircraft fuselage fuel tank, the reinforcing ribs on the inner sides of the first head and the second head are annular.

[0013] Optionally, in the above-mentioned aircraft fuselage fuel tank, the reinforcing ribs on the inner sides of the first head and the second head are radially shaped.

[0014] On the other hand, a method for machining and assembling an aircraft fuselage fuel tank is provided, which is used to realize the machining and assembling of the aircraft fuselage fuel tank, comprising: The cylinder is formed by spinning process using thick plate as raw material, and secondary processing is performed to meet the dimensional accuracy requirements; Multiple full-ring frames distributed along the axial direction are welded on the inner side of the cylinder, as well as multiple circles of small arc frames distributed along the axial direction, and an oil suction pump is arranged in the outer convex pump room; The first and second heads are formed by spinning process using thick plates as raw materials, and secondary processing is performed to meet the dimensional accuracy requirements; Annular or radial reinforcing ribs are welded on the inner sides of the first head and the second head; The first end cap and the second end cap are welded to the two ends of the cylinder to seal the two ends of the cylinder, wherein the second end cap is close to the convex pump chamber; Thread the maintenance cover onto the second end cap to seal the maintenance window.

[0015] This application has at least the following beneficial technical effects: The aircraft fuselage fuel tank connection processing and assembly method disclosed in the above-mentioned embodiment is designed to mainly include a cylinder, a first head, a second head, and a maintenance cover, and the cylinder, the first head, the second head, and the maintenance cover are designed to be an integrally formed structure, which are larger-sized components, thereby reducing the number of small components, and then reducing the number of connecting parts, thereby improving the sealing and reliability of the aircraft fuselage fuel tank. In addition, the bottom of the side wall of the cylinder is designed to have an outward convex pump cabin for arranging an oil suction pump, so that the inlet of the oil suction pump can always be kept lower than the liquid level in the tank, thereby improving the utilization rate of the oil in the tank and reducing the amount of residual oil. The outward convex pump cabin is set close to the second head. After removing the maintenance cover, the oil suction pump can be conveniently maintained through the maintenance window. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 is a schematic diagram of an aircraft fuselage fuel tank provided in an embodiment of the present application; in: 1- cylinder body; 2- first end cap; 3- second end cap; 4- maintenance cover; 5- full annular frame; 6- small arc frame.

[0017] In order to better illustrate the present embodiment, some parts of the drawings may be omitted, enlarged or reduced, and do not represent the size of the actual product. In addition, the drawings are only used for illustrative purposes and should not be construed as limitations on the present application. DETAILED DESCRIPTION

[0018] In order to make the technical solution and advantages of the present application clearer, the technical solution of the present application will be described in further detail in detail and in detail with reference to the accompanying drawings. It can be understood that the specific embodiments described here are only partial embodiments of the present application, which are only used to explain the present application, not to limit the present application. It should be noted that, for the convenience of description, only the parts related to the present application are shown in the accompanying drawings, and other related parts can refer to the general design.

[0019] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application shall have the usual meanings understood by those of ordinary skill in the art to which this application belongs. The words used in the description of this application to indicate orientation are only used to indicate relative directions or positional relationships. When the absolute position of the described object changes, its relative positional relationship may also change accordingly. The word "include" used in the description of this application indicates that the elements or objects appearing before the word include the elements or objects listed after the word and their equivalents, but does not exclude other elements or objects.

[0020] In addition, it should be noted that, unless otherwise clearly specified and limited, the words "installation", "connection" and similar terms used in the description of this application should be understood in a broad sense. For example, the connection can be a fixed connection or a detachable connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium. Technical personnel in the field can understand its specific meaning in this application according to the specific circumstances.

[0021] On the one hand, an aircraft fuselage fuel tank is provided, such as Figure 1 As shown, it includes a cylinder 1, a first head 2, a second head 3, and a maintenance cover 4; The cylinder 1 is an integrally formed structure, and the bottom of the side wall has a convex pump cabin for arranging the oil suction pump; the side wall of the cylinder 1 can be provided with holes for the pipeline to pass through, as well as interfaces for the installation of various temperature, pressure, liquid level and other instruments; The first end cap 2 is an integrally formed structure, which is welded to one end of the cylinder 1, or can be connected with a fastener to seal the end of the cylinder 1; The second end cap 3 is an integrally formed structure with a maintenance window thereon, which is welded to the other end of the cylinder 1, or can be connected with fasteners to seal the end of the cylinder 1, and the outward convex pump chamber is close to the end of the cylinder 1; The maintenance cover 4 is an integrally formed structure, which is threadedly connected to the second head 3, and can also be connected by bolts to block the maintenance window.

[0022] The aircraft fuselage fuel tank disclosed in the above-mentioned embodiment is mainly designed to include a cylinder 1, a first head 2, a second head 3, and a maintenance cover 4, and the cylinder 1, the first head 2, the second head 3, and the maintenance cover 4 are designed to be an integrally formed structure, which is a larger-sized component, thereby reducing the number of small components, and then reducing the number of connecting parts, thereby improving the sealing and reliability of the aircraft fuselage fuel tank. In addition, the bottom of the side wall of the cylinder 1 is designed to have an outward convex pump cabin for arranging an oil suction pump, so that the inlet of the oil suction pump can always be kept lower than the liquid level in the tank, thereby improving the utilization rate of the oil in the tank and reducing the amount of residual oil, and the outward convex pump cabin is set close to the second head 3. After removing the maintenance cover 4, the oil suction pump can be conveniently maintained through the maintenance window.

[0023] In some optional embodiments, in the above-mentioned aircraft fuselage fuel tank, the cylinder 1, the first head 2, and the second head 3 are made of thick plates as raw materials, formed by a spinning process, and subjected to secondary processing to meet dimensional accuracy requirements.

[0024] In some optional embodiments, in the above-mentioned aircraft fuselage fuel tank, multiple full-ring frames 5 distributed along the axial direction are welded on the inner side of the cylinder 1, and multiple circles of small arc frames 6 distributed along the axial direction are welded; Each full annular frame 5 and each circle of small arc-shaped frame 6 are spaced apart in the axial direction; The cross sections of each full annular frame 5 and each circle of small arc-shaped frame 6 are in an I-shape.

[0025] In the aircraft fuselage fuel tank disclosed in the above-mentioned embodiment, a plurality of full annular frames 5 distributed along the axial direction are welded on the inner side of the cylinder body 1, and the full annular frames 5 can effectively support and maintain the overall shape of the cylinder body 1 and the fuel tank. A plurality of circles of small arc frames 6 distributed along the axial direction are welded on the inner side of the cylinder body 1, which can assist in supporting and maintaining the overall shape of the cylinder body 1 and the fuel tank, and can reduce the increase in the overall mass of the fuel tank. The cross-sections of each full annular frame 5 and each circle of small arc frames 6 are designed to be I-shaped, which can effectively reduce the shaking of the oil in the fuel tank.

[0026] In some optional embodiments, in the above-mentioned aircraft fuselage fuel tank, Reinforcing ribs are welded inside the first head 2 and the second head 3; The reinforcing ribs on the inner sides of the first head 2 and the second head 3 are annular or radial, so as to enhance the rigidity of the first head 2 and the second head 3.

[0027] On the other hand, a method for machining and assembling an aircraft fuselage fuel tank is provided, which is used to realize the machining and assembling of the aircraft fuselage fuel tank, comprising: The cylinder 1 is formed by spinning process using thick plate as raw material, and secondary processing is performed to meet the dimensional accuracy requirements; A plurality of full-ring frames 5 distributed along the axial direction are welded on the inner side of the cylinder 1, and a plurality of small arc frames 6 distributed along the axial direction are welded, and an oil suction pump is arranged in the outer convex pump room; The first head 2 and the second head 3 are formed by using a spinning process with a thick plate as the raw material, and then the secondary processing is performed to meet the dimensional accuracy requirements; Annular or radial reinforcing ribs are welded inside the first head 2 and the second head 3; The first end cap 2 and the second end cap 3 are welded to the two ends of the cylinder 1 to seal the two ends of the cylinder 1, wherein the second end cap 3 is close to the convex pump chamber; The maintenance cover 4 is threadedly connected to the second head 3 to block the maintenance window.

[0028] The aircraft fuselage fuel tank processing and assembly method disclosed in the above-mentioned embodiment is used to realize the processing and assembly of the aircraft fuselage fuel tank disclosed in the above-mentioned embodiment. The description is relatively simple. For specific related matters, please refer to the relevant description of the aircraft fuselage fuel tank part. Its technical effects can also refer to the technical effects of the relevant parts of the aircraft fuselage fuel tank, which will not be repeated here.

[0029] The various embodiments in the specification are described in a progressive manner, and each embodiment focuses on the differences from other embodiments. The same or similar parts between the various embodiments can be referenced to each other. In the absence of conflict, the embodiments in this application and the technical features in the embodiments can be combined with each other to obtain new embodiments.

[0030] So far, the technical solution of the present application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of the present application is obviously not limited to these specific embodiments. Without departing from the principles of the present application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will fall within the scope of protection of the present application.

Claims

1. An aircraft fuselage fuel tank, characterized in that: It comprises a cylinder (1), a first end cap (2), a second end cap (3), and a maintenance cover (4); The cylinder (1) is an integrally formed structure, and the bottom of the side wall is provided with an outwardly convex pump cabin for arranging an oil suction pump; The first end cap (2) is an integrally formed structure and is welded to one end of the cylinder (1) to seal the end of the cylinder (1); The second end cap (3) is an integrally formed structure having a maintenance window thereon and is welded to the other end of the cylinder (1) to seal the end of the cylinder (1), and the outwardly convex pump chamber is close to the end of the cylinder (1); The maintenance cover (4) is an integrally formed structure and is threadedly connected to the second head (3) to seal the maintenance window.

2. The aircraft fuselage fuel tank according to claim 1, characterized in that: The cylinder (1), the first end cap (2) and the second end cap (3) are made of thick plates and are formed by a spinning process, and are subjected to secondary processing to meet dimensional accuracy requirements.

3. The aircraft fuselage fuel tank according to claim 2, characterized in that: The inner side of the cylinder (1) is welded with a plurality of full annular frames (5) distributed along the axial direction, and a plurality of small arc frames (6) distributed along the axial direction.

4. The aircraft fuselage fuel tank according to claim 3, characterized in that: Each full annular frame (5) and each circle of small arc-shaped frame (6) are spaced apart in the axial direction.

5. The aircraft fuselage fuel tank according to claim 4, characterized in that: The cross sections of each full annular frame (5) and each circle of small arc-shaped frame (6) are in an I-shape.

6. The aircraft fuselage fuel tank according to claim 5, characterized in that: Reinforcing ribs are arranged on the inner sides of the first end cap (2) and the second end cap (3).

7. The aircraft fuselage fuel tank according to claim 6, characterized in that: The first end cap (2), the second end cap (3) and the inner reinforcing ribs are connected by welding.

8. The aircraft fuselage fuel tank according to claim 7, characterized in that: The reinforcing ribs on the inner sides of the first end cap (2) and the second end cap (3) are in the shape of a ring.

9. The aircraft fuselage fuel tank according to claim 8, characterized in that: The reinforcing ribs on the inner sides of the first end cap (2) and the second end cap (3) are radially shaped.

10. A method for machining and assembling an aircraft fuselage fuel tank, for realizing the machining and assembling of the aircraft fuselage fuel tank as claimed in claim 9, characterized in that: include: The cylinder (1) is formed by spinning process using thick plate as raw material, and secondary processing is performed to meet the dimensional accuracy requirements; A plurality of full-ring frames (5) distributed along the axial direction are welded on the inner side of the cylinder (1), and a plurality of small arc frames (6) distributed along the axial direction are welded, and an oil suction pump is arranged in the outer convex pump room; Using thick plates as raw materials, a first end cap (2) and a second end cap (3) are formed by a spinning process, and secondary processing is performed to meet dimensional accuracy requirements; Annular or radial reinforcing ribs are welded on the inner sides of the first end cap (2) and the second end cap (3); The first end cap (2) and the second end cap (3) are welded to the two ends of the cylinder (1) to seal the two ends of the cylinder (1), wherein the second end cap (3) is close to the convex pump chamber; The maintenance cover (4) is threadedly connected to the second head (3) to seal the maintenance window.

Images