Oil tank cabin

Abstract

The utility model belongs to the technical field of aviation, and particularly relates to an oil tank cabin which comprises a front web plate located on the axial front side of an aircraft body, a rear web plate located on the axial rear side and a side wall connected between the front web plate and the rear web plate. The front web, the rear web and the side wall form an oil tank cabin; wherein the side wall comprises a plurality of discrete side walls which are distributed in the circumferential direction, the edges of the discrete side walls are bent outwards by 90 degrees to form connecting edges, and the adjacent discrete side walls are fixedly connected through the connecting edges; an inlet and outlet cover (15) and an oil drainage precipitation tank (14) formed in a sunken mode are arranged below the side wall, and an oil filling port (16) is formed above the side wall.

Description

TECHNICAL FIELD

[0001] The application belongs to the field of aviation technology, and particularly relates to an oil tank cabin. BACKGROUND

[0002] The oil tank cabin is a cabin for hanging and placing a soft oil tank or an integral oil tank, is repeatedly acted on by oil pressure, fully utilizes space, increases oil storage capacity, and can increase the range of an airplane. Structural arrangement guarantees the maximum utilization of the oil tank cabin, reduces protruding pieces in the cabin, and influences of fuel on structural strength and requirements of structural forms. How to guarantee that fuel in the oil tank does not leak, how reliable is the sealing process and how convenient is construction, and anticorrosion of the structure. Therefore, necessary requirements are proposed for the design of the oil tank cabin, so as to guarantee that the oil tank cabin realizes the functions of containing oil, refueling, discharging sediments, personnel access, installation and maintenance, and the structure is light in weight and the skin does not collapse. SUMMARY

[0003] In order to solve the above problems, the application provides an oil tank cabin, comprising,

[0004] a front web plate located at an axial front side of an airplane fuselage, a rear web plate located at an axial rear side, and a side wall connected between the front web plate and the rear web plate;

[0005] The front web plate, the rear web plate and the side wall form the oil tank cabin.

[0006] The side wall comprises a plurality of circumferentially distributed discrete side walls, edges of the discrete side walls are bent outward by 90 degrees to form connecting edges, and adjacent discrete side walls are fixedly connected through the connecting edges.

[0007] An inlet and outlet cover and a discharge sediment groove formed by recessing are arranged below the side wall, and a refueling port is arranged above the side wall.

[0008] Preferably, a flexible film is arranged in the oil tank cabin and used for containing fuel.

[0009] Preferably, a surrounding frame is arranged at an axial middle position of the side wall and used for improving the strength of the side wall.

[0010] Preferably, the discrete side walls comprise an upper side wall, a left upper side wall, a middle upper side wall, a middle lower side wall, a lower side wall and a lower wall.

[0011] The two lower side walls and the lower wall form a U-shaped bottom, two edges of the U-shaped bottom are connected with the two middle lower side walls, the two middle lower side walls are respectively connected with the two middle upper side walls, the two middle upper side walls are respectively connected with the two left upper side walls upward, and the two left upper side walls are connected on two sides of the upper side wall.

[0012] Preferably, a middle lower longitudinal stiffener is arranged at the joint of the middle lower side wall and the lower side wall, a middle upper longitudinal stiffener is arranged at the joint of the middle lower side wall and the middle upper side wall, the left upper side wall is divided into a horizontally arranged front half and a downwardly inclined rear half at the frame, an upper front longitudinal stiffener and an upper rear longitudinal stiffener are arranged at the joint of the front half and the rear half of the left upper side wall and the middle upper side wall, and a lower stiffener is arranged between the lower side wall and the lower wall.

[0013] Preferably, triangular reinforcing pieces are arranged on the lower wall, and hexagonal reinforcing pieces are arranged on the middle upper side wall, so as to increase the structural strength.

[0014] The advantages of the present application include that the present application forms a complete internal fuel tank cabin without protruding components, the fuel tank cabin is formed by the front web and the rear web of the fuselage itself, and the soft fuel tank is formed by a film, and the soft fuel tank in the fuel tank cabin stores fuel. BRIEF DESCRIPTION OF DRAWINGS

[0015] Figure 1 is a schematic view of a side wall of a fuel tank cabin according to a preferred embodiment of the present application. DETAILED DESCRIPTION

[0016] In order to make the technical solutions of the present application and the advantages thereof clearer, the technical solutions of the present application will be further described in detail below with reference to the drawings, and it should be understood that the specific embodiments described herein are only part of the embodiments of the present application, and are only used to explain the present application, but not to limit the present application. It should be noted that, for the purpose of description, only parts related to the present application are shown in the drawings, and other related parts can be referred to the general design. In the case of no conflict, the embodiments in the present application and the technical features in the embodiments can be combined to obtain new embodiments.

[0017] As shown in Figure 1 , the present application provides a fuel tank cabin, comprising,

[0018] a front web arranged at an axial front side of a fuselage, a rear web arranged at an axial rear side of the fuselage, and a side wall connected between the front web and the rear web;

[0019] the front web, the rear web and the side wall form the fuel tank cabin;

[0020] wherein the side wall comprises a plurality of circumferentially distributed discrete side walls, edges of the discrete side walls are bent outwardly by ninety degrees to form connecting edges, and adjacent discrete side walls are fixedly connected through the connecting edges;

[0021] The lower part of the side wall is provided with an inlet and outlet cover 15 and a recessed oil draining tank 14, and the upper part of the side wall is provided with a fuel inlet 16. The inlet and outlet cover 15 is located at the lower part and has a size according to the size of the personnel to facilitate the personnel to enter the fuel tank cabin for construction and maintenance. The oil draining tank 14 is made of corrosion-resistant stainless steel welding parts and is installed at the lowest part of the fuel tank cabin to easily drain the precipitates. The fuel inlet 16 is located at the top to facilitate gravity fueling.

[0022] Preferably, a flexible film is arranged in the fuel tank cabin, i.e. a soft fuel tank, for containing fuel.

[0023] Preferably, the axial middle part of the side wall has a surrounding frame 17 for improving the strength of the side wall. The surrounding frame 17 is formed by sheet metal and maintains the shape of the fuel tank cabin and the skin.

[0024] Preferably, the discrete side wall includes an upper side wall 1, a left upper side wall 3, a middle upper side wall 6, a middle lower side wall 8, a lower side wall 10 and a lower wall 12.

[0025] The two lower side walls 10 and the lower wall 12 form a U-shaped bottom, the two edges of the U-shaped bottom are connected to the two middle lower side walls 8, the two middle lower side walls 8 are respectively connected to the two middle upper side walls 6, the two middle upper side walls 6 are respectively connected to the two left upper side walls 3 upwards, and the two left upper side walls 3 are connected to the two sides of the upper side wall 1.

[0026] Preferably, a middle lower longitudinal reinforcing member 9 is arranged at the connection between the middle lower side wall 8 and the lower side wall 10, a middle upper longitudinal reinforcing member 7 is arranged at the connection between the middle lower side wall 8 and the middle upper side wall 6, the left upper side wall 3 is divided into a front half part arranged horizontally and a rear half part arranged downwardly at the surrounding frame 17, an upper front longitudinal reinforcing member 2 and an upper rear longitudinal reinforcing member 4 are arranged at the connections between the front half part and the rear half part of the left upper side wall 3 and the middle upper side wall 6, and a lower reinforcing member 11 is arranged between the lower side wall 10 and the lower wall 12. The reinforcing members are all strip-shaped reinforcing ribs matched with the connections of the side wall and are fixed by riveting.

[0027] Preferably, a triangular reinforcing piece 13 is arranged on the lower wall 12 and a hexagonal reinforcing piece 5 is arranged on the middle upper side wall 6 to increase the structural strength. The hexagonal reinforcing piece 5 and the triangular reinforcing piece 13 are arranged at the intersections of the components or the strength reinforcing positions of the longitudinal and transverse parts.

[0028] The advantages of the present application include that the present application forms a complete internal fuel tank cabin without protruding components, the fuel tank cabin is formed by the front and rear webs of the fuselage itself and is located in the cabin, and a soft fuel tank is arranged inside to contain fuel.

[0029] The above merely provides the specific implementation of the present application, but the protection scope of the present application is not limited to this. Any person skilled in the art can easily think of the changes or replacements within the technical range disclosed by the present application, which should be covered in the protection scope of the present application. Therefore, the protection scope of the present application should be subject to the protection scope of the claims.

Claims

1. A fuel tank compartment, characterized in that, include, The front web is located on the axially forward side of the aircraft fuselage, the rear web is located on the axially rear side, and the sidewall connects the front web and the rear web. The anterior and posterior webs and sidewalls form the fuel tank compartment; The sidewalls include multiple circumferentially distributed discrete sidewalls, the edges of which are bent outward at a 90-degree angle to form connecting edges, and adjacent discrete sidewalls are fixedly connected by the connecting edges. The lower part of the side wall is provided with an inlet / outlet cover (15) and an oil settling tank (14) formed by a recess, and the upper part of the side wall is provided with an oil filling port (16).

2. The fuel tank compartment as described in claim 1, characterized in that, A flexible membrane is installed inside the fuel tank to hold the fuel.

3. The fuel tank compartment as described in claim 1, characterized in that, The sidewall has a frame (17) at the axial midpoint to enhance its strength.

4. The fuel tank compartment as described in claim 3, characterized in that, The discrete sidewalls include: upper sidewall (1), upper left sidewall (3), upper middle sidewall (6), lower middle sidewall (8), lower sidewall (10), and lower wall (12); Among them, two lower sidewalls (10) and one lower wall (12) form a U-shaped bottom. The two edges of the U-shaped bottom are connected to two middle lower sidewalls (8). The middle lower sidewalls (8) on both sides are connected to the middle upper sidewalls (6) on both sides respectively. The middle upper sidewalls (6) on both sides are connected upward to the left upper sidewalls (3) on both sides respectively. The left upper sidewalls (3) on both sides are connected to the two sides of one upper sidewall (1).

5. The fuel tank compartment as described in claim 4, characterized in that, There is a lower longitudinal reinforcement (9) at the connection between the lower side wall (8) and the lower side wall (10), and there is an upper longitudinal reinforcement (7) at the connection between the lower side wall (8) and the upper side wall (6). The upper left side wall (3) is divided into a horizontally arranged front half and a downwardly inclined rear half in the frame (17). There is an upper front longitudinal reinforcement (2) and an upper rear longitudinal reinforcement (4) at the connection between the front half and the rear half of the upper left side wall (3) and the upper side wall (6). There is a lower reinforcement (11) between the lower side wall (10) and the lower wall (12).

6. The fuel tank compartment as described in claim 4, characterized in that, A triangular reinforcing plate (13) is provided on the lower wall (12), and a hexagonal reinforcing plate (5) is provided on the upper middle side wall (6) to increase the structural strength.

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