Cable connection structure for auxiliary fuel tank of airplane

Abstract

The utility model relates to the technical field of airplane auxiliary fuel tank electric equipment, in particular to an airplane auxiliary fuel tank cable connection structure, which comprises a functional mounting seat, a plug seat and a cable tube. The cable pipe is arranged in the airplane auxiliary fuel tank, one end of the cable pipe is connected with the connector assembly, the other end of the cable pipe is connected with the functional installation seat, the wind resistance coefficient of the airplane auxiliary fuel tank is reduced, it is guaranteed that an electric power system is not prone to being interfered in the strong electromagnetic environment, and the electromagnetic compatibility of the airplane auxiliary fuel tank is improved; the temperature in the cable pipe is prevented from being too high by arranging the heat insulation inner pipe, the shielding effectiveness and the electromagnetic compatibility of the aircraft auxiliary fuel tank system are further improved by arranging the shielding inner pipe, the fuel in the aircraft auxiliary fuel tank is prevented from making contact with the cable by arranging the protection outer pipe, and the reliability of the aircraft auxiliary fuel tank is improved; the welding part is arranged on the plug seat, so that the cable outlet and the cable tube are packaged, and fuel oil is prevented from entering a plug of electric equipment.

Description

Technical Field

[0001] The utility model relates to the technical field of electrical equipment for aircraft auxiliary fuel tanks, in particular to a cable connection structure for aircraft auxiliary fuel tanks. Background Art

[0002] At present, in order to facilitate the maintenance of the control part of the electrical equipment of the auxiliary fuel tank of domestic aircraft and isolate the contact between fuel and cables, the control part of the electrical equipment of the auxiliary fuel tank is arranged outside the auxiliary fuel tank, and its cables need to be arranged along the outside of the auxiliary fuel tank.

[0003] In actual use, the cables of the auxiliary fuel tank's electrical equipment are arranged outside the auxiliary fuel tank, and it is necessary to add sleeves and multiple cable fixing devices, which makes the auxiliary fuel tank structure complicated, increases the wind resistance coefficient of the auxiliary fuel tank, and reduces reliability; and when used in a strong electromagnetic environment, the entire power system is easily interfered, resulting in electrical signal distortion. The reason is that the cables of the auxiliary fuel tank's electrical equipment are arranged outside the auxiliary fuel tank. Utility Model Content

[0004] Aiming at the problem that the cables of the above-mentioned aircraft auxiliary fuel tank are arranged outside the auxiliary fuel tank, resulting in a complex structure of the auxiliary fuel tank and being easily interfered with, the utility model proposes an aircraft auxiliary fuel tank cable connection structure, comprising a functional mounting seat, a plug seat, and a cable tube; by arranging the cable tube in the aircraft auxiliary fuel tank, connecting one end of the cable tube to the plug seat and the other end to the functional mounting seat, the wind resistance coefficient of the aircraft auxiliary fuel tank is reduced, ensuring that the power system is not easily interfered with in a strong electromagnetic environment, and improving the electromagnetic compatibility of the aircraft auxiliary fuel tank.

[0005] The specific implementation contents of the utility model are as follows:

[0006] An aircraft auxiliary fuel tank cable connection structure, connected to the aircraft end; including a functional mounting seat, a plug seat, and a cable tube;

[0007] The functional mounting seat is fixedly connected to the aircraft auxiliary fuel tank, and the electrical equipment is arranged in the inner cavity of the functional mounting seat;

[0008] The plug socket is fixedly connected to the aircraft auxiliary fuel tank;

[0009] The cable tube is arranged in the aircraft auxiliary fuel tank, and one end of the cable tube is connected to the plug socket, and the other end of the cable tube is connected to the functional mounting socket;

[0010] The cable of the electric device is arranged in the cable tube, passes through the cable tube and is connected with the electric plug.

[0011] In order to better realize the utility model, further, the cable tube includes a heat-insulating inner tube, a shielding inner tube, and a protective outer tube;

[0012] The cables of the electrical equipment are arranged in the heat-insulating inner tube;

[0013] The inner wall of the shielding inner tube is closely connected to the outer wall of the heat-insulating inner tube;

[0014] The inner wall of the protective outer tube is fitted and connected to the outer wall of the shielding inner tube, and the outer wall of the protective outer tube is arranged in the aircraft auxiliary fuel tank.

[0015] In order to better realize the utility model, further, the shielding inner tube is an electromagnetic shielding heat shrink tube.

[0016] In order to better implement the utility model, further, the plug socket includes a first through hole arranged at the bottom and a second through hole arranged at the side;

[0017] The cable of the electrical equipment on the top of the aircraft auxiliary fuel tank passes through the cable tube and the first through hole and is connected to the electrical plug;

[0018] The cable of the electrical equipment at the bottom of the aircraft auxiliary fuel tank passes through the cable tube and the second through hole and is connected to the electric plug.

[0019] In order to better implement the utility model, further, the plug socket also includes a first welding portion and a second welding portion;

[0020] The cable tube is fixedly connected to the first through hole via a first welding portion, and the cable tube is fixedly connected to the second through hole via a second welding portion.

[0021] In order to better implement the present utility model, further, the first welding portion is a circular weld corresponding to the first through hole;

[0022] The second welding portion is a circular welding seam corresponding to the second through hole.

[0023] The utility model has the following beneficial effects:

[0024] (1) The utility model provides a cable tube inside the auxiliary fuel tank and arranges the cable inside the cable tube, thereby preventing the fuel in the auxiliary fuel tank from contacting the cable; one end of the cable tube is connected to the plug socket, and the other end is connected to the functional mounting socket, thereby reducing the wind resistance coefficient of the aircraft auxiliary fuel tank, ensuring that the power system is not easily interfered in a strong electromagnetic environment, and improving the electromagnetic compatibility of the aircraft auxiliary fuel tank.

[0025] (2) The utility model prevents the temperature inside the cable tube from being too high by providing an insulating inner tube, further improves the shielding effectiveness and electromagnetic compatibility of the aircraft auxiliary fuel tank system by providing a shielding inner tube, and prevents the fuel in the aircraft auxiliary fuel tank from contacting the cable by providing a protective outer tube, thereby improving the reliability of the aircraft auxiliary fuel tank.

[0026] (3) The utility model provides a welding portion on the plug socket to seal the cable outlet and the cable tube, thereby preventing fuel from entering the plug of the electrical equipment. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] Figure 1 It is a schematic diagram of the overall structure of the utility model connected with electrical equipment.

[0028] Figure 2 This is a partial enlarged schematic diagram of the connection between the electric socket and the cable tube provided by the utility model.

[0029] Figure 3 This is a schematic diagram of the cable tube and cable outlet packaging structure provided by the utility model.

[0030] Figure 4 The present invention is a schematic diagram of the specific structure of the cable tube provided by the utility model.

[0031] Among them, 1. cable, 2. aircraft auxiliary fuel tank, 3. cable pipe, 31. insulation inner tube, 32. shielding inner tube, 33. protective outer tube, 4. plug socket, 5. electrical equipment, 6. first through hole, 7. second through hole, 8. first welding part, 9. second welding part, 10. electric plug, 11. functional mounting socket. DETAILED DESCRIPTION

[0032] In order to more clearly illustrate the technical solutions of the embodiments of the utility model, the technical solutions in the embodiments of the utility model will be clearly and completely described below in conjunction with the drawings in the embodiments of the utility model. It should be understood that the described embodiments are only part of the embodiments of the utility model, not all of the embodiments, and therefore should not be regarded as limiting the scope of protection. Based on the embodiments of the utility model, all other embodiments obtained by ordinary technical personnel in this field without creative work are within the scope of protection of the utility model.

[0033] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "disposed", "connected", and "connected" 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 the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0034] Embodiment 1:

[0035] This embodiment provides an aircraft auxiliary fuel tank cable connection structure, such as Figure 1 As shown, it includes a functional mounting seat 11, a plug seat 4, and a cable tube 3;

[0036] The functional mounting seat 11 is fixedly connected to the aircraft auxiliary fuel tank 2, and the electrical equipment 5 is arranged in the inner cavity of the functional mounting seat 11;

[0037] The plug socket 4 is fixedly connected to the aircraft auxiliary fuel tank 2;

[0038] The cable tube 3 is arranged in the aircraft auxiliary fuel tank 2, and one end of the cable tube 3 is connected to the plug socket 4, and the other end is connected to the functional mounting socket 11;

[0039] The cable 1 of the electric device 5 is arranged in the cable tube 3 , and passes through the cable tube 3 to be connected to the electric plug 10 .

[0040] Working principle: In this embodiment, a cable tube 3 is arranged inside the aircraft auxiliary fuel tank 2, and the aircraft auxiliary fuel tank cable 1 is arranged inside the aircraft auxiliary fuel tank 2 through the cable tube 3, one end of the cable tube 3 is connected to the plug socket 4, and the other end is connected to the functional mounting socket 11, thereby reducing the wind resistance coefficient of the aircraft auxiliary fuel tank 2, ensuring that the power system is not easily interfered in a strong electromagnetic environment, and improving the electromagnetic compatibility of the aircraft auxiliary fuel tank 2.

[0041] Embodiment 2:

[0042] This embodiment is based on the above embodiment 1. Figure 4 As shown, the cable tube 3 includes a heat-insulating inner tube 31, a shielding inner tube 32, and a protective outer tube 33;

[0043] The cables of the electrical equipment 5 are arranged in the heat-insulating inner tube 31;

[0044] The inner wall of the shielding inner tube 32 is closely connected to the outer wall of the heat-insulating inner tube 31;

[0045] The inner wall of the protective outer tube 33 is fitted and connected to the outer wall of the shielding inner tube 32 , and the outer wall of the protective outer tube 33 is arranged in the aircraft auxiliary fuel tank 2 .

[0046] The shielding inner tube 32 of this embodiment is configured as an electromagnetic shielding heat shrink tube.

[0047] Working principle: This embodiment prevents the temperature inside the cable tube from being too high by providing an insulating inner tube 31, further improves the shielding effectiveness and electromagnetic compatibility of the aircraft auxiliary fuel tank system by providing a shielding inner tube 32, and prevents the fuel in the aircraft auxiliary fuel tank 2 from contacting the aircraft auxiliary fuel tank cable 1 by providing a protective outer tube 33, thereby improving the reliability of the aircraft auxiliary fuel tank.

[0048] The other parts of this embodiment are the same as those of the above-mentioned embodiment 1, and thus will not be described in detail.

[0049] Embodiment 3:

[0050] This embodiment is based on any one of the above embodiments 1 to 2. Figure 1 , Figure 2 , Figure 3 As shown, the plug socket 4 includes a first through hole 6 arranged at the bottom and a second through hole 7 arranged at the side;

[0051] The cable of the electrical equipment 5 on the top of the aircraft auxiliary fuel tank 2 passes through the cable tube 3 and the first through hole 6 and is connected to the electrical plug 10;

[0052] The cables of the electrical equipment 5 at the bottom of the aircraft auxiliary fuel tank 2 pass through the cable tube 3 and the second through hole 7 and are connected to the electrical plug 10 .

[0053] In order to better implement the utility model, further, the plug socket 4 also includes a first welding portion 8 and a second welding portion 9;

[0054] The cable tube 3 is fixedly connected to the first through hole 6 via a first welding portion 8 , and the cable tube 3 is fixedly connected to the second through hole 7 via a second welding portion 9 .

[0055] In order to better implement the present utility model, further, the first welding portion 8 is a circular weld corresponding to the first through hole 6;

[0056] The second welding portion 9 is a circular welding seam corresponding to the second through hole 7 .

[0057] Working principle: In this embodiment, a second through hole 7 and a first through hole 6 are respectively arranged on the side and the bottom of the electrical socket 4. The second through hole 7 arranged on the side is connected to the electrical equipment 5 on the top of the aircraft auxiliary fuel tank 2 through the aircraft auxiliary fuel tank cable 1, and the first through hole 6 arranged on the bottom is connected to the electrical equipment 5 at the bottom of the aircraft auxiliary fuel tank 2 through the aircraft auxiliary fuel tank cable 1, thereby ensuring the vertical positioning of multiple electrical equipment 5 and the electric plug 10 respectively, and by arranging a first welding portion 8 and a second welding portion 9 on the plug socket 4, the outlet of the aircraft auxiliary fuel tank cable 1 and the cable tube 3 are encapsulated, thereby preventing fuel from entering the electrical plug 10 of the electrical equipment 5, and ensuring the safety of the internally arranged cable tube 3 and the aircraft auxiliary fuel tank cable 1.

[0058] The other parts of this embodiment are the same as any of the above-mentioned embodiments 1-2, so they will not be repeated here.

[0059] The above description is only a preferred embodiment of the present invention and does not limit the present invention in any form. Any simple modification or equivalent changes made to the above embodiments based on the technical essence of the present invention shall fall within the protection scope of the present invention.

Claims

1. An aircraft auxiliary fuel tank cable connection structure, connected to an electrical plug (10); characterized in that: It comprises a functional mounting seat (11), a plug seat (4), a cable tube (3), and electrical equipment (5); The functional mounting seat (11) is fixedly connected to the aircraft auxiliary fuel tank (2), and the electrical equipment (5) is arranged in the inner cavity of the functional mounting seat (11); The plug socket (4) is fixedly connected to the aircraft auxiliary fuel tank (2); The cable tube (3) is arranged in the aircraft auxiliary fuel tank (2), and one end of the cable tube (3) is fixedly connected to the plug socket (4), and the other end of the cable tube (3) is fixedly connected to the functional mounting socket (11); The cable (1) of the electrical device (5) is arranged in the cable tube (3), passes through the cable tube (3) and is connected to the electrical plug (10).

2. The aircraft auxiliary fuel tank cable connection structure according to claim 1, characterized in that: The cable tube (3) comprises a heat-insulating inner tube (31), a shielding inner tube (32), and a protective outer tube (33); The cable (1) of the electrical equipment (5) is arranged in the heat-insulating inner tube (31); The inner wall of the shielding inner tube (32) is fitted and connected to the outer wall of the heat-insulating inner tube (31); The inner wall of the protective outer tube (33) is fitted and connected to the outer wall of the shielding inner tube (32), and the outer wall of the protective outer tube (33) is arranged in the aircraft auxiliary fuel tank (2).

3. The aircraft auxiliary fuel tank cable connection structure according to claim 2, characterized in that: The shielding inner tube (32) is an electromagnetic shielding heat shrink tube.

4. The aircraft auxiliary fuel tank cable connection structure according to claim 1, characterized in that: The plug socket (4) comprises a first through hole (6) arranged at the bottom and a second through hole (7) arranged at the side; The cable of the electrical equipment (5) on the top of the aircraft auxiliary fuel tank (2) passes through the cable tube (3), the first through hole (6) and is connected to the electrical plug (10); The cable of the electrical equipment (5) at the bottom of the aircraft auxiliary fuel tank (2) passes through the cable tube (3), the second through hole (7) and is connected to the electrical plug (10).

5. The aircraft auxiliary fuel tank cable connection structure according to claim 4, characterized in that: The plug socket (4) further comprises a first welding portion (8) and a second welding portion (9); The cable tube (3) is fixedly connected to the first through hole (6) via a first welding portion (8), and the cable tube (3) is fixedly connected to the second through hole (7) via a second welding portion (9).

6. The aircraft auxiliary fuel tank cable connection structure according to claim 5, characterized in that: The first welding portion (8) is a circular welding seam corresponding to the first through hole (6); The second welding portion (9) is a circular welding seam corresponding to the second through hole (7).

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