Novel electric auxiliary device for assembling and disassembling aviation cockpit fuel tank

Abstract

The utility model relates to the field of aviation cockpit fuel tank assisting, in particular to a novel electric auxiliary device for assembling and disassembling an aviation cockpit fuel tank, which comprises a movable platform, a support, an operation panel and a small hydraulic station connected with the operation panel. The device further comprises a lifting bracket arranged on the support, a hoop fixed to the side face of the support through a bolt, a hydraulic cylinder fixed to the top of the support, and a pull pressure sensor connected to the head of a piston rod of the hydraulic cylinder through threads. According to the utility model, the thrust applied to the fuel tank cap of the aircraft cockpit and the spring force in the fuel tank piston of the aircraft cockpit are always kept in dynamic balance, so that an operator can realize complete alignment of an internal thread of the fuel tank cap of the aircraft cockpit and an external thread on a fuel tank body through slight shaking, and the threads are tightened through very small torque; manpower is greatly saved, efficiency is improved, and the safety and reliability of the assembling and disassembling technological process of the aviation cockpit fuel tank are improved.

Description

Technical Field

[0001] This utility model relates to the field of aircraft cockpit fuel tank assistance, specifically a novel electric auxiliary device for the assembly and disassembly of aircraft cockpit fuel tanks. Background Technology

[0002] The aircraft cabin fuel tank has a cylindrical piston structure, with hydraulic oil at one end and a compression spring at the other. During assembly, the compression spring inside the fuel tank piston, along with the fuel tank cap, needs to be compressed until the internal thread on the fuel tank cap is fully in contact with the external thread on the fuel tank body before tightening the threads. The natural length of the compression spring is approximately 380mm, and the compressed length is approximately 150mm. At this point, the spring's compression force is approximately 1000N. Once the internal thread on the fuel tank cap is fully in contact with and aligned with the external thread on the fuel tank body, the fuel tank cap is tightened by rotating it clockwise to complete the installation. Disassembly is the reverse process.

[0003] Problems exist: First, the compression spring requires a large compression force, which is difficult to achieve by direct manual compression.

[0004] Secondly, when the spring is fully compressed, the thread needs to be aligned before rotating to cut in. At this time, when tightening the thread, it is always necessary to overcome the 1000N spring force, making it difficult to align the thread and cut in, and the tightening force is large.

[0005] Third, during the assembly and disassembly of the aircraft's cabin fuel tanks, the forces applied to the fuel tank caps and retractable cartridges need to be kept balanced or increased or decreased slowly to reduce physical impact damage during the assembly and disassembly process. An auxiliary device needs to be developed to complete the fuel tank assembly or disassembly.

[0006] The existing method uses a mechanical lead screw to load the compression spring inside the aircraft cabin fuel tank and the fuel tank cap. This can partially solve the first problem mentioned above, but cannot solve the second and third problems. At the same time, because the spring compression stroke is long, it needs to be rotated more than 100 times to complete one installation, which is time-consuming, labor-intensive, inefficient and unreliable. Utility Model Content

[0007] To address the aforementioned problems, this utility model proposes a novel electrically assisted device for assembling and disassembling aircraft cockpit fuel tanks.

[0008] A novel electrically assisted device for assembling and disassembling aircraft cockpit fuel tanks includes a mobile platform, a bracket and an operation panel mounted on the mobile platform, a small hydraulic station connected to the operation panel, a lifting bracket mounted on the bracket, clamps bolted to the side of the bracket, a hydraulic cylinder bolted to the top of the bracket, and a tension / compression sensor threaded to the piston rod head of the hydraulic cylinder.

[0009] The tension / compression sensor has a pressure cap at the lower end of the adapter, which is placed on the fuel tank cap of the aircraft cabin fuel tank.

[0010] The small hydraulic station is a small electric pump station with start / stop, three-position four-way solenoid directional valve, flow regulation and pressure regulation functions.

[0011] The mobile platform is equipped with several sets of movable casters at its bottom.

[0012] The piston rod of the hydraulic cylinder extends and drives the pressure cap pressing on the fuel tank opening cover of the aircraft cabin to move downward.

[0013] The retraction of the piston rod of the hydraulic cylinder causes the compression spring inside the aircraft cabin oil to push the oil tank cap and pressure cap upward, ensuring that they are always in contact with the adapter of the tension / compression sensor.

[0014] The control panel is fixed to the side of the bracket by bolts.

[0015] The control panel is equipped with a power switch, a reversing switch, and a pressure adjustment knob for the small hydraulic station.

[0016] The beneficial effects of this utility model are:

[0017] This invention utilizes a small hydraulic station to drive a hydraulic cylinder piston rod, which loads the spring inside the aircraft cabin fuel tank piston and the fuel tank cap. The piston rod extends and retracts via a reversing valve attached to the small hydraulic station, the speed of extension and retraction is adjusted via a flow regulating valve attached to the small hydraulic station, and the magnitude of the thrust of the hydraulic cylinder piston rod is adjusted via a system pressure regulating valve attached to the small hydraulic station. This ensures that the thrust applied to the aircraft cabin fuel tank cap and the spring force inside the aircraft cabin fuel tank piston are always dynamically balanced. This allows the operator to achieve complete alignment of the internal thread of the aircraft cabin fuel tank cap with the external thread on the fuel tank body with a slight shaking motion, and to tighten the threads with very little torque. This significantly saves manpower, improves efficiency, and enhances the safety and reliability of the aircraft cabin fuel tank assembly and disassembly process. Attached Figure Description

[0018] The present invention will be further described below with reference to the accompanying drawings and embodiments.

[0019] Figure 1 This is a schematic diagram of the main structure of this utility model;

[0020] Figure 2 This is a side view of the structure of this utility model;

[0021] Figure 3 This is a schematic diagram of the system principle structure of this utility model;

[0022] Reference numerals in the attached drawings: 1. Mobile platform; 2. Support frame; 3. Lifting bracket; 4. Clamp; 5. Pressure cover; 6. Tension / compression sensor; 7. Hydraulic cylinder; 8. Control panel; 9. Small hydraulic station. Detailed Implementation

[0023] To make the technical means, creative features, objectives and effects of this utility model easier to understand, the utility model will be further described below.

[0024] like Figures 1 to 3 As shown, a novel electric auxiliary device for assembling and disassembling aircraft cockpit fuel tanks includes a mobile platform 1, a bracket 2 and an operation panel 8 mounted on the mobile platform 1, a small hydraulic station 9 connected to the operation panel 8, a lifting bracket 3 mounted on the bracket 2, a clamp 4 bolted to the side of the bracket 2, a hydraulic cylinder 7 bolted to the top of the bracket 2, and a tension / compression sensor 6 threaded to the piston rod head of the hydraulic cylinder 7.

[0025] The tension / compression sensor 6 is equipped with a pressure cap 5 at the lower end of the adapter. The pressure cap 5 is placed on the fuel tank cover of the aircraft cabin fuel tank. The pressure adjustment of the small hydraulic station 9 realizes the adjustment of the pushing force of the piston rod of the hydraulic cylinder 7. The tension / compression sensor 6 can monitor the pressure applied to the fuel tank cover and its internal compression spring in real time, thereby providing reference guidance for dynamically adjusting the pressure of the small hydraulic station 9 to control the compression amount of the internal compression spring of the fuel tank cover.

[0026] The small hydraulic station 9 is a small electric pump station with start / stop, three-position four-way solenoid directional valve, flow regulation and pressure regulation functions. Its main parameters include AC220V / 0.4kW power supply, flow regulation range of 0-1L / min, and pressure regulation range of 0.2-1MPa.

[0027] The mobile platform 1 is equipped with several sets of movable casters at its bottom and a flat platform on top. The lifting bracket 3 is installed on the bottom platform of the support 2 and is adjusted for lifting by a screw to support the aircraft cabin fuel tank and balance its vertical force.

[0028] When the piston rod of the hydraulic cylinder 7 extends, it drives the pressure cap 5 pressing on the fuel tank opening cover of the aircraft cockpit to move downward. The hydraulic cylinder 7 is fixed to the top of the bracket 2 by bolts, and auxiliary supports are added to the side of the bracket 2 to prevent shaking.

[0029] When the piston rod of the hydraulic cylinder 7 retracts, the compression spring inside the aircraft cabin oil tank pushes the fuel tank cap and pressure cap 5 upwards, ensuring they remain in contact with the adapter of the tension / compression sensor 6. The speed of the extension / retraction movement is adjusted by the flow regulating valve attached to the small hydraulic station 9, and the magnitude of the pushing force of the piston rod of the hydraulic cylinder 7 is adjusted by the system pressure regulating valve attached to the small hydraulic station 9. This ensures that the thrust applied to the fuel tank cap and the spring force inside the fuel tank piston remain dynamically balanced. This allows the operator to achieve complete alignment of the internal thread of the fuel tank cap with the external thread on the fuel tank body with a slight shaking motion, and to tighten the threads with very little torque. This significantly saves manpower, improves efficiency, and enhances the safety and reliability of the aircraft cabin fuel tank assembly and disassembly process.

[0030] The operation panel 8 is fixed to the side of the bracket 2 by bolts.

[0031] The control panel 8 is equipped with a power switch, a reversing switch, and a pressure adjustment knob for the small hydraulic station 9. The power switch is used to control the start and stop of the small hydraulic station 9. The reversing switch is used to switch the three-position four-way solenoid reversing valve inside the small hydraulic station 9. The pressure adjustment knob is used to adjust the working pressure of the hydraulic system to change the pressure applied to the fuel tank cap of the aircraft cabin. The piston rod of the hydraulic cylinder 7 driven by the small hydraulic station 9 loads the spring inside the piston of the aircraft cabin fuel tank and the pressure cap 5 of the fuel tank cap. The piston rod of the hydraulic cylinder 7 is extended and retracted through the reversing valve attached to the small hydraulic station 9.

[0032] The foregoing has shown and described the basic principles, main features, and advantages of this utility model. Those skilled in the art should understand that this utility model is not limited to the above embodiments. The embodiments and descriptions in the specification are merely the principles of this utility model. Various changes and modifications can be made to this utility model without departing from its spirit and scope, and all such changes and modifications fall within the scope of the claims. The scope of protection of this utility model is defined by the appended claims and their equivalents.

Claims

1. A new type of electric auxiliary device for disassembling and assembling the cockpit tank of an aircraft, comprising a moving platform (1), a support (2) and an operating panel (8) arranged on the moving platform (1), and a small hydraulic station (9) connected with the operating panel (8), characterized in that: It also includes lifting bracket (3) set on the bracket (2), fixed on the bracket (2) side hoop (4), fixed on the bracket (2) top hydraulic cylinder (7), connecting in the hydraulic cylinder (7) piston rod head tension and pressure sensor (6).

2. A new type of electric auxiliary assembly for disassembly of the cockpit tank of an aircraft according to claim 1, characterized in that: The tension and pressure sensor (6) is provided with a gland (5) at the lower end of the adapter, and the gland (5) is placed on the oil tank cover of the aircraft cabin tank.

3. A new type of electric auxiliary assembly for disassembly of the cockpit tank of an aircraft according to claim 1, characterized in that: The small hydraulic station (9) is a small electric pump station with start / stop, three-position four-way electromagnetic reversing valve, flow regulation and pressure regulation functions.

4. A new type of electric auxiliary assembly for disassembly of the cockpit tank of an aircraft according to claim 1, characterized in that: The bottom of the moving platform (1) is provided with several groups of movable casters.

5. A new type of electrically powered auxiliary assembly for disassembly of the fuel tank of the cockpit of an aircraft, according to claim 1, characterized in that: The piston rod of the hydraulic cylinder (7) extends to drive the gland (5) pressed on the cover of the aircraft cabin tank to move downward.

6. A new type of electrically powered auxiliary assembly for disassembly of the cockpit tank of an aircraft, according to claim 1, characterized by the fact that it comprises: The piston rod of the hydraulic cylinder (7) retracts to drive the compression spring inside the aircraft cabin tank to lift the tank cover and the gland (5) upward, and the adapter of the tension and pressure sensor (6) is attached.

7. A new type of electrically powered auxiliary assembly for disassembly of the cockpit tank of an aircraft, according to claim 1, characterized by the fact that it comprises: The operation panel (8) is fixed on the side of the bracket (2) by bolts.

8. A new type of electrically powered auxiliary assembly for disassembly of the fuel tank of the cockpit of an aircraft, according to claim 1, characterized by the fact that it comprises: The operation panel (8) is provided with a power switch, a reversing switch and a pressure adjustment knob of the small hydraulic station (9).

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