Aircraft fuel system refuelling pressure monitoring and emergency shut-off device

Abstract

The utility model relates to the technical field of aircraft maintenance, concretely is a kind of aircraft fuel system refueling pressure monitoring and emergency cut-off device, including support column, still including the pressure blocking component being set on the upper end of support column, the locking cap being set in the lower end of support column, the utility model is installed on the gravity refueling port of aircraft No. 1 tank, pressure display and control terminal are installed at ground convenient observation position, not only can real-time display the pressure in aircraft tank, but also can emergency cut-off ground refueling equipment when aircraft refueling system failure, improve the security of aircraft refueling process, the device can also meet the aircraft fuel tank tightness test use simultaneously.

Description

Technical Field

[0001] This utility model relates to the field of aircraft maintenance technology, specifically to a device for monitoring and emergency shut-off of refueling pressure in an aircraft fuel system. Background Technology

[0002] The aircraft fuel system is an important component of an aircraft. The aircraft pressure refueling emergency shut-off function is an emergency measure to ensure refueling safety during the refueling process. When the aircraft's electric refueling shut-off switch fails, the refueling valve controlled by the float valve will shut off the refueling pipeline on the aircraft in an emergency, stopping the refueling process.

[0003] When verifying the emergency shut-off function of aircraft pressure refueling, it is necessary to open the electric shut-off switch on the aircraft and then cut off the power to the aircraft. Under this state, pressure refueling is performed on the aircraft. The emergency shut-off function is verified by whether the aircraft can automatically stop refueling after the fuel tank is full.

[0004] To prevent overpressure in the aircraft fuel tank, the previous practice was to install a pressure gauge with a safety valve on the gravity refueling port of the aircraft's No. 1 fuel tank during the pressure refueling emergency shut-off test. This gauge was used to monitor the pressure inside the tank, and refueling would stop when the pressure reached a specified value. If the emergency shut-off function of the aircraft refueling system failed and the pressure inside the fuel tank exceeded the allowable value, the aircraft fuel tank would release pressure through the safety valve.

[0005] Using pressure gauges with safety valves to monitor aircraft fuel tank pressure still has the following drawbacks: 1. The time between filling the tank and the aircraft's emergency shut-off during pressurized refueling is very short. Relying on personnel to visually monitor pressure changes on the gauges results in a very short reaction time, easily leading to overpressure within the tank. 2. During pressurized refueling, although pressure can be released through the safety valve in case of an emergency shut-off system failure, the gravity refueling port of fuel tank 1 is located at a high position, and leaked fuel will flow into the aircraft interior, causing contamination and impact on onboard products.

[0006] Therefore, it is necessary to invent a device that can monitor the pressure inside the fuel tank in real time and automatically shut down the ground pressure refueling equipment when the aircraft's emergency shut-off function fails, based on the existing safety measures. Summary of the Invention

[0007] To address the aforementioned problems, this invention proposes a refueling pressure monitoring and emergency shut-off device for an aircraft fuel system.

[0008] A refueling pressure monitoring and emergency shut-off device for an aircraft fuel system includes a support column, a pressure blocking component disposed at the upper end of the support column, and a locking cap disposed at the lower end of the support column.

[0009] The supporting column is designed in a T-shape, consisting of a horizontal beam and a vertical column.

[0010] The support column is also equipped with a base plate at the bottom of the column, a pressure gauge base, a safety valve base, and a pressure sensor base that are welded horizontally to the beam in sequence.

[0011] The base plate is adapted to the mounting surface of the gravity-fed fuel filler port of the fuel tank.

[0012] The aforementioned crossbeams, columns, pressure gauge bases, safety valve bases, pressure sensor bases, and base plates are all hollow structures.

[0013] The pressure blocking assembly includes a pressure gauge, a safety valve, a pressure sensor, and a manual venting valve located at the end of the crossbeam, respectively mounted on the pressure gauge base, the safety valve base, and the pressure sensor base.

[0014] A sealing ring is provided between the pressure gauge and the crossbeam to ensure their respective sealing performance.

[0015] The pressure sensor is connected to a pressure display and control terminal via a cable.

[0016] The locking cover engages with the threaded section located at the end of the column and is connected to the aircraft fuel tank via a rubber gasket.

[0017] The beneficial effects of this utility model are as follows: This utility model is installed on the gravity refueling port of the No. 1 fuel tank of the aircraft, and the pressure display and control terminal is installed on the ground in a position that is easy to observe. It can not only display the pressure in the aircraft fuel tank in real time, but also cut off the ground refueling equipment in case of aircraft refueling system failure, thereby improving the safety of the aircraft refueling process. This device can also meet the requirements for aircraft fuel tank sealing test. 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 overall installation of the present invention;

[0020] Figure 2 This is a three-dimensional structural diagram of the present invention;

[0021] Figure 3 This is a schematic diagram of the support column structure of the present invention.

[0022] Figure 4 This is a schematic diagram of the locking device structure of the present invention.

[0023] Figure 5 This is a schematic diagram of the gravity refueling port structure of the No. 1 oil tank of the present invention.

[0024] Figure 6 This is a schematic diagram of the pressure display and control terminal circuit of the present invention.

[0025] Attached reference numerals: 1. Manual vent valve; 2. Pressure sensor; 3. Safety valve; 4. Pressure gauge; 5. Sealing ring; 6. Support column; 7. Locking cover; 8. Rubber gasket; 9. Pressure display and control terminal; 6-1. Base plate; 6-2. Column; 6-3. Crossbeam; 6-4. Pressure sensor base; 6-5. Safety valve base; 6-6. Pressure gauge base. Detailed Implementation

[0026] 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.

[0027] like Figures 1 to 6 As shown, an aircraft fuel system refueling pressure monitoring and emergency shut-off device includes a support column 6, a pressure blocking assembly disposed at the upper end of the support column 6, and a locking cover 7 disposed at the lower end of the support column 6. Figure 1 The attached diagram shows the gravity filler neck for the fuel tank.

[0028] The support column 6 is T-shaped and consists of a crossbeam 6-3 and a column 6-2. Each mounting point on the support column 6 has a threaded hole that matches the thread of the corresponding component. The sealing ring 5 added during installation ensures the sealing performance of each component.

[0029] This utility model is installed on the gravity refueling port of aircraft fuel tank No. 1, with the pressure display and control terminal 99 installed on the ground in an easily observable location. It not only displays the pressure inside the aircraft fuel tank in real time but also allows for emergency shutdown of ground refueling equipment in case of aircraft refueling system failure, thus improving the safety of the aircraft refueling process. This device can also be used for aircraft fuel tank sealing tests.

[0030] The support column 6 is also provided with a base plate 6-1 at the bottom end of the column 6-2, a pressure gauge base 6-6, a safety valve base 6-5, and a pressure sensor base 6-4 which are welded horizontally to the crossbeam 6-3 in sequence. The pressure sensor base 6-4, the safety valve base 6-5, and the pressure gauge base 6-6 are welded to the upper surface of the crossbeam 6-3, the upper end of the column 6-2 is welded to the lower surface of the crossbeam 6-3, and the lower end of the column 6-2 is welded to the base plate 6-1.

[0031] The base plate 6-1 is adapted to the mounting surface of the gravity filling port of the fuel tank.

[0032] The crossbeam 6-3, column 6-2, pressure gauge base 6-6, safety valve base 6-5, pressure sensor base 6-4, and base plate 6-1 are all hollow structures to ensure unobstructed gas flow.

[0033] The pressure blocking assembly includes a pressure gauge 4, a safety valve 3, a pressure sensor 2, and a manual venting valve 1, which are respectively installed on the pressure gauge base 6-6, the safety valve base 6-5, and the pressure sensor base 6-4. The pressure relief pressure of the safety valve 3 is set to 1.25 times the rated pressure.

[0034] The emergency cut-off response pressure of the pressure display and control terminal 9 is set to 1.1 times the rated pressure. A sealing ring 5 is provided between the pressure gauge 4 and the crossbeam 6-3 to ensure their respective sealing performance.

[0035] The pressure sensor 2 is connected to a pressure display and control terminal 9 via a cable. The pressure display and control terminal 9 is installed on the ground in a position that is easy for the operator to observe. It needs to display the measured pressure in real time, and when the pressure reaches a set threshold, it disconnects the power supply to the ground refueling equipment to stop refueling.

[0036] The locking cover 7 engages with the threaded section at the end of the column 6-2 and is connected to the aircraft fuel tank via a rubber gasket 8.

[0037] Manual vent valve 1 is used for manual pressure relief. After the fuel tank airtightness test is completed, manual vent valve 1 can be manually opened to release the gas in the fuel tank. Pressure sensor 2 is used to measure and transmit the real-time pressure in the fuel tank and transmit the pressure to the pressure display and control terminal 9. Safety valve 3 is used for automatic pressure relief, which plays a protective role. During the aircraft fuel tank sealing test, if the pressure is too high, exceeding the rated pressure by 1.25 times, the safety valve will automatically release the pressure to protect the fuel tank from damage. Pressure gauge 4 is used to display the pressure in the fuel tank, mainly to provide pressure indication for the aircraft operators, and serves as a backup for the pressure sensor. Sealing ring 5 is used to seal the pressure sensor 2, safety valve 3, and pressure gauge 4 when they are installed. Locking cap 7 is installed on support column 6 and is adjusted up and down by threads to fasten the aircraft fuel system refueling pressure monitoring and emergency cut-off device to the gravity refueling port of the fuel tank. Rubber gasket 8 is installed at the contact point between support column 6 and fuel tank refueling port, which plays a sealing and protective role. The pressure is transmitted to the pressure display and control terminal 9, which is installed on the ground in a convenient location for observation. It displays the pressure inside the aircraft's fuel tank in real time in digital form. When the refueling pressure inside the fuel tank reaches 1.1 times the rated pressure, the power supply to the refueling equipment is disconnected, thereby interrupting refueling.

[0038] like Figure 3As shown, the support column 6 is composed of a base plate 6-1, a column 6-2, a crossbeam 6-3, a pressure sensor base 6-4, a safety valve base 6-5, and a pressure gauge base 6-6, all welded together. After welding, the welds must be secure, the weld seams smoothed, and the airtightness checked to ensure no leakage. The dimensions of the base plate 6-1 are adapted to the mounting surface of the fuel tank's gravity filler neck to ensure a tight fit after installation. All components of the support column 6 are hollow structures to ensure unobstructed gas flow. The crossbeam 6-3 serves as a transition beam connecting the pressure sensor 2, the safety valve 3, and the pressure gauge 4. The pressure sensor base 6-4, the safety valve base 6-5, and the pressure gauge base 6-6 are welded to the upper surface of the crossbeam 6-3, leaving sufficient spacing, to connect the pressure sensor 2, the safety valve 3, and the pressure gauge 4. After the locking cover 7 is threaded onto the column 6-2, the base plate 6-1 and the column 6-2 are welded together.

[0039] like Figure 4 As shown, the two ends of the bottom of the locking cover 7 correspond to the notches of the gravity filler port of the oil tank. During installation, first rotate the locking cover 7 to the bottom of the column 6-2, and rotate the locking cover 7 into the internal structure of the gravity filler port through the notch of the oil port. Continue to rotate the locking cover 7 upward. When it is rotated to the limited position of the gravity filler port, the base plate 6-1 is pressed against the oil tank filler port.

[0040] like Figure 6 The diagram shows the circuit principle of the pressure display and control terminal. When the pressure signal voltage value is less than the standard voltage, the comparator circuit outputs a high level, and the control circuit is turned on, and the ground equipment is in a power supply state. When the pressure signal voltage value is greater than the standard voltage, the comparator circuit outputs a low level, and the control circuit is turned off, the power supply to the ground refueling equipment is disconnected, and refueling stops.

[0041] 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 device for monitoring and emergency shut-off of refueling pressure in an aircraft fuel system, characterized in that: It includes a support column (6), a pressure blocking assembly disposed at the upper end of the support column (6), and a locking cap (7) disposed at the lower end of the support column (6); The support column (6) is set in a T-shape and is divided into a crossbeam (6-3) and a column (6-2).

2. The aircraft fuel system refueling pressure monitoring and emergency shut-off device according to claim 1, characterized in that: The support column (6) is also provided with a base plate (6-1) at the bottom of the column (6-2), a pressure gauge base (6-6), a safety valve base (6-5), and a pressure sensor base (6-4) which are welded horizontally to the beam (6-3) in sequence.

3. The aircraft fuel system refueling pressure monitoring and emergency shut-off device according to claim 2, characterized in that: The base plate (6-1) is adapted to the mounting surface of the gravity filling port of the fuel tank.

4. The aircraft fuel system refueling pressure monitoring and emergency shut-off device according to claim 2, characterized in that: The crossbeam (6-3), column (6-2), pressure gauge base (6-6), safety valve base (6-5), pressure sensor base (6-4), and base plate (6-1) are all hollow structures.

5. The aircraft fuel system refueling pressure monitoring and emergency shut-off device according to claim 2, characterized in that: The pressure blocking assembly includes a pressure gauge (4), a safety valve (3), a pressure sensor (2), and a manual venting valve (1) respectively installed on the pressure gauge base (6-6), the safety valve base (6-5), and the pressure sensor base (6-4).

6. The aircraft fuel system refueling pressure monitoring and emergency shut-off device according to claim 5, characterized in that: A sealing ring (5) is provided between the pressure gauge (4) and the crossbeam (6-3) to ensure their respective sealing performance.

7. The aircraft fuel system refueling pressure monitoring and emergency shut-off device according to claim 5, characterized in that: The pressure sensor (2) is connected to a pressure display and control terminal (9) via a cable.

8. The aircraft fuel system refueling pressure monitoring and emergency shut-off device according to claim 1, characterized in that: The locking cover (7) engages with the threaded section at the end of the column (6-2) and is connected to the aircraft fuel tank via a rubber gasket (8).

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