Explosion-proof device for aircraft air source vehicle

Abstract

The utility model discloses an explosion-proof device for an airplane gas source vehicle, which comprises a box body, a storage tank is arranged in the box body, a cooling pipe is arranged in the box body, the storage tank is arranged in the cooling pipe, and a pipeline for conveying gas is respectively connected with one end of a fixed pipe and one end of an airplane. The conveying assembly is started to circularly convey water mixed with cooling liquid in the two water tanks to the cooling pipe, the cooling pipe cools the storage tank and gas in the storage tank, meanwhile, the conveying pump is started, the conveying pump conveys the gas in the storage tank into the fixing pipe through the conveying pipe, and then the gas is conveyed into the airplane through the pipeline for conveying the gas. The pressure relief assembly is installed between the fixing pipe and the exhaust pipe, when the pressure of conveyed gas is too high, the pressure relief assembly exhausts the gas from the exhaust pipe to reduce the gas pressure, explosion caused by too high temperature or too high pressure intensity of the storage tank is prevented, and the safety and reliability of the aircraft gas source vehicle are improved.

Description

Technical Field

[0001] The utility model relates to the technical field of gas supply vehicles, and particularly relates to an explosion-proof device for an aircraft gas supply vehicle. Background Technique

[0002] In the technical field of aircraft ground comprehensive support, the aircraft gas supply vehicle is one of the key ground support equipment. Its main function is to provide high-pressure and large-flow gas sources for aircraft to meet the gas source starting requirements of medium and large aircraft. The aircraft gas supply vehicle usually integrates a fuel system, a fire extinguishing system, a gas turbine engine, an intake and exhaust system, a power supply system, a gas supply system, a lighting system, and an operation control system. These systems cooperate together to ensure that the aircraft gas supply vehicle can work efficiently and stably.

[0003] However, during the actual operation process, the internal pressure of the tank of the aircraft gas supply vehicle may abnormally increase due to various reasons, such as too high temperature or too high gas pressure, etc. This will not only affect the normal operation of the aircraft gas supply vehicle, but may even cause an explosion and lead to safety accidents, causing damage to personnel and equipment. Therefore, we provide an explosion-proof device for an aircraft gas supply vehicle for use. Content of the Utility Model

[0004] The purpose of the utility model is to provide an explosion-proof device for an aircraft gas supply vehicle to solve the problems raised in the above background technique.

[0005] To achieve the above purpose, the utility model provides the following technical scheme: An explosion-proof device for an aircraft gas supply vehicle, including a box body. A storage tank is installed inside the box body. A cooling pipe is installed inside the box body and the storage tank is located inside the cooling pipe. One end at the bottom of the cooling pipe is provided with a water inlet, and the end of the cooling pipe away from the water inlet is provided with a water outlet. Two groups of water tanks are respectively installed at the bottom end inside the box body, and the water inlet and the water outlet are respectively connected inside the two groups of water tanks;

[0006] A conveying assembly is installed between the two groups of water tanks and the cooling pipe for circulating and conveying cooling water. A fixed pipe is installed on one side at the bottom of the box body, and an exhaust pipe is connected to the bottom of the fixed pipe. A conveying pump is installed at one end inside the box body. The two ends of the conveying pump are respectively connected with conveying pipes, and one ends of the two groups of conveying pipes are respectively connected inside the fixed pipe and inside the storage tank. A pressure relief assembly is installed between the fixed pipe and the exhaust pipe.

[0007] Preferably, the pressure relief assembly includes an electromagnetic valve, a controller, and a pressure gauge. The two electromagnetic valves are respectively installed at the outer ends of the fixed pipe and the exhaust pipe. The two controllers are respectively installed at one ends of the two electromagnetic valves. The pressure gauge is installed on the top of the fixed pipe to detect the pressure when the fixed pipe conveys gas.

[0008] Preferably, the conveying assembly includes a first water pump, a second water pump and a support pipe. The first water pump is installed on the top of one of the water tanks, one end of the water inlet is connected to the inside of the first water pump, the second water pump is installed on one side of the other water tank, the support pipe is connected to one end of the second water pump and the other end of the support pipe is connected to the inside of the other water tank.

[0009] Preferably, stabilizing plates are respectively installed on the tops of the two water tanks and the inner top end of the box body, and the cooling pipe is installed between the four stabilizing plates.

[0010] Preferably, support rods are respectively connected to both ends of the storage tank, support plates are respectively connected to one sides of the two support rods and the support plates are attached to both sides inside the box body, and four bolts are respectively connected to one sides of the two support plates and the bolts penetrate through the support plates and are threadedly connected to the inside of the box body.

[0011] Preferably, a connecting seat is installed on one side of the fixed pipe, and a sealing ring is installed inside the connecting seat.

[0012] Compared with the prior art, the beneficial effects of the present utility model are as follows:

[0013] 1. In the present utility model, the pipelines for conveying gas are respectively connected to one end of the fixed pipe and one end of the aircraft. The conveying assembly is turned on to circulate the water in the mixed coolant in the two water tanks to the cooling pipe. The cooling pipe cools the storage tank and the gas inside the storage tank. At the same time, the conveying pump is turned on. The conveying pump uses the conveying pipe to convey the gas in the storage tank into the fixed pipe and then conveys it into the aircraft through the pipeline for conveying gas. The pressure relief assembly installed between the fixed pipe and the exhaust pipe discharges the gas from the exhaust pipe to reduce the air pressure when the conveying gas pressure is too high, preventing explosion caused by too high temperature or pressure of the storage tank, and improving the safety and reliability of the aircraft air source vehicle.

[0014] 2. In the present utility model, one end of the pipeline for conveying gas is connected to the connecting seat installed on one side of the fixed pipe, and the sealing ring installed inside the connecting seat seals the pipeline for conveying gas to avoid leakage when conveying gas. The support plates respectively connected to both sides of the two support rods are attached to both sides inside the box body. Multiple bolts are respectively penetrated and connected inside the support plates and threadedly extended to the inside of the box body. The storage tank is suspended inside the box body. At the same time, the stabilizing plates support the cooling pipe, and the cooling pipe can be stably suspended inside the box body. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 is a schematic diagram of the internal structure of the box body of the present utility model;

[0016] Figure 2 is a partial schematic diagram of the cold zone pipe of the present utility model;

[0017] Figure 3 Schematic enlarged view of part A of the present utility model Figure 1 ;

[0018] Figure 4 Partial schematic view of the fixed pipe of the present utility model

[0019] In the figure: 1, box body; 2, storage tank; 3, water tank; 4, first water pump; 5, second water pump; 6, support pipe; 7, stabilizing plate; 8, cooling pipe; 9, water inlet; 10, water outlet; 11, support rod; 12, support plate; 13, bolt; 14, fixed pipe; 15, exhaust pipe; 16, electromagnetic valve; 17, controller; 18, pressure gauge; 19, delivery pump; 20, delivery pipe; 21, connecting seat; 22, sealing ring Specific embodiments

[0020] Next, the technical solutions in the embodiments of the present utility model will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present utility model. Obviously, the described embodiments are only a part of the embodiments of the present utility model, rather than all the embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present utility model

[0021] Please refer to Figures 1-4 As shown, the present utility model is an explosion-proof device for an aircraft air source vehicle, including a box body 1. A storage tank 2 is installed inside the box body 1. A cooling pipe 8 is installed inside the box body 1 and the storage tank 2 is located inside the cooling pipe 8. One end of the bottom of the cooling pipe 8 is provided with a water inlet 9, and the end of the cooling pipe 8 away from the water inlet 9 is provided with a water outlet 10. Two groups of water tanks 3 are respectively installed at the bottom end inside the box body 1, and the water inlet 9 and the water outlet 10 are respectively connected to the inside of the two groups of water tanks 3

[0022] A conveying assembly is installed between the two groups of water tanks 3 and the cooling pipe 8 for circulating and conveying cooling water. A fixed pipe 14 is installed on one side of the bottom of the box body 1. The bottom of the fixed pipe 14 is connected to an exhaust pipe 15. A delivery pump 19 is installed at one end inside the box body 1. Both ends of the delivery pump 19 are respectively connected to a delivery pipe 20, and one end of the two groups of delivery pipes 20 is respectively connected to the inside of the fixed pipe 14 and the inside of the storage tank 2. A pressure relief assembly is installed between the fixed pipe 14 and the exhaust pipe 15

[0023] In this embodiment, by connecting the pipelines for conveying gas to one end of the fixed pipe 14 and one end of the aircraft respectively, and starting the conveying assembly, the conveying assembly circulates the water mixed with coolant in the two groups of water tanks 3 to the cooling pipe 8. The cooling pipe 8 cools the storage tank 2 and the gas in the storage tank 2. At the same time, start the delivery pump 19. The delivery pump 9 uses the delivery pipe 20 to deliver the gas in the storage tank 2 into the fixed pipe 14 and then conveys it into the aircraft through the pipeline for conveying gas. A pressure relief assembly is installed between the fixed pipe 14 and the exhaust pipe 15. When the conveying gas pressure is too high, the pressure relief assembly discharges the gas from the exhaust pipe 15 to reduce the air pressure and prevent the explosion caused by the too high temperature or pressure of the storage tank 2.

[0024] Please refer to Figure 4 As shown in the figure, the pressure relief assembly includes an electromagnetic valve 16, a controller 17 and a pressure gauge 18. Two groups of electromagnetic valves 16 are respectively installed at the outer ends of the fixed pipe 14 and the exhaust pipe 15. Two controllers 17 are respectively installed at one ends of the two groups of electromagnetic valves 16. The pressure gauge 18 is installed on the top of the fixed pipe 14 to detect the pressure when the fixed pipe 14 conveys gas.

[0025] In this embodiment, through the electromagnetic valve 16 installed at the outer ends of the fixed pipe 14 and the exhaust pipe 15, the controller 17 installed outside the electromagnetic valve 16 controls the opening and closing of the electromagnetic valve 16. The pressure gauge 18 installed on the top of the fixed pipe 14 detects the pressure when conveying gas. When the pressure is too high, the controller 17 located outside the exhaust pipe 15 controls the electromagnetic valve 16 to open to discharge the gas and reduce the pressure.

[0026] Please refer to Figure 1 As shown in the figure, the conveying assembly includes a first water pump 4, a second water pump 5 and a support pipe 6. The first water pump 4 is installed on the top of one of the water tanks 3. One end of the water inlet 9 is connected to the inside of the first water pump 4. The second water pump 5 is installed on one side of the other water tank 3. The support pipe 6 is connected to one end of the second water pump 5 and the other end of the support pipe 6 is connected to the inside of the other water tank 3.

[0027] In this embodiment, by starting the first water pump 4, the water mixed with coolant in one of the water tanks 3 is conveyed into the cooling pipe 8 through the water inlet 9 and finally discharged into the other water tank 3 through the water outlet 10 connected to one end of the cooling pipe 8. Start the second water pump 5, and through the connected support pipe 6, the water in the water tank 3 is conveyed into the other water tank 3 for circulating conveyance.

[0028] Please refer to Figure 2 As shown in the figure, stabilizing plates 7 are respectively installed at the tops of the two groups of water tanks 3 and the inner top end of the box body 1. The cooling pipe 8 is installed between the four stabilizing plates 7.

[0029] In this embodiment, by providing stabilizing plates 7 at the top of the water tank 3 and the inner top of the box body 1 respectively, the stabilizing plates 7 support the cooling pipes 8, enabling the cooling pipes 8 to be stably suspended inside the box body 1.

[0030] Please refer to Figure 3 As shown, support rods 11 are respectively connected to both ends of the storage tank 2. On one side of the two groups of support rods 11, support plates 12 are respectively connected, and the support plates 12 are attached to both sides inside the box body 1. On one side of the two groups of support plates 12, four groups of bolts 13 are respectively connected, and the bolts 13 penetrate through the support plates 12 and are threadedly connected to the inside of the box body 1.

[0031] In this embodiment, by attaching the support plates 12 respectively connected to both sides of the two groups of support rods 11 to both sides inside the box body 1, and respectively passing a plurality of bolts 13 through the inside of the support plates 12 and threadedly extending them into the inside of the box body 1, the storage tank 2 is suspended inside the box body 1.

[0032] Please refer to Figure 4 As shown, a connection seat 21 is installed on one side of the fixed pipe 14, and a sealing ring 22 is installed inside the connection seat 21.

[0033] In this embodiment, one end of the pipeline for conveying gas is connected to the connection seat 21 installed on one side of the fixed pipe 14. The sealing ring 22 installed inside the connection seat 21 seals the pipeline for conveying gas, preventing leakage during gas conveyance.

[0034] Working principle: The present utility model is an explosion-proof device for an aircraft air source vehicle. During use, one end of the pipeline for conveying gas is connected to the connection seat 21 installed on one side of the fixed pipe 14. The sealing ring 22 installed inside the connection seat 21 seals the pipeline for conveying gas, preventing leakage during gas conveyance. The other end of the pipeline for conveying gas is connected to the inside of the aircraft. The conveying pump 9 is turned on, and the gas in the storage tank 2 is conveyed into the fixed pipe 14 through the conveying pipe 20 and then conveyed into the aircraft through the pipeline for conveying gas. The first water pump 4 is turned on to convey the water in the mixed coolant in one of the water tanks 3 into the cooling pipes 8 through the water inlet 9, and finally discharged into the other water tank 3 from the water outlet 10 connected to one end of the cooling pipes 8. The second water pump 5 is turned on, and through the connected support pipe 6, the water in the water tank 3 is conveyed into the other water tank 3 for circulating conveyance, enabling the cooling pipes 8 to cool the storage tank 2 filled with gas. At the same time, the pressure gauge 18 installed on the top of the fixed pipe 14 detects the pressure during gas conveyance. When the pressure is too high, the controller 17 located outside the exhaust pipe 15 controls the solenoid valve 16 to open to discharge the gas and reduce the pressure. The content not described in detail in this specification belongs to the prior art well-known to those skilled in the art.

[0035] Although the present utility model has been described in detail with reference to the foregoing embodiments, those skilled in the art can still modify the technical solutions described in the foregoing embodiments, or perform equivalent replacements for some of the technical features. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present utility model shall be included within the protection scope of the present utility model.

Claims

1. An explosion-proof device for an aircraft air source vehicle, comprising a box body (1), characterized in that: Inside the box body (1), a storage tank (2) is installed. Inside the box body (1), a cooling pipe (8) is installed and the storage tank (2) is located inside the cooling pipe (8). One end of the bottom of the cooling pipe (8) is provided with a water inlet (9), and the end of the cooling pipe (8) away from the water inlet (9) is provided with a water outlet (10). At the bottom end inside the box body (1), two groups of water tanks (3) are respectively installed. The water inlet (9) and the water outlet (10) are respectively connected inside the two groups of water tanks (3). A conveying assembly is installed between the two groups of water tanks (3) and the cooling pipe (8) to circulate and convey cooling water. On one side of the bottom of the box body (1), a fixed pipe (14) is installed. The bottom of the fixed pipe (14) is connected to an exhaust pipe (15). Inside one end of the box body (1), a delivery pump (19) is installed. Both ends of the delivery pump (19) are respectively connected to a delivery pipe (20), and one end of the two delivery pipes (20) is respectively connected inside the fixed pipe (14) and inside the storage tank (2). A pressure relief assembly is installed between the fixed pipe (14) and the exhaust pipe (15).

2. The explosion-proof device for an aircraft air source vehicle according to claim 1, characterized in that: The pressure relief assembly includes an electromagnetic valve (16), a controller (17) and a pressure gauge (18). The two electromagnetic valves (16) are respectively installed at the outer ends of the fixed pipe (14) and the exhaust pipe (15). The two controllers (17) are respectively installed at one end of the two electromagnetic valves (16). The pressure gauge (18) is installed on the top of the fixed pipe (14) to detect the pressure when the fixed pipe (14) conveys gas.

3. The explosion-proof device for an aircraft air source vehicle according to claim 1, characterized in that: The conveying assembly includes a first water pump (4), a second water pump (5) and a support pipe (6). The first water pump (4) is installed on the top of one of the water tanks (3). One end of the water inlet (9) is connected inside the first water pump (4). The second water pump (5) is installed on one side of the other water tank (3). The support pipe (6) is connected to one end of the second water pump (5), and the other end of the support pipe (6) is connected to the inside of the other water tank (3).

4. An explosion-proof device for an aircraft air source vehicle according to claim 3, characterized in that: On the tops of the two groups of water tanks (3) and the inner top end of the box body (1), stabilizing plates (7) are respectively installed. The cooling pipe (8) is installed between the four stabilizing plates (7).

5. An explosion-proof device for an aircraft air source vehicle according to claim 4, characterized in that: Both ends of the storage tank (2) are respectively connected to a support rod (11). On one side of the two support rods (11), a support plate (12) is respectively connected, and the support plate (12) is attached to both sides inside the box body (1). On one side of the two support plates (12), four bolts (13) are respectively connected, and the bolts (13) penetrate through the support plate (12) and are threadedly connected to the inside of the box body (1).

6. The explosion-proof device for an aircraft air source vehicle according to claim 2, characterized in that: On one side of the fixed pipe (14), a connecting seat (21) is installed. Inside the connecting seat (21), a sealing ring (22) is installed.

Images