Integrated aviation fuel supply equipment

Abstract

The present invention belongs to the field of aviation fuel supply, and specifically discloses an integrated aviation fuel supply equipment, including an oil storage device, a fuel supply device and a security system, wherein the oil storage device includes an oil tank; the fuel supply device includes an oil filling mechanism for conveying aviation fuel in the oil tank to an external oil receiving part, an oil receiving mechanism for introducing external aviation fuel into the oil tank, a quality inspection mechanism for quality inspection of aviation fuel, and an emptying mechanism for emptying the aviation fuel in the oil tank; the oil filling mechanism includes an oil pump, a filter separator, and a flow meter connected in sequence, the flow meter is connected to a gravity refueling unit, a pressure refueling unit, and an oil delivery joint, and the oil inlet end of the oil pump is connected to a first connection unit for connecting with the oil tank; the security system includes a fire-blocking breathing valve for maintaining air pressure balance, a manhole cover for emergency pressure relief, and a liquid level detection component for detecting the liquid level in the oil tank. The solution of the present invention can solve the problem that the existing refueling equipment has a relatively single function.

Description

Technical Field

[0001] The invention belongs to the field of aviation fuel supply, and in particular relates to integrated aviation fuel supply equipment. Background Art

[0002] To ensure the flight of general aviation, a fuel supply system is indispensable. Safety factors such as whether the resource channel is correct, whether the resource quality is reliable, whether the fuel supply measures are up to standard, and whether the quality of practitioners is qualified are all related to the foundation of the future development of the general aviation industry.

[0003] Airport refueling equipment is one of the necessary logistical support equipment for various airports. Large transport airports generally use pipeline refueling trucks to refuel aviation fuel, and feeder airports use tank refueling trucks to refuel aviation fuel. General aviation airports are relatively small, with small aircraft parked and few take-offs and landings. The demand for aviation fuel is not large. Due to investment restrictions, it is difficult to build pipelines to transport aviation fuel or to build oil storage facilities that integrate depots and stations. The aviation refueling equipment in the existing technology currently has a relatively single function and can only realize the refueling function. At present, there is no integrated skid-mounted refueling and storage device with diversified functions. Summary of the invention

[0004] In view of the deficiencies in the prior art, the present invention provides an integrated aviation fuel supply device to solve the problem that the aviation fuel supply device in the prior art has a relatively single function.

[0005] To achieve the above-mentioned purpose, the present invention adopts the following technical scheme: an integrated aviation fuel supply equipment, including a fuel storage device, a fuel supply device and a security system, the fuel storage device includes a fuel tank; the fuel supply device includes a refueling mechanism for conveying aviation fuel in the fuel tank to an external fuel receiving part, a fuel receiving mechanism for introducing external aviation fuel into the fuel tank, a quality inspection mechanism for performing quality inspection on aviation fuel, and an emptying mechanism for emptying the aviation fuel in the fuel tank; the refueling mechanism includes an oil pump, a filter separator, and a flow meter connected in sequence, and the outlet end of the flow meter is connected to There are gravity refueling unit, pressure refueling unit and oil delivery joint. The oil inlet end of the oil pump is connected to a first connecting unit for connecting with the oil tank. The security system includes a flame-retardant breathing valve installed on the upper end of the oil tank for maintaining the air pressure balance in the oil tank, a manhole cover for emergency pressure relief of the oil tank, and a level detection component for detecting the aviation fuel level in the oil tank. The security system also includes a combustible gas detector for detecting whether there is a combustible gas leak outside the oil tank, and an electro-hydraulic valve connected to the oil outlet end of the oil pump and controlling the opening and closing of the oil outlet end of the oil pump. The electro-hydraulic valve is connected to a Deadman control handle.

[0006] Compared with the prior art, the present invention has the following beneficial effects:

[0007] The fuel supply device is provided with an oil filling and dispensing mechanism, an oil collecting mechanism, a quality inspection mechanism and an emptying mechanism, which meet the requirements of refueling, dispensing, collecting and quality inspection. At the same time, due to the special storage of aviation fuel, the moisture and impurities in the aviation fuel will accumulate at the bottom of the oil tank, and it is necessary to discharge the accumulated moisture and impurities in the oil tank through the corresponding pipeline. In this scheme, an emptying mechanism is provided to empty the aviation fuel in the oil tank. The aviation fuel supply equipment in this scheme is functionally integrated, and the oil filling and dispensing mechanism includes a gravity refueling unit and a pressure refueling unit, which meet the two modes of gravity refueling and pressure refueling. In actual use, one of the refueling methods can be selected according to the actual situation, which is more convenient.

[0008] In addition, the setting of the security system in this application can ensure the safety of the oil tank during operation. The Deadman control handle controls the opening or closing of the electro-hydraulic valve through manual operation when in use, thereby controlling the oil tank to output oil or shut down. Its main purpose is to lock the operator at the oil supply device, so that the operator can promptly discover the safety hazards generated during the refueling process, and then quickly cut off the transportation of aviation fuel, avoiding the situation of safety hazards. BRIEF DESCRIPTION OF THE DRAWINGS

[0009] Figure 1 Schematic diagram of the working process of the oil supply device of Examples 1-7 of the present invention.

[0010] Figure 2 It is a top view of embodiment 1 of the present invention.

[0011] Figure 3 This is a schematic diagram of the structure of the security system in Example 1 of the present invention.

[0012] Figure 4 for Figure 3 Top view of the .

[0013] Figure 5 It is a top view of embodiment 2 of the present invention.

[0014] Figure 6 This is a front cross-sectional view of the oil tank in Example 2 of the present invention.

[0015] Figure 7 This is a control block diagram of embodiment 3 of the present invention.

[0016] Figure 8 It is a front cross-sectional view of embodiment 4 of the present invention.

[0017] Fig. 9 It is a front cross-sectional view of embodiment 5 of the present invention.

[0018] Fig.10 It is a top view of embodiment 7 of the present invention.

[0019] In the figure: oil tank 1, drain pipe 2, drain branch pipe 3, sampling branch pipe 4, first closed-circuit sampler 5, first quality inspection tank 6, recovery pump 7, valve II 8, valve III 9, skid-mounted seat 10, pressure refueling pipe 11, gravity refueling pipe 12, oil outlet pipe 13, drain connecting pipe 14, sampling connecting pipe 15, oil inlet common pipe 16, oil inlet pipe 17, oil supply pipe 18, oil supply common pipe 19, oil pump 20, first connecting pipe 21, filter separator 22, second Connecting pipe 23, flow meter 24, oil delivery pipe 25, oil receiving joint 26, second closed-circuit sampler 27, second quality inspection tank 28, oil return pipe 29, fence 30, escalator 31, manhole cover 32, flame arrester breathing valve 33, magnetostrictive liquid level gauge 34, liquid level switch 35, oil measuring hole 36, aviation kerosene tank 37, aviation gasoline tank 38, partition 39, outer tank 40, inner tank 41, interlayer 42, kerosene inner tank 43, gasoline inner tank 44, support rod 45. DETAILED DESCRIPTION

[0020] The present invention is further described in detail below with reference to the accompanying drawings, and specific implementation methods are given.

[0021] Example 1

[0022] like Figure 1 , Figure 2 As shown, the integrated aviation fuel supply equipment includes an oil storage device, a fuel supply device and a security system. The oil storage device includes an oil tank 1. In this embodiment, there are at least two oil storage devices. The following is explained by taking two oil storage devices (i.e., two oil tanks 1) as an example. The oil tanks 1 of the two oil storage devices both store aviation gasoline or aviation kerosene, and a skid-mounted seat 10 is fixed at the lower end of the oil tank 1.

[0023] The oil supply device includes an emptying mechanism, an oil adding mechanism, an oil collecting mechanism and a quality inspection mechanism, as follows:

[0024] The emptying mechanism includes a first quality inspection tank 6, a second connecting unit is connected between the first quality inspection tank 6 and the oil tank 1, the second connecting unit includes an emptying pipe 2 connected to the lower end of the oil tank 1, the emptying pipe 2 is L-shaped, the second connecting unit also includes an emptying branch pipe 3 connected to the middle of the emptying pipe 2 and a sampling branch pipe 4 connected to the end of the emptying pipe 2 away from the oil tank 1, a first closed-circuit sampler 5 is installed on the sampling branch pipe 4, a valve I is installed on the emptying pipe 2 between the oil tank 1 and the emptying branch pipe 3, a valve II8 is installed on the emptying branch pipe 3, and a valve III9 is ​​installed on the sampling branch pipe 4 between the first closed-circuit sampler 5 and the emptying pipe 2.

[0025] In this embodiment, the emptying branches 3 of the two second connection units are connected to form an emptying branch, the middle of the emptying branch is connected to an emptying connecting pipe 14, the two sampling branches 4 are connected to form a sampling branch, the middle of the sampling branch is connected to a sampling connecting pipe 15, the emptying connecting pipe 14 is connected to the lower end of the first quality inspection tank 6, and the sampling connecting pipe 15 is connected to the lower part of the first quality inspection tank 6. In this solution, the pipelines on the two oil tanks 1 are connected and blocked by valves, which reduces the setting of pipelines and facilitates pipeline control. The emptying mechanism is used to empty and detect the residual aviation fuel in the oil tank 1.

[0026] The refueling mechanism includes an oil pump 20, a first connecting pipe 21, a filter separator 22, a second connecting pipe 23, and a flow meter 24 connected in sequence. The flow meter 24 is connected to a gravity refueling unit and a pressure refueling unit. The gravity refueling unit includes a gravity refueling pipe 12 and a gravity refueling gun. One end of the gravity refueling pipe 12 is connected to the flow meter 24, and the other end of the gravity refueling pipe 12 is connected to the gravity refueling gun. The pressure refueling unit includes a pressure refueling pipe 11 and a pressure refueling joint. One end of the pressure refueling pipe 11 is connected to the flow meter 24, and the other end of the pressure refueling pipe 11 is connected to the pressure refueling joint. The gravity refueling gun and the pressure refueling joint are both used to refuel the aircraft. The pressure refueling pipe and the gravity refueling pipe are both made of soft rubber hoses. The refueling mechanism also includes two sets of reels. To ensure the convenience of refueling, the pressure refueling pipe and the gravity refueling pipe can be set longer and wound on the two sets of reels respectively. The reels can be electric reels or manual reels, as long as the pressure refueling pipe and the gravity refueling pipe can be reeled.

[0027] The oil pump 20 is connected to a first connection unit for connecting to the oil tank 1. In this embodiment, the first connection unit includes a common oil supply pipe 19 and an oil outlet pipe 13 connected to the oil tank 1. The oil outlet pipe 13 on each oil tank 1 is connected to the common oil supply pipe 19. An oil supply valve is installed on the oil tank 1 at a position connected to the oil outlet pipe 13. The middle of the common oil supply pipe 19 is connected to an oil supply pipe 18, and the oil supply pipe 18 is connected to the oil pump 20.

[0028] The refueling mechanism also includes an oil delivery pipe 25 connected to the flow meter 24. One end of the oil delivery pipe 25 away from the flow meter 24 is connected to an oil delivery joint, which is used to transport the aviation fuel in the oil tank 1 to the oil tanker.

[0029] The oil collection mechanism includes an oil collection joint 26 connected between the oil supply pipe 18 and the oil pump 20, and a third connection unit connected between the filter separator 22 or the flow meter 24 and the oil tank 1. In this embodiment, the third connection unit is connected between the filter separator 22 and the oil tank 1. In this embodiment, the third connection unit includes an oil inlet common pipe 16, an oil return pipe 29 connected to the filter separator 22, and an oil inlet pipe 17 connected to the oil tank 1. The oil inlet pipe 17 on each oil tank 1 is connected to the oil inlet common pipe 16, and the oil inlet common pipe 16 is connected to the oil tank 1. An oil inlet valve is installed on the oil tank 1 at a position connected to the oil inlet pipe 17. The oil collection mechanism is used to transport aviation fuel in the oil tanker to the oil tank 1.

[0030] The quality inspection mechanism includes a return oil pump 20, a second quality inspection tank 28 and a second closed-circuit sampler 27 which are connected in sequence. The return oil pump 20 is connected to the middle of the return oil pipe 29, and the return oil pump 20 is connected to the drain pipe 2 through a pipeline. The quality inspection mechanism is used to sample and inspect the aviation fuel output from the oil tank 1.

[0031] The pipes used in this embodiment can be installed with valves in actual processing to control the flow or blocking of the pipes. This technology is relatively conventional and will not be described in detail in this embodiment. The first closed-circuit sampler 5, the second closed-circuit sampler 27, the filter separator 22, and the flow meter 24 used in this embodiment are all conventional structures of the prior art, and their installation and connection methods are well known to those skilled in the art. For example, the first closed-circuit sampler 5 and the second closed-circuit sampler 27 can both use the samplers of Changzhou Lantian Tengfei Aviation Equipment Co., Ltd., the filter separator 22 can use the filter separator 22 for aircraft fuel of Zijing Sanyi Filtration Technology Co., Ltd., and the flow meter 24 can use the graphite scraper flowmeter of Chongqing Naide Industrial Co., Ltd. For details, please refer to the graphite scraper flowmeter disclosed in the patent "CN201821551853.4".

[0032] like Figure 3 , Figure 4As shown, the security mechanism includes a fence 30 installed on the top of the oil tank 1. A ladder 31 is provided on one side of the oil tank 1. The left end of the ladder 31 is fixed to the fence 30, and the right end of the ladder 31 is tilted downward. In the actual processing process, the lower end of the ladder 31 can be designed to contact the ground, so that the staff can go up and down the ladder 31. The top of the oil tank 1 is located in the fence 30 and is provided with a first mounting hole, a manhole and a second mounting hole connected to the oil tank 1. The first mounting hole is provided with a fire-blocking breathing valve 33 for maintaining the air pressure balance in the oil tank 1. The manhole cover 32 for emergency pressure relief of the oil tank 1 is installed in the manhole. The second mounting hole is provided with a liquid level monitoring component for monitoring the liquid level height in the oil tank 1. The liquid level detection component is a magnetostrictive liquid level gauge 34 and / or a liquid level switch 35. The magnetostrictive liquid level gauge 34 is used because it is suitable for the liquid level measurement of the clean liquid level with high precision requirements, with an accuracy of 1mm. The latest product accuracy can reach 0.1mm. When the magnetostrictive level gauge 34 and the level switch 35 are used simultaneously, they can be arranged one above and one below, thereby providing double protection for the fuel level in the oil tank 1 .

[0033] The fence 30 is also provided with an oil measuring hole 36, and the oil measuring hole 36 is installed with a locking fixed cover to improve safety. An emergency stop switch is connected to the oil pump 20, and the oil pump 20 adopts the existing oil pump 20 for aviation fuel unloading and refueling on the market. The emergency stop switch can adopt the existing switch structure on the market that can realize the emergency switch of the oil pump 20 and has a self-locking function or adopt the existing emergency shut-off valve. The specific structure of the oil pump 20 and the emergency stop switch is not repeated in this application.

[0034] The equipment has four working modes: refueling, oil collection, oil delivery and tank emptying. The specific working process is as follows (the two oil tanks 1 are respectively called oil tank A and oil tank B):

[0035] Refueling mode:

[0036] Taking the refueling of aviation fuel stored in tank A as an example, valves I, II8 and III9 are all closed, so that a passage is formed between the oil supply pipe 18 and the oil outlet pipe 13 on the oil tank A; the passage between the oil receiving joint 26 and the oil supply pipe 18 is closed; and the passage between the oil return pipe 29 and the filter separator 22 is closed.

[0037] That is to say, in the refueling mode, the refueling passage in this scheme is oil tank A-oil outlet pipe 13-oil supply common pipe 19-oil supply pipe 18-oil pump 20-first connecting pipe 21-filter separator 22-second connecting pipe 23-flow meter 24-gravity refueling pipe 12 or pressure refueling pipe 11-gravity refueling gun or pressure refueling connector. The aviation fuel is finally discharged from the gravity refueling gun or the pressure refueling connector through the refueling passage to refuel the aircraft. Depending on different situations, the two refueling modes of gravity refueling or pressure refueling can be selected.

[0038] The filter separator 22 is used to filter impurities in the aviation fuel, and the flow meter 24 is used to monitor the flow of aviation fuel in the entire refueling passage. When the flow in the refueling passage displayed by the flow meter 24 deviates greatly from the actual required flow during operation, refueling needs to be stopped and maintenance needs to be carried out.

[0039] Oil collection mode:

[0040] Taking the example of a refueling truck transporting aviation fuel into oil tank A, the passage from the oil receiving joint 26 to the oil pump 20 is opened, the passage between the oil pump 20 and the oil supply pipe 18 is closed, the passage between the filter separator 22 and the oil return pipe 29 is opened, and the passage between the filter separator 22 and the flow meter 24 is closed. That is to say, in the oil receiving mode, the oil receiving passage in this scheme is the refueling truck-oil receiving joint 26-oil pump 20-first connecting pipe 21-filter separator 22-oil return pipe 29-oil inlet common pipe 16-oil inlet pipe 17-oil tank A, and the aviation fuel in the refueling truck can enter the oil tank A through this oil receiving passage.

[0041] Hair oil mode:

[0042] Taking the example of transporting aviation fuel in tank A to a refueling truck, the passage from the flow meter 24 to the gravity refueling unit and the pressure refueling unit is closed, and the oil delivery joint and the oil tanker are connected. The oil delivery passage is tank A-oil outlet pipe 13-oil supply common pipe 19-oil supply pipe 18-oil pump 20-first connecting pipe 21-filter separator 22-second connecting pipe 23-flow meter 24-oil delivery pipe 25-oil delivery joint-oil tanker. The oil passes through the oil delivery passage and finally enters the oil tanker through the oil delivery joint.

[0043] Tank pouring mode:

[0044] When the aviation fuel in tank A needs to be emptied for maintenance, the passage between the filter separator 22 and the gravity refueling unit, the pressure refueling unit, and the oil delivery joint is closed. If there is still a large amount of aviation fuel in tank A, the remaining aviation fuel in tank A needs to be discharged into tank B. The passage for oil circulation is: tank A-oil outlet pipe 13-fuel supply common pipe 19-fuel supply pipe 18-oil pump 20-first connecting pipe 21-filter separator 22-oil return pipe 29-fuel inlet common pipe 16-oil inlet pipe 17-tank B. After the aviation fuel is discharged into tank B, tank B can still be used as usual and will not be suspended due to maintenance. During the tank emptying process, the oil return pump 20 is started, and the passage between the second closed-circuit sampler 27 and the filter separator 22 can be opened at a fixed time, and the aviation fuel that is about to enter tank B can be sampled and tested through the second closed-circuit sampler 27.

[0045] Since the oil outlet pipe 13 is connected to the lower end of the oil tank 1, when the height of the remaining aviation fuel in the oil tank 1 is lower than the height of the oil outlet pipe 13, it means that there is less aviation fuel in the oil tank 1 at this time, and the tank is stopped. Open the valve I in the emptying pipe 2 on the oil tank A, and open the valve III9 on this side at the same time, and close the valve II8 on this side, so that the aviation fuel in the oil tank A passes through the emptying pipe 2 and the sampling branch pipe 4 and enters the first closed-circuit sampler 5. The operator can observe the quality of the aviation fuel in the first closed-circuit sampler 5. After sampling and testing, the aviation fuel remaining in the sampling branch pipe 4 is discharged into the first quality inspection tank 6. At this time, close the valve III9, and open the valve II8 on this side, and the remaining aviation fuel in the oil tank A is discharged into the first quality inspection tank 6 through the emptying branch pipe 3. At this time, the operator can perform a quality test on the aviation fuel in the first quality inspection tank 6, and then determine whether this part of the aviation fuel can continue to be used.

[0046] The working process of the security mechanism in this embodiment is as follows: the security personnel can climb to the top of the oil tank 1 through the escalator 31 and check or repair the oil tank 1 in the fence 30, which can effectively solve the potential safety hazards during the inspection process of the security personnel. At the same time, the top of the oil tank 1 is provided with a fire-blocking breathing valve 33 for maintaining the air pressure balance in the oil tank 1, a manhole cover 32 for emergency pressure relief, and a level gauge for detecting the liquid level height in the oil tank 1, so as to ensure the safety of the oil tank 1 during the working process.

[0047] In the present embodiment, only one set of oil supply devices is required for multiple oil storage devices, thereby simplifying the structure. When one of the oil tanks 1 is under maintenance, only the opening and closing conditions of the valves on the oil tank 1 need to be adjusted to replace other oil tanks 1 for oil supply. This is convenient for operation and maintenance, and multiple oil tanks 1 can be used to increase the oil storage capacity of large airports for emergency use.

[0048] Example 2

[0049] The difference between this embodiment and embodiment 1 is that: there is one oil storage device and two oil supply devices, wherein the first connection unit, the second connection unit and the third connection unit are arranged differently, as follows:

[0050] like Figure 5 , Figure 6As shown, a partition 39 is fixed in the middle of the oil tank 1, and the partition 39 divides the oil tank 1 into an aviation kerosene tank 37 and an aviation gasoline tank 38. The aviation kerosene tank 37 is used to store aviation kerosene, and the aviation gasoline tank 38 is used to store aviation gasoline. The first connecting unit includes an oil outlet pipe 13 connected to the lower end of the oil tank 1, and the oil outlet pipes 13 of the two first connecting units are respectively connected to the lower end of the aviation kerosene tank 37 and the aviation gasoline tank 38. The oil pumps 20 of the two oil supply devices are respectively connected to the two oil outlet pipes 13. The second connecting unit includes an emptying pipe 2, and the emptying pipes 2 of the two second connecting units are respectively connected to the aviation gasoline tank 38 and the aviation kerosene tank 37. The middle of the emptying pipe 2 is connected to an emptying branch pipe 3, and the end of the emptying pipe 2 away from the oil tank 1 is connected to a sampling branch pipe 4. The emptying branch pipe 3 and the sampling branch pipe 4 are directly connected to the first quality inspection tank 6. The third connecting unit includes an oil return pipe 29 connected to the end face of the oil tank 1. The oil return pipes 29 of the two third connecting units are respectively connected to the aviation kerosene tank 37 and the aviation gasoline tank 38. The ends of the oil return pipe 29 away from the oil tank 1 are respectively connected to the filter separators 22 of the two oil supply devices.

[0051] A floating oil outlet unit is installed in the aviation kerosene tank 37. The floating oil outlet unit includes a buoy (not shown in the figure) arranged in the aviation kerosene tank 37. The buoy floats on the upper part of the kerosene due to the buoyancy of the kerosene. The buoy is connected with a hose. The end of the hose away from the buoy is fixed to the inner wall of the aviation kerosene tank 37 and is connected with the oil outlet pipe 13 on the aviation kerosene tank 37. Since the buoy always floats on the upper part of the kerosene, and the kerosene undergoes a certain sedimentation in the aviation kerosene tank 37, the quality of the kerosene discharged from the aviation kerosene tank 37 can be guaranteed. The floating oil outlet unit can be specifically referred to the floating oil outlet device in the prior art. Its installation and connection methods are well known to those skilled in the art, and will not be described in detail in this embodiment.

[0052] The device has three working modes of refueling, collecting oil and sending oil, excluding the tank dumping mode. In specific operation, according to the different situations of aviation kerosene or aviation gasoline required for refueling, the fuel supply device on one side of the aviation kerosene tank 37 or the aviation gasoline tank 38 can be selected to work, and the working process of the fuel supply device is consistent with that of embodiment 1.

[0053] Compared with Example 1, the oil tank 1 of this embodiment is divided into an aviation kerosene tank 37 and an aviation gasoline tank 38, which are used to store aviation kerosene and aviation gasoline respectively, and two sets of fuel supply devices are provided for refueling aviation kerosene and aviation gasoline respectively, meeting the requirement that the storage device can store different types of oil products and refill them separately. Compared with setting up two oil tanks 1, this solution divides one oil tank 1 into two, and only one oil tank 1 needs to be installed and transported, which is more convenient for the transportation and installation of the oil tank 1.

[0054] Example 3

[0055] This embodiment, based on the first embodiment, controls the operation of the entire security system through an integrated controller, as follows:

[0056] like Figure 7 As shown, the security system also includes an electro-hydraulic valve connected to the oil outlet of the oil pump 20 and used to control the opening and closing of the oil outlet of the oil pump 20. The electro-hydraulic valve is also connected to a Deadman control handle. When in use, the Deadman control handle is used to lock the operator within a certain range near the oil supply device, so that when a safety failure occurs, the operator can cut off the passage through the electro-hydraulic valve as soon as possible, thereby minimizing or eliminating the impact of the safety failure.

[0057] The security system also includes a master controller and an audible and visual alarm, both of which are located outside the oil tank 1. The input end of the master controller is electrically connected to the liquid level monitoring device (magnetostrictive level gauge 34 and / or liquid level switch 35) and the Deadman control handle to receive signals from each device, and the output end of the master controller is electrically connected to the audible and visual alarm, the emergency stop switch of the oil pump 20 and the electro-hydraulic valve to output control signals. A combustible gas detector for detecting whether a combustible gas leak occurs outside the oil tank 1 is also provided outside the oil tank 1 and / or at the connection between the oil outlet pipe 13 and the oil tank 1. The combustible gas detector is electrically connected to the master controller. The oil tank 1 is connected to an electrostatic grounding controller, which is electrically connected to the master controller.

[0058] The master controller is used to receive signals from the liquid level monitoring device, the sound and light alarm and the Deadman control handle to perform security protection control on the input or output of the oil tank 1. Specifically, two oil tanks 1 (oil tank A and oil tank B) are used as an example. Magnetostrictive level gauges 34 (respectively, level gauge A and level gauge B) for measuring the level of aviation fuel are installed on the top of oil tank A and oil tank B. The master controller can collect the level signal and temperature signal of level gauge A and level gauge B in real time in the working state of each oil tank 1, convert the level value into volume value through calculation of the master controller chip, and connect a display outside the oil tank 1 to display the empty volume, apparent volume, oil temperature and oil height in each tank on the display; the upper part of the inner wall of oil tank A and oil tank B can also be respectively provided with a level switch A and a level switch B slightly lower than each level gauge. Since the aviation fuel in the oil tank 1 is prone to tank overflow accidents when the liquid level is high, during use, when the aviation fuel level in each tank reaches or exceeds each liquid level switch 35, each liquid level switch 35 is communicated and connected to the main controller, and the main controller will output an alarm signal to the sound and light alarm to issue an sound and light prompt, and the main controller controls the emergency stop switch to shut down the oil pump 20 to stop it from running, so as to protect the oil tank 1 as a whole; the working principle of each liquid level gauge is roughly the same as that of the liquid level switch 35, that is, when the surface of the aviation fuel reaches the height of the liquid level gauge, the signal is transmitted to the main controller to control the oil pump 20 to shut down. The purpose of setting each liquid level gauge is to form a double insurance alarm interlocking control with the liquid level switch 35, which can effectively avoid the safety hazard caused by the oil pump 20 continuing to work when the liquid level switch 35 fails.

[0059] The combustible gas detector is used to monitor the oil and gas concentration outside the oil tank 1. When the combustible gas is detected to exceed the set value, the combustible gas detector outputs a signal to the main controller, and the main controller sends an alarm signal to the sound and light alarm to issue a sound and light prompt, and the main controller controls the emergency stop switch to shut down the oil pump 20 to stop it from running, so as to protect the entire oil tank 1. When the grounding is unreliable, the electrostatic grounding controller transmits an alarm signal to the main controller, and then controls the sound and light alarm to issue a sound and light prompt, and the main controller controls the emergency stop switch to shut down the oil pump 20 to stop it from running.

[0060] When the input end of the master controller is electrically connected to the Deadman control handle, and the output end of the master controller is electrically connected to the electro-hydraulic valve, the master controller is used to receive the signal sent by the Deadman control handle and is used to control the electro-hydraulic valve. The Deadman control handle can be used to control the unloading and refueling operations within a certain range. Specifically, when the aviation fuel supply equipment is unloading and refueling, the operator presses the Deadman control handle, the master controller receives the signal sent by the Deadman control handle, transmits it to the electro-hydraulic valve, the electro-hydraulic valve opens, the oil circuit is opened, and the aviation fuel supply equipment starts unloading and refueling. When the operator needs to temporarily leave the work station due to special circumstances, he needs to release the Deadman control handle, the master controller receives the signal sent by the Deadman control handle, transmits it to the electro-hydraulic valve, the electro-hydraulic valve closes, the oil circuit is closed, and the aviation fuel supply equipment stops unloading and refueling. In addition, during the normal unloading and refueling process, the Deadman control handle needs to be released and then pressed to restart within a period of time to prevent the operator from leaving the work station and ensure the safety of the entire operation process. At the same time, the circuit connecting the Deadman control handle and the main controller is also provided with a control button that exceeds the Deadman. If the Deadman control handle fails, the Deadman can be used to start and terminate the emergency control operation. The specific structure of the Deadman control handle and the electro-hydraulic valve is the structure of the Deadman control commonly used in existing aircraft refueling trucks, or adopts the structure of the Deadman handle, control circuit and electromagnetic reversing valve disclosed in the Chinese patent "A Logical Timing Intelligent Control Deadman Refueling System" with publication number CNCN201350975Y (or increase the model of the Deadman control used), which belongs to the prior art, so its specific structure will not be repeated here.

[0061] The master controller is also connected to the data monitoring machine in the monitoring room to transmit the received information to the monitoring room. The master controller has a data remote transmission interface, which can upload the data in the security protection system to the data monitoring device in the duty room. The data monitoring machine in the monitoring room can also upload the data to the data monitoring machine in the superior manager's office through a network communication connection to realize multi-level transmission of monitoring data. During the operation of the security system of the aviation fuel supply equipment in this embodiment, when the automatic control process fails, the emergency stop switch with a self-locking function can also be used to mechanically cut off the circuit and shut down the entire system in an emergency, thereby protecting the system's operational safety.

[0062] The above-mentioned master controller adopts the JSK-2012 controller developed by our company with the MSP430F169 high-end intelligent microprocessor as the core, or the existing controller on the market that can realize the corresponding control function; the sound and light alarm adopts the existing alarm on the market that can realize the corresponding function, and the combustible gas detector adopts the structure of the sensor with the combustible gas detection function in the prior art; the electrostatic grounding controller adopts the existing structure with electrostatic grounding function on the market, so the above structures are not repeated in this application. The electrical connection between the master controller and each device can realize effective control through the input / output circuit commonly used in the existing communication field and matched with the controller. The specific connection of the circuit is an existing structure, so it is not repeated here.

[0063] Example 4

[0064] This embodiment is based on the embodiment 1. Figure 8 As shown, the oil tank 1 includes an outer tank 40 and an inner tank 41 fixed in the outer tank 40, and a steel support rod 45 is fixed between the inner tank 41 and the outer tank 40, and the inner tank 41 and the outer tank 40 are fixed by the support rod 45. An interlayer 42 is formed between the inner tank 41 and the outer tank 40, and an interlayer leak detector and an interlayer breathing valve are installed between the interlayer 42. The interlayer leak detector and the interlayer breathing valve are conventional structures in the prior art, and their installation and connection methods are well known to those skilled in the art. For example, the interlayer leak detector can use the existing ET-LLD-D double-layer tank leakage detector on the market or other models of leakage detectors with the function of detecting fuel leakage in the interlayer 42 of the oil tank 1. The interlayer leak detector is used to detect whether there is fuel leakage in the interlayer 42, and the interlayer breathing valve can use the existing tank breathing valve on the market with the function of maintaining the sealing of the interlayer 42.

[0065] In this embodiment, based on the third embodiment, the interlayer leak detector can also be connected to the main controller signal, and the main controller can receive the signal sent by the interlayer leak detector. When in use, the interlayer leak detector is always open and keeps detecting whether there is a fuel leak in the interlayer 42. When there is a leak, the interlayer leak detector sends a leakage signal to the main controller, and the main controller will output an alarm signal to the sound and light alarm to send out an sound and light prompt, and the main controller controls the emergency stop switch to turn off the oil pump 20 to stop it from running, so as to protect the oil tank 1 as a whole.

[0066] Example 5

[0067] This embodiment is based on embodiment 2. Fig. 9As shown, a kerosene inner tank 43 is fixed in the aviation kerosene tank 37, and a gasoline inner tank 44 is fixed in the aviation gasoline tank 38. Steel support rods (not shown in the figure, and the specific configuration can be referred to in Example 4) are fixed between the kerosene inner tank 43 and the aviation kerosene tank 37, and between the gasoline inner tank 44 and the aviation gasoline tank 38. An interlayer 42 is formed between the kerosene inner tank 43 and the aviation kerosene tank 37, and between the gasoline inner tank 44 and the aviation gasoline tank 38, and an interlayer leak detector is installed in the interlayer 42.

[0068] Compared with Example 2, the solution in this embodiment has better separation of aviation kerosene and aviation gasoline by adding gasoline inner tank 44 and kerosene inner tank 43, thus avoiding oil pollution; and by providing gasoline inner tank 44 and kerosene inner tank 43, which are equivalent to aviation gasoline tank 38 and aviation kerosene tank 37 being double-layered, when external force is applied, the structural thickness and comprehensive strength of the double-layer oil tank 1 are higher.

[0069] Example 6

[0070] In this embodiment, based on the third embodiment, the oil supply device further comprises an authorization management module for authenticating user authority and a payment settlement module for paying oil costs. Both the authorization management module and the payment settlement module are connected to the main controller by signal.

[0071] The authorization management module can adopt multiple identification methods such as fingerprint recognition, face recognition or IC card recognition. The input end of the authorization management module is used to input identification signals (i.e., fingerprint, face or IC card signals). The identification signals input by the management personnel generate original data in the background of the main controller, and the identification signals input by other personnel are matched with the original data in the background. If the original data is matched, the output end of the authorization management module can output a signal and open authorization, which is similar to the access control system in the prior art, that is, only designated personnel or personnel with designated IC cards can pass the identification and use the oil supply device. The setting of the authorization management module is relatively conventional in the prior art and will not be repeated in this embodiment.

[0072] The input end of the payment settlement module is used to input oil price data and receive the flow signal of the flow meter. The oil price data input by the manager generates the current oil price. When the oil price changes, the manager can re-enter the oil price data. The master controller receives the flow signal from the flow meter and inputs it into the payment settlement module. The payment settlement module calculates according to the current oil price and flow signal. The output end of the payment settlement module is used to output the oil fee settlement payment data, that is, output the calculation result of multiplying the current oil price and the flow signal.

[0073] Example 7

[0074] In this embodiment, Fig.10As shown (only the specific arrangement on the right side of the oil tank 1 is shown in the figure, and the arrangement on the left side of the oil tank 1 is completely symmetrical with the right side), the oil storage device includes at least two, and the oil supply device is also provided with two. The following description is taken as an example of two oil storage devices. The oil storage device includes an oil tank 1, and a partition 39 is fixed in the middle of the oil tank 1. The partition 39 separates the oil tank 1 into an aviation kerosene tank 37 and an aviation gasoline tank 38. The arrangement of the oil storage device can be specifically referred to in Example 2. When the two oil tanks 1 are placed, the aviation kerosene tank 37 is located on one side (such as both located on the left side), and the aviation gasoline tank 38 is located on one side (such as both located on the right side) to facilitate the subsequent pipeline laying. The arrangement of the oil supply device in this embodiment specifically refers to Example 1, wherein the arrangement of the first connecting unit, the second connecting unit, and the third connecting unit are the same as in Example 1, and the two sets of oil supply devices are respectively arranged on the left and right sides of the oil tank 1, that is, they are connected to the aviation kerosene tank 37 and the aviation gasoline tank 38 respectively.

[0075] When in use, this embodiment combines Embodiment 1 and Embodiment 2. Multiple aviation kerosene tanks 37 share one set of fuel supply devices, and multiple aviation gasoline tanks 38 share one set of fuel supply devices. This is also convenient for tank emptying and maintenance. It is especially suitable for small airports. At least two oil tanks 1 and two sets of fuel supply devices need to be installed. It occupies a small area and can meet the requirements of tank emptying and storage and separate filling of two types of aviation fuel.

[0076] Finally, it should be noted that the above embodiments are only used to illustrate the technical solution of the present invention rather than to limit it. Although the present invention has been described in detail with reference to the preferred embodiments, those skilled in the art should understand that the technical solution of the present invention can be modified or replaced by equivalents without departing from the purpose and scope of the technical solution of the present invention, which should be included in the scope of the claims of the present invention.

Claims

1. Integrated aviation fuel supply equipment, characterized by: It includes an oil storage device, an oil supply device and a security system, and the oil storage device includes an oil tank; The fuel supply device includes a fueling mechanism for delivering aviation fuel in the fuel tank to an external fuel receiving part, a fuel receiving mechanism for introducing external aviation fuel into the fuel tank, a quality inspection mechanism for conducting quality inspection on the aviation fuel, and an emptying mechanism for emptying the aviation fuel in the fuel tank; The oil filling mechanism includes an oil pump, a filter separator, and a flow meter which are connected in sequence. The outlet end of the flow meter is connected to a gravity refueling unit, a pressure refueling unit, and an oil delivery joint. The oil inlet end of the oil pump is connected to a first connection unit for connecting with an oil tank. The gravity refueling unit includes a gravity refueling pipe, the pressure refueling unit includes a pressure refueling pipe, and the oil filling mechanism also includes two sets of reels for winding the pressure refueling pipe and the gravity refueling pipe respectively. The emptying mechanism includes a first quality inspection tank, a second connection unit is connected between the first quality inspection tank and the oil tank, the second connection unit includes an emptying pipe connected to the lower end of the oil tank, an emptying branch pipe and a sampling branch pipe connected to the emptying pipe, and the sampling branch pipe is connected to a first closed-circuit sampler; The oil collecting mechanism comprises an oil collecting joint connected to the oil inlet end of the oil pump and a third connecting unit connected between the filter separator or the flow meter and the oil tank; The quality inspection mechanism includes an oil return pump, a second quality inspection tank and a second closed-circuit sampler which are connected in sequence, and the oil return pump is connected between the filter separator and the oil tank; The security system includes a flame-retardant breathing valve installed on the upper end of the oil tank for maintaining the air pressure balance in the oil tank, a manhole cover for emergency pressure relief of the oil tank, and a liquid level detection component for detecting the aviation fuel level in the oil tank. The security system also includes a combustible gas detector for detecting whether there is a combustible gas leak outside the oil tank, and an electro-hydraulic valve connected to the oil outlet of the oil pump and controlling the opening and closing of the oil outlet of the oil pump. The electro-hydraulic valve is connected to a Deadman control handle.

2. The integrated aviation fuel supply equipment according to claim 1, characterized in that: The oil tanks are provided with at least two, the first connecting unit includes an oil supply common pipe for connecting with the oil pump and an oil outlet pipe connected with the oil tank, the oil outlet pipe on each oil tank is connected with the oil supply common pipe, and an oil supply valve is installed on the oil tank at a position connected with the oil outlet pipe.

3. The integrated aviation fuel supply equipment according to claim 1, characterized in that: A partition is fixed in the middle of the oil tank, which divides the oil tank into an aviation kerosene tank and an aviation gasoline tank. The first connecting unit includes two oil outlet pipes respectively connected to the aviation kerosene tank and the aviation gasoline tank; the oil supply device is provided with two oil pumps, and the oil pumps of the two oil supply devices are respectively connected to the two oil outlet pipes.

4. The integrated aviation fuel supply equipment according to claim 1, characterized in that: The oil tank includes an outer tank and an inner tank fixed in the outer tank, and a sandwich is formed between the inner tank and the outer tank. The security system also includes a sandwich leak detector installed in the sandwich for detecting fuel leakage in the sandwich and a sandwich breathing valve for maintaining the sealing of the sandwich.

5. The integrated aviation fuel supply equipment according to claim 1, characterized in that: The security system also includes a main controller and an audible and visual alarm. The input end of the main controller is electrically connected to the liquid level monitoring device and the Deadman control handle to receive signals from each device. The output end of the main controller is electrically connected to the audible and visual alarm, the oil pump, and the electro-hydraulic valve to output control signals. The main controller is also provided with a data remote transmission interface.

6. The integrated aviation fuel supply equipment according to claim 1, characterized in that: The oil supply device also includes an authorization management module for authenticating user permissions and a payment settlement module for paying oil costs. The input end of the payment settlement module is used to input oil price data and receive flow signals from a flow meter, and the output end of the payment settlement module is used to output oil fee settlement payment data.

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