CN113998138A - Wet wing refueling system for aircraft - Google Patents
Wet wing refueling system for aircraft Download PDFInfo
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- CN113998138A CN113998138A CN202111466861.5A CN202111466861A CN113998138A CN 113998138 A CN113998138 A CN 113998138A CN 202111466861 A CN202111466861 A CN 202111466861A CN 113998138 A CN113998138 A CN 113998138A
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- oil
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F1/00—Ground or aircraft-carrier-deck installations
- B64F1/28—Liquid-handling installations specially adapted for fuelling stationary aircraft
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- Aviation & Aerospace Engineering (AREA)
- Loading And Unloading Of Fuel Tanks Or Ships (AREA)
Abstract
The invention belongs to the technical field of aircraft refueling, and particularly discloses a wet wing refueling system for an aircraft, which comprises a base, a pipeline assembly, an explosion-proof oil discharge pump and a filtering separator, wherein the pipeline assembly, the explosion-proof oil discharge pump and the filtering separator are all fixed on the base, the pipeline assembly comprises an oil inlet pipe and an oil outlet pipe, the filtering separator is connected between the oil inlet pipe and the oil outlet pipe, the inlet pressure of the oil inlet pipe is less than or equal to 0.15Mpa, and the outlet pressure of the oil outlet pipe is 0.345Mpa or less and P is less than or equal to 0.375 Mpa. By adopting the scheme of the invention, the base, the pipeline assembly, the explosion-proof oil discharge pump and the filtering separator are integrated into the refueling system, and the refueling system can be carried by a large airplane, so that temporary oil transfer between the large airplane and an aircraft (small airplane) can be realized by the refueling system provided by the scheme under the wartime or emergency condition, thereby effectively dealing with ground refueling under special conditions and supplementing the current ground refueling mode.
Description
Technical Field
The invention belongs to the technical field of aircraft refueling, and particularly relates to a wet wing refueling system for an aircraft.
Background
The aviation aircraft mainly has two refueling modes at present: air refueling and ground refueling; wherein, whether the fighter, the bomber, the transporter or the helicopter generally has the air refueling capability; and the ground refueling comprises: gravity refueling and pressure refueling; the gravity refueling refers to a fuel refueling mode that fuel flows into an aircraft from a fuel tank upper fuel filler opening of a large aircraft by means of the weight of the fuel. Similarly, pressure refueling refers to a fuel filling method for filling fuel from a fuel supply pipeline or a refueling truck into an aircraft fuel tank or an external fuel tank through a pressure refueling joint.
The main advantages of pressure refueling compared with gravity refueling are that the fuel refueling speed is high, safety is high, less manpower is needed, most of the existing fighters refuel in a pressure refueling mode, a refueling truck is usually adopted to supply fuel in the pressure refueling mode, but the refueling truck is blocked to supply fuel in some special scenes, such as emergency states in wartime, road blocking and the like, and the fuel supply in the situations cannot be met.
Disclosure of Invention
Aiming at the defects in the prior art, the invention provides a wet wing refueling system for an aircraft, which realizes temporary oil transfer between a large aircraft and the aircraft in wartime or emergency so as to perfect the ground refueling mode of the aircraft in special situations.
In order to achieve the purpose, the invention adopts the following technical scheme:
a wet wing refueling system for aircraft, including base, pipeline assembly, explosion-proof oil discharge pump and filtering separator all fix on the base, pipeline assembly is including advancing oil pipe and play oil pipe, and filtering separator connects into oil pipe and play oil pipe between, advances oil pipe's entry pressure and is less than or equal to 0.15Mpa, and the export pressure that goes out oil pipe is 0.345Mpa and is less than or equal to P and is less than or equal to 0.375 Mpa.
Compared with the prior art, the invention has the following beneficial effects:
adopt base, pipeline assembly, explosion-proof oil discharge pump and filtering separator integrated refueling system in this scheme, this refueling system can be carried by big aircraft, like this under wartime or emergency situation, through the refueling system that this scheme provided, can realize the interim commentaries on classics oil between large aircraft and aircraft (little aircraft) to ground refueling under can effectively coping with special situation has supplemented the mode of refueling on present ground.
Further, the base includes the framework of rectangle, the truckle is installed to the bottom of framework, still be equipped with a plurality of locating parts in the framework, the locating part includes screw rod and spacing dish, spacing dish is fixed in the screw rod bottom, and screw rod threaded connection is in the framework, and threaded connection has the lock nut who is located the framework upper and lower side on the screw rod, still be equipped with a plurality of stands in the framework.
Has the advantages that: the base that sets up like this can freely remove on the one hand, and on the other hand can make spacing dish compress tightly subaerial through adjusting screw at the during operation, improves the stability of base.
Further, the oil inlet of the oil inlet pipe and the oil outlet of the oil outlet pipe are both connected with an aviation oil delivery pressure joint.
Has the advantages that: this ensures that the fitting can be fitted through the duct with the joints at the large aircraft end as well as at the small aircraft end.
Further, the oil inlet pipe is provided with a flowmeter, and the oil outlet of the oil outlet pipe is provided with a pressure detection sensor.
Has the advantages that: the flow of the oil supply can be accurately controlled through the flowmeter, the pressure of the oil outlet can be detected through the pressure detection sensor, and the safety of the oil transferring process is guaranteed.
Further, the oil inlet of the oil inlet pipe is provided with a valve I, the oil outlet of the oil inlet pipe is provided with a valve II, and the oil outlet pipe is provided with a valve III.
Has the advantages that: the adjustment of the flow and the pressure of the oil inlet pipe and the oil outlet pipe is realized through the arrangement of a plurality of valves.
Further, still include the oil gas recovery subassembly, the oil gas recovery subassembly includes first pressure release blast pipe, second pressure release blast pipe, explosion-proof oil-well pump and oil tank, first pressure release blast pipe is connected in the oil inlet department that advances oil pipe, first pressure release blast pipe and explosion-proof oil-well pump are connected, be equipped with valve IV near the oil inlet on the first pressure release blast pipe and be close to explosion-proof oil-well pump's valve VII, oil pipe and oil tank are connected to second pressure release blast pipe, be connected with the intervalve between first pressure release blast pipe and the second pressure release blast pipe, be equipped with valve V on the second pressure release blast pipe, valve VI and valve VIII, valve V is close to the intervalve setting, valve VI is close to oil pipe setting, valve VIII is close to the oil tank setting.
Has the advantages that: the arrangement can discharge the pressure and residual fuel in the pipelines at the large airplane end and the small airplane end into the fuel tank or pump out the fuel in the pipelines through the explosion-proof oil well pump.
Further, the oil gas recovery subassembly still includes third pressure release blast pipe, and filter separator and oil tank are connected to third pressure release blast pipe, and the discharge port department of oil tank is equipped with valve IX, is equipped with the blow off pipe on the filter separator, is equipped with valve X on the blow off pipe.
Has the advantages that: therefore, residual oil gas in the filtering separator can be decompressed into the oil tank, and oil stains are discharged from the sewage discharge pipe.
Furthermore, still include explosion-proof block terminal and fire extinguisher, explosion-proof block terminal and fire extinguisher all fix on the base, and explosion-proof oil discharge pump and explosion-proof oil-well pump all supply power through explosion-proof block terminal.
Has the advantages that: the safety of explosion-proof oil discharge pump and explosion-proof oil-well pump in refueling system can be improved to the setting like this, and the configuration of fire extinguisher can be used when the condition of a fire appears fast in addition, reduces the loss.
Drawings
FIG. 1 is a schematic flow diagram of an embodiment of a wet wing fueling system for an aircraft of the present invention.
FIG. 2 is an isometric view of an embodiment of a wet wing refueling system for an aircraft according to the present invention.
FIG. 3 is an isometric view of a base in an embodiment of the wet wing refueling system for aircraft of the present invention.
Reference numerals in the drawings of the specification include: the device comprises a small aircraft end 1, a large aircraft end 2, a base 10, an explosion-proof oil discharge pump 11, a filtering separator 12, an explosion-proof distribution box 13, a fire extinguisher 14, a frame 101, casters 102, a screw 103, a limiting disc 104, a locking nut 105, an oil inlet pipe 15, an oil outlet pipe 16, an aviation oil transportation pressure joint 17, a valve I18, a valve II 19, a valve III 20, a first pressure relief exhaust pipe 21, a second pressure relief exhaust pipe 22, a third pressure relief exhaust pipe 23, an explosion-proof oil well pump 24, an oil tank 25, a valve IV 26, a valve VII 27, a safety valve 28, a middle pipe 29, a valve V30, a valve VI 31, a valve VIII 32, a valve IX 33, a valve X34 and an oil sac 35.
Detailed Description
The invention is further described in detail below with reference to the accompanying drawings, and specific embodiments are given.
Embodiment as shown substantially in fig. 1, 2 and 3, a wet wing refueling system for aircraft includes a base 10, a piping assembly, an explosion-proof fuel dump pump 11, a filter separator 12, an explosion-proof electric box 13, a fire extinguisher 14, an oil and gas recovery assembly. The pipeline assembly, the explosion-proof oil discharge pump 11, the filtering separator 12, the explosion-proof distribution box 13, the fire extinguisher 14 and the oil gas recovery assembly are all fixedly arranged on the base 10.
The model of the explosion-proof oil discharge pump 11 in the present embodiment: CZB 80-40/40; flow rate: 45m3H; lift: 40 m; motor power: 5.5 Kw; suction lift: 7 m.
In this embodiment, the base 10 includes a rectangular frame 101, casters 102 located at four vertex angles are installed at the bottom of the frame 101, and a plurality of limiting members are further disposed on the frame 101, where the limiting members include a screw 103 and a limiting disc 104, the limiting disc 104 is fixed at the bottom of the screw 103, the screw 103 is connected to the frame 101 through a thread, and the screw 103 is connected to lock nuts 105 located on the upper and lower sides of the frame 101 through a thread; the frame 101 is further provided with a plurality of columns for supporting other components.
The pipeline assembly in the embodiment comprises an oil inlet pipe 15 and an oil outlet pipe 16, a filtering separator 12 is connected between the oil inlet pipe 15 and the oil outlet pipe 16, an oil inlet of the oil inlet pipe 15 and an oil outlet of the oil outlet pipe 16 are both connected with an aviation oil transportation pressure joint 17, the inlet pressure of the oil inlet pipe 15 is less than or equal to 0.15Mpa, and the outlet pressure of the oil outlet pipe 16 is 0.345Mpa less than or equal to P less than or equal to 0.375 Mpa; advance oil pipe 15 in this embodiment including advancing oil pipe I, advance oil pipe II and advance oil pipe III, advance oil pipe I, advance oil pipe II and advance oil pipe III and connect through pipeline flange respectively, advance to be equipped with the flowmeter on the oil pipe I, explosion-proof oil discharge pump 11 is connected on advancing oil pipe II, advances oil pipe III and is connected with filter separator 12.
The oil outlet of the oil outlet pipe 16 is provided with a pressure detection sensor, when the pressure exceeds a threshold value, an audible and visual alarm is given out, the oil inlet of the oil inlet pipe 15 is provided with a valve I18, the oil outlet of the oil inlet pipe is provided with a valve II 19, and the oil outlet pipe is provided with a valve III 20.
The oil-gas recovery assembly in this embodiment includes a first pressure relief exhaust pipe 21, a second pressure relief exhaust pipe 22, a third pressure relief exhaust pipe 23, an explosion-proof oil-well pump 24 and an oil tank 25, wherein the model of the explosion-proof oil-well pump 24: 20 GZB-3/2.5K; flow rate: 50L/min; lift: 20 m; suction lift: 5M. The explosion-proof oil discharge pump 11 and the explosion-proof oil well pump 24 are both powered by the explosion-proof distribution box 13.
The first pressure relief and exhaust pipe 21 is connected to an oil inlet of the oil inlet pipe 15, the first pressure relief and exhaust pipe 21 is connected with the explosion-proof oil well pump 24, the first pressure relief and exhaust pipe 21 is provided with a valve IV 26 close to an oil inlet and a valve VII 27 close to the explosion-proof oil well pump, the first pressure relief and exhaust pipe 21 is further provided with a safety valve 28 located between the valve IV 26 and the valve VII 27, when the pressure at the oil inlet exceeds 0.375MPa, the safety valve 28 performs pressure relief protection, and the pressure at the oil inlet is ensured to be below 0.375 MPa.
The second pressure relief exhaust pipe 22 is connected with the oil outlet pipe 26 and the oil tank 25, an intermediate pipe 29 is connected between the first pressure relief exhaust pipe 21 and the second pressure relief exhaust pipe 22, a valve V30, a valve VI 31 and a valve VIII 32 are arranged on the second pressure relief exhaust pipe 22, the valve V30 is arranged close to the intermediate pipe 29, the valve VI 31 is arranged close to the oil outlet pipe 16, the valve VIII 32 is arranged close to the oil tank 25, the third pressure relief exhaust pipe 23 is connected with the filtering separator 12 and the oil tank 25, a valve IX 33 is arranged at the outlet of the oil tank 25, a drain pipe is arranged on the filtering separator 12, a valve X34 is arranged on the drain pipe, and when the oil-gas recovery assembly is in use, the explosion-proof oil-well pump 24 is further connected with an oil sac 35.
The working principle of oil transfer, pressure relief and oil discharge in this embodiment is shown in table 1 below.
TABLE 1 working principle table for oil transfer, pressure relief and oil discharge
The process of transferring oil from the large airplane end 2 to the small airplane end 1 is as follows: opening the valve I, the valve II, the valve III, the valve IV and the valve VI, closing the valve V, the valve VII, the valve VIII, the valve IX and the valve X, starting the explosion-proof oil unloading pump, and conveying the fuel oil at the large airplane end 2 to the small airplane end 1.
Pressure relief of a pipeline at the large airplane end 2: the valves iv and viii are opened and the other valves are closed, so that the pressure in the large aircraft end 2 line can be relieved into the tank.
Thirdly, pressure relief of a pipeline at the small airplane end 1: the valves V, VII and VIII are opened and the other valves are closed, thus the pressure in the pipeline at the small aircraft end 1 can be discharged into the oil tank.
Fourthly, oil is discharged from the pipeline at the end 2 of the large airplane: and opening the valve IV and the valve VII, closing other valves, and pumping oil gas in the pipeline at the end 2 of the large aircraft into the oil bag through the explosion-proof oil well pump.
Pipeline oil discharge of the small airplane end 1: and opening the valve V, the valve VI and the valve VII, closing other valves, and pumping oil gas in the pipeline at the small aircraft end 1 into the oil bag through the explosion-proof oil well pump.
It is noted that, herein, relational terms such as first and second, and the like may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus.
Finally, the above embodiments are only for illustrating the technical solutions of the present invention and not for limiting, although the present invention has been described in detail with reference to the preferred embodiments, it should be understood by those skilled in the art that modifications or equivalent substitutions may be made to the technical solutions of the present invention without departing from the spirit and scope of the technical solutions of the present invention, and all of them should be covered in the claims of the present invention.
Claims (8)
1. A wet wing refueling system for aircraft, its characterized in that: including base, pipeline assembly, explosion-proof oil discharge pump and filtering separator all fix on the base, pipeline assembly is including advancing oil pipe and going out oil pipe, and filtering separator connects into oil pipe and goes out between the oil pipe, advances oil pipe's entry pressure and is less than or equal to 0.15Mpa, and the export pressure that goes out oil pipe is 0.345Mpa and is less than or equal to P and is less than or equal to 0.375 Mpa.
2. The wet wing refueling system for aircraft as recited in claim 1 wherein: the base includes the framework of rectangle, the truckle is installed to the bottom of framework, still be equipped with a plurality of locating parts in the framework, the locating part includes screw rod and spacing dish, spacing dish is fixed in the screw rod bottom, and screw rod threaded connection is in the framework, and threaded connection has the lock nut who is located the framework upper and lower side on the screw rod, still be equipped with a plurality of stands in the framework.
3. The wet wing refueling system for aircraft as recited in claim 1 wherein: the oil inlet of the oil inlet pipe and the oil outlet of the oil outlet pipe are both connected with an aviation oil delivery pressure joint.
4. The wet wing refueling system for aircraft as recited in claim 3 wherein: the oil inlet pipe is provided with a flowmeter, and the oil outlet of the oil outlet pipe is provided with a pressure detection sensor.
5. The wet wing refueling system for aircraft according to claim 4 wherein: the oil inlet of the oil inlet pipe is provided with a valve I, the oil outlet of the oil inlet pipe is provided with a valve II, and the oil outlet pipe is provided with a valve III.
6. The wet wing refueling system for aircraft according to claim 5, wherein: still include the oil gas recovery subassembly, the oil gas recovery subassembly includes first pressure release blast pipe, second pressure release blast pipe, explosion-proof oil-well pump and oil tank, first pressure release blast pipe is connected in the oil inlet department that advances oil pipe, first pressure release blast pipe and explosion-proof oil-well pump are connected, be equipped with valve IV near the oil inlet on the first pressure release blast pipe and be close to explosion-proof oil-well pump's valve VII, oil pipe and oil tank are connected to second pressure release blast pipe, be connected with the intervalve between first pressure release blast pipe and the second pressure release blast pipe, be equipped with valve V on the second pressure release blast pipe, valve VI and valve VIII, valve V is close to the intervalve setting, valve VI is close to oil pipe setting, valve VIII is close to the oil tank setting.
7. The wet wing refueling system for aircraft according to claim 6 wherein: the oil gas recovery subassembly still includes third pressure release blast pipe, and filter separator and oil tank are connected to third pressure release blast pipe, and the discharge port department of oil tank is equipped with valve IX, is equipped with the blow off pipe on the filter separator, is equipped with valve X on the blow off pipe.
8. The wet wing refueling system for aircraft as recited in claim 7 wherein: still include explosion-proof block terminal and fire extinguisher, explosion-proof block terminal and fire extinguisher all fix on the base, and explosion-proof oil discharge pump and explosion-proof oil-well pump all supply power through explosion-proof block terminal.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111466861.5A CN113998138A (en) | 2021-12-01 | 2021-12-01 | Wet wing refueling system for aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111466861.5A CN113998138A (en) | 2021-12-01 | 2021-12-01 | Wet wing refueling system for aircraft |
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| Publication Number | Publication Date |
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| CN113998138A true CN113998138A (en) | 2022-02-01 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111466861.5A Pending CN113998138A (en) | 2021-12-01 | 2021-12-01 | Wet wing refueling system for aircraft |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115353061A (en) * | 2022-10-21 | 2022-11-18 | 中国航空油料有限责任公司成都分公司 | Pressure relief protection system of aircraft ground oil filling pipeline |
-
2021
- 2021-12-01 CN CN202111466861.5A patent/CN113998138A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115353061A (en) * | 2022-10-21 | 2022-11-18 | 中国航空油料有限责任公司成都分公司 | Pressure relief protection system of aircraft ground oil filling pipeline |
| CN115353061B (en) * | 2022-10-21 | 2023-01-17 | 中国航空油料有限责任公司成都分公司 | Pressure relief protection system of aircraft ground oil filling pipeline |
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