CN112706931A - Unmanned aerial vehicle fuel supply system and fuel supply and refueling control method - Google Patents
Unmanned aerial vehicle fuel supply system and fuel supply and refueling control method Download PDFInfo
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- CN112706931A CN112706931A CN202110112374.2A CN202110112374A CN112706931A CN 112706931 A CN112706931 A CN 112706931A CN 202110112374 A CN202110112374 A CN 202110112374A CN 112706931 A CN112706931 A CN 112706931A
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- 239000000446 fuel Substances 0.000 title claims abstract description 78
- 238000000034 method Methods 0.000 title claims abstract description 30
- 239000003921 oil Substances 0.000 claims abstract description 252
- 239000000295 fuel oil Substances 0.000 claims abstract description 14
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims abstract description 4
- 239000002828 fuel tank Substances 0.000 claims description 16
- 238000012544 monitoring process Methods 0.000 claims description 12
- 239000000945 filler Substances 0.000 claims description 9
- 230000005484 gravity Effects 0.000 description 5
- 230000008569 process Effects 0.000 description 5
- 239000002131 composite material Substances 0.000 description 2
- 230000008878 coupling Effects 0.000 description 2
- 238000010168 coupling process Methods 0.000 description 2
- 238000005859 coupling reaction Methods 0.000 description 2
- 230000003247 decreasing effect Effects 0.000 description 2
- 239000003292 glue Substances 0.000 description 2
- 239000010705 motor oil Substances 0.000 description 2
- 239000011435 rock Substances 0.000 description 2
- 229920000049 Carbon (fiber) Polymers 0.000 description 1
- 230000002411 adverse Effects 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 239000004917 carbon fiber Substances 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000001066 destructive effect Effects 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000003365 glass fiber Substances 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 1
- 238000012806 monitoring device Methods 0.000 description 1
- 238000005086 pumping Methods 0.000 description 1
- 230000008439 repair process Effects 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D37/00—Arrangements in connection with fuel supply for power plant
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/12—Propulsion using turbine engines, e.g. turbojets or turbofans
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Loading And Unloading Of Fuel Tanks Or Ships (AREA)
Abstract
The invention discloses an unmanned aerial vehicle fuel oil supply system and a fuel oil supply and supply control method, wherein a part of an oil tank group in the system is respectively connected with a pressurized oil pump through a first pipeline; the pressurized oil pump is connected with the pressurized oil tank through a third pipeline; the other part of the oil tank group is respectively connected with the oil filling port through a second pipeline; the pressurized oil tank is connected with the engine through an oil supply assembly; a four-way joint is arranged between the pressure oil pump and the first pipeline, and one end of the four-way joint is connected with the second pipeline through a fuel sequence control valve; the controller is respectively connected with the pressurized oil pump, the oil supply assembly and the fuel oil sequence control valve; the controller is also connected with the flight control computer and used for receiving the pressurization command and sending the oil pressure and flow value. The invention can ensure that the oil supply system has a relative pressure of 25-50 kpa under the condition of 1-6 g of overload in use within the height range of 0-20000 m, and can ensure that the oil is smoothly supplied to the engine.
Description
Technical Field
The invention belongs to the technical field of fuel supply equipment of unmanned aerial vehicles, and particularly relates to a fuel supply system of an unmanned aerial vehicle and a fuel supply and refueling control method.
Background
The long-endurance unmanned aerial vehicle is a large-mobility recoverable unmanned aerial vehicle system and has the advantages of invisibility, high speed (high subsonic speed to supersonic speed) and large mobility (stable 6G and instantaneous 9G).
The design scheme adopted by the pressure-maintaining oil supply prior art adopts the air-bleed pressurization from an engine, therefore, a turbojet engine used for an unmanned aerial vehicle is provided with an engine air-bleed port, namely a small amount of high-pressure airflow is led out from the back of an engine compressor and is input into an oil tank cabin to pressurize the inside or outside of the oil tank, and the oil tank is a rubber soft oil tank, but the pressure (pressure) of the turbojet engine pressurized outside the oil tank or inside the oil tank is born by a hard shell bearing structure of an aircraft body, and because the turbojet engine has large oil consumption, the onboard fuel oil carrying capacity is large, generally accounts for 25 to 40 percent of the total weight of the aircraft takeoff, and accounts for the equivalent percentage of the volume of the aircraft body. In terms of pressure, a pressure of 50Kpa means that 0.5 kg of force is applied per square centimetre and for an aircraft structure having a tank area of 1 square metre the tension to be experienced is 5000 kg.
At present, a composite material structure (whether glass fiber, carbon fiber or other composite materials) is basically adopted for connecting body structures from small unmanned aerial vehicles to large unmanned aerial vehicles, most of the body structures are connected by glue, particularly the connection between a body skin of an airplane and a body frame and a beam, the peeling strength of the glue connection structure is very low, and the pressure input into an oil tank cabin generates the tension with extremely strong destructive force, namely the peeling force; once the structural connection is peeled off, the structural strength of the airplane is reduced sharply, and the airplane can be disassembled in severe cases. In addition to the peel failure, the pressure may cause the related aircraft profile plate to bulge and deform, thereby destroying the aircraft aerodynamic profile, increasing the aircraft drag, and decreasing the flight performance of the aircraft.
In addition, in order to pressurize, the structure of the engine body needs to be sealed, the seal can bear the expansion pressure of inflation while bearing the pneumatic load of flight, and ensure that the deformation (bending and torsion) of the engine body under various stress conditions can not cause air leakage of the sealed cabin, once the air leakage occurs, oil can not be supplied to the engine, thereby causing serious accidents of parking in the air; the secondary sealing is difficult to carry out during repair, the requirements on the structural design and the manufacturing process of the machine body are high, and the cost is greatly increased.
Disclosure of Invention
In view of this, the main object of the present invention is to provide a fuel supply system for an unmanned aerial vehicle and a fuel supply and refueling control method.
In order to achieve the purpose, the technical scheme of the invention is realized as follows:
the embodiment of the invention provides an unmanned aerial vehicle fuel supply system, which comprises an oil tank group, a first pipeline, a second pipeline, an oil filling port, a pressurized oil pump, a pressurized oil tank, a controller and an oil supply assembly, wherein the oil tank group comprises a first oil tank, a second oil tank, a first oil tank and a second oil tank;
one part of the oil tank group is connected with the pressurized oil pump through a first pipeline respectively;
the pressurized oil pump is connected with the pressurized oil tank through a third pipeline;
the other part of the oil tank group is connected with the oil filling port through a second pipeline respectively;
the pressurized oil tank is connected with the engine through an oil supply assembly;
a four-way joint is arranged between the pressure oil pump and the first pipeline, and one end of the four-way joint is connected with the second pipeline through a fuel sequence control valve;
the controller is respectively connected with the pressurized oil pump, the oil supply assembly and the fuel oil sequence control valve; the controller is also connected with the flight control computer, receives the pressurization command and sends the oil pressure and flow value.
In the above scheme, the device further comprises a ball valve, and the second pipeline is further connected with a third pipeline through the ball valve and used for pumping air on the ground or filling oil.
In the scheme, the pressure monitoring device further comprises a pressure monitoring assembly, and the other end of the four-way joint is connected with the pressurizing oil tank through the pressure monitoring assembly.
In the above scheme, the pressure monitoring subassembly includes relief pressure valve, pressure detector, the relief pressure valve sets up and forms pressure release circuit on the pipeline between the one end of four way connection and the pressurization oil tank, pressure detector sets up on the relief pressure valve, or on the pipeline between relief pressure valve and the pressurization oil tank, or set up on other pipelines that directly link to each other with the pressurization oil tank, the controller is connected with pressure detector.
In the above scheme, the oil tank group includes preceding oil tank, back oil tank, preceding oil tank, back oil tank constitute by the split type soft oil tank in a plurality of groups vacuum, the split type soft oil tank in a plurality of groups vacuum of preceding oil tank respectively with first tube coupling, the split type soft oil tank in a plurality of groups vacuum of back oil tank respectively with the second tube coupling.
In the above scheme, the fuel feeding subassembly includes that fourth pipeline, oil strain, flowmeter, total oil way solenoid valve, engine main oil pump, the pressurization oil tank passes through the fuel feeding subassembly and is connected with the engine, the fourth pipeline sets gradually flowmeter, total oil way solenoid valve, engine main oil pump along the fuel feeding direction, the oil strain sets up between flowmeter and pressurization oil tank, or between flowmeter and the total oil way solenoid valve, the flowmeter is connected with the controller, total oil way solenoid valve, engine main oil pump are connected with the engine controller respectively.
The embodiment of the invention also provides an oil supply control method of the fuel oil supply system of the unmanned aerial vehicle, which comprises the following steps: at unmanned aerial vehicle early stage flight in-process, the ball valve defaults to be in the closed condition, the controller drive the fuel sequential control valve is closed to the pressurized oil pump, the preceding oil tank of oil tank group supplies oil in to the pressurized oil tank through first pipeline, fuel in the pressurized oil tank passes through fuel feeding assembly and carries to the engine.
In the above scheme, the method further comprises: at unmanned aerial vehicle back-phase flight in-process, the ball valve defaults to be in the closed condition, the controller drive the fuel sequence control valve is opened to the pressurized oil pump, the back oil tank of oil tank group passes through second pipeline, pressurized oil pump fuel feeding in to the pressurized oil tank, the fuel in the pressurized oil tank passes through fuel feeding unit and carries to the engine.
In the above scheme, the pressure detector of the pressure monitoring assembly collects the pressure in the pressurized oil tank, and the controller determines whether to increase or decrease the pressure in the pressurized oil tank according to the pressure condition in the pressurized oil tank.
The embodiment of the invention also provides a refueling control method of the fuel oil supply system of the unmanned aerial vehicle, which comprises the following steps: bleed and refuel in-process at unmanned aerial vehicle, the manual ball valve of opening, the fuel sequence control valve is opened to the controller, and fuel filling equipment bleeds and refuels through oil filler hole, second pipeline to the back oil tank of oil tank group, bleeds and refuels through the anterior segment of oil filler hole, second pipeline through fuel sequence control valve and four way connection to the preceding oil tank of first pipeline to the oil tank group, bleeds and refuels through oil filler hole, ball valve to the oil tank that pressurizes, until all oil tank gas clean-outs and fuel fill up.
Compared with the prior art, the invention can ensure that the oil supply system has the relative pressure of 25-50 kpa (or other pressure ranges) under the condition of 1-6 g of overload in use within the height range of 0-20000 m, and can ensure that the oil is smoothly supplied to the engine.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate embodiment(s) of the invention and together with the description serve to explain the invention without limiting the invention. In the drawings:
fig. 1 is a schematic structural diagram of a fuel supply system of an unmanned aerial vehicle according to an embodiment of the present invention;
fig. 2 is a flowchart of an oil supply control method of an unmanned aerial vehicle fuel supply system according to an embodiment of the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in further detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
The embodiment of the invention provides an unmanned aerial vehicle fuel supply system, which comprises an oil tank group 1, a first pipeline 2, a second pipeline 3, an oil filling port 4, a pressurized oil pump 6, a pressurized oil tank 7, a controller 8 and an oil supply assembly 9, wherein the first pipeline 2 is connected with the second pipeline 3;
one part of the oil tank group 1 is respectively connected with a pressurized oil pump 6 through a first pipeline 2;
the pressurized oil pump 6 is connected with the pressurized oil tank 7 through a third pipeline 61;
the other part of the oil tank group 1 is respectively connected with an oil filling port 4 through a second pipeline 3;
the pressurized oil tank 7 is connected with an engine through an oil supply assembly 9;
a four-way joint 11 is arranged between the pressure oil pump 6 and the first pipeline 2, and one end of the four-way joint 11 is connected with the second pipeline 3 through a fuel sequence control valve 12;
the controller 8 is respectively connected with the pressurized oil pump 6, the oil supply assembly 9 and the fuel sequence control valve 12; the controller 8 is also connected with a flight control computer, receives a pressurization command and sends oil pressure and flow values.
The controller 8 is connected with the pressurized oil pump 6 and used for adjusting the working state of the pressurized oil pump, the controller 8 is connected with the oil supply assembly 9 and used for collecting the fuel consumption and controlling the opening time of the fuel sequence control valve 12 according to the fuel consumption, the controller 8 is connected with the pressure detection assembly 10 and used for collecting the pressure in the pressurized oil tank and controlling the rotating speed of the pressurized oil pump by using the pressure, and the controller 8 is connected with the fuel sequence control valve 12 and used for controlling the opening and the closing of the pressurized oil pump.
Further, still include pressure monitoring subassembly 10, set up four-way connection 11 between pressurization oil pump 6 and the first pipeline 2, the one end of four-way connection 11 is passed through pressure monitoring subassembly 10 and is connected with pressurization oil tank 7.
The pressure monitoring assembly 10 comprises a pressure reducing valve 1001 and a pressure detector 1002, the pressure reducing valve 1001 is arranged on a pipeline between one end of the four-way joint 11 and the pressurized oil tank 7 to form a pressure relief loop, the pressure detector 1002 is arranged on the pressure reducing valve 1001, or a pipeline between the pressure reducing valve 1001 and the pressurized oil tank 7, or other pipelines directly connected with the pressurized oil tank, and the controller 8 is connected with the pressure detector 1002.
The pressure detector 1002 detects the pressure in the pressurized oil tank 7 by using a pressure sensor, i.e., a pressure transmitter; may be installed on the pressure reducing valve 1001, in the line between the pressure reducing valve 1001 and the pressurized oil tank 7, in the line between the pressurized oil pump 6 and the pressurized oil tank 7, and in the line between the oil filter 91 and the pressurized oil tank 7.
The pressure reducing valve 1001 is a mechanical pressure reducing valve, and the opening pressure can be adjusted as needed, and when the pressure in the pressurized oil tank 7 exceeds a designed value, the pressure is automatically opened to release the pressure.
When the pressure in the pressurized oil tank 7 exceeds a design value, the pressure reducing valve 1001 is immediately opened, and the fuel in the pressurized oil tank 7 can be caused to flow back to the line at the inlet of the pressurized oil pump 6.
The oil tank group 1 comprises a front oil tank 101 and a rear oil tank 102, wherein the front oil tank 101 and the rear oil tank 102 are formed by a plurality of groups of vacuum split type soft oil tanks, the plurality of groups of vacuum split type soft oil tanks of the front oil tank 101 are respectively connected with a first pipeline 2, and the plurality of groups of vacuum split type soft oil tanks of the rear oil tank 102 are respectively connected with a second pipeline 3.
Preceding oil tank 101, back oil tank 102 adopt the split type soft oil tank of vacuum, can restrain comprehensively that flight in-process fuel rocks, and it rocks the centrobaric influence of unmanned aerial vehicle flight to restrain the fuel.
The front fuel tank 101 and the rear fuel tank 102 are managed according to the fuel sequence to reduce the change of the center of gravity of the whole engine caused by the fuel consumption.
The oil supply assembly 9 comprises a fourth pipeline 91, an oil filter 92, a flow meter 93, a main oil path electromagnetic valve 94 and an engine main oil pump 95, the pressurizing oil tank 7 is connected with the engine through the oil supply assembly 9, the fourth pipeline 91 is sequentially provided with the flow meter 93, the main oil path electromagnetic valve 94 and the engine main oil pump 95 along the oil supply direction, the oil filter 92 is arranged between the flow meter 93 and the pressurizing oil tank 7 or between the flow meter 93 and the main oil path electromagnetic valve 94, the flow meter 93 is connected with the controller 8, and the main oil path electromagnetic valve 94 and the engine main oil pump 95 are respectively connected with the engine controller.
According to the requirement of the engine on an oil supply system, when the engine does not work, oil cannot be supplied to the engine, when the engine oil supply pump 95 does not work, the engine oil supply pump does not have stopping capacity, and once a large amount of fuel oil flows into the engine which does not work, the engine cannot be started; therefore, a main oil path electromagnetic valve 94 is designed at the tail end of the oil source system, and the oil supply path is opened when the engine is started until the engine is closed after the engine stops working.
The flow meter 93 measures the amount of fuel flowing out, provides the total fuel consumption, and provides a basis for the opening timing of the fuel sequence control valve 12.
As shown in fig. 2, an embodiment of the present invention further provides an oil supply control method for an unmanned aerial vehicle fuel supply system, where the method includes: in the process of front-stage flight of the unmanned aerial vehicle, the ball valve 5 is in a closed state by default, the controller 8 drives the pressurized oil pump 6, the fuel sequence control valve 12 is closed, the front oil tank 101 of the oil tank group 1 supplies oil to the pressurized oil tank 7 through the first pipeline 2, and the fuel in the pressurized oil tank 7 is conveyed to an engine through the oil supply assembly 9;
in the unmanned aerial vehicle back-stage flight process, ball valve 5 defaults to be in the closed condition, controller 8 drives pressurized oil pump 6 opens fuel sequence control valve 12, the fuel feeding is passed through second pipeline 3, pressurized oil pump 6 to pressurized oil tank 7 to the back oil tank 102 of oil tank group 1, the fuel in the pressurized oil tank 7 is carried to the engine through fuel feeding unit 9.
The pressure detector 1002 of the pressure monitoring assembly 10 collects the pressure in the pressurized oil tank 7, and the controller 8 determines whether to increase or decrease the pressure in the pressurized oil tank 7 according to the pressure in the pressurized oil tank 7.
The increase or decrease in the pressure in the pressurized oil tank 7 is achieved by increasing or decreasing the flow rate of the pressurized oil pump 6.
The pressure reducing valve 1001 automatically opens to release pressure once the pressure in the pressurized oil tank 7 exceeds a design value.
The design value of the embodiment of the invention is 45-50Kpa, and other pressure ranges can be designed according to requirements.
Because the center of gravity of the airplane moves forward seriously after the high-speed target takeoff boosting rocket falls off and the center of gravity of the airplane moves forward after the cruise boosting rocket works, the fuel before the center of gravity is used firstly after the airplane takes off, so that the center of gravity of the airplane moves backward, and the adverse effect caused by the boosting rocket is compensated.
The embodiment of the invention also provides a refueling control method of the fuel oil supply system of the unmanned aerial vehicle, which comprises the following steps: bleed at unmanned aerial vehicle and refuel in-process, manually open ball valve 5, fuel sequence control valve 12 is opened to controller 8, and refuel equipment draws air and refuels through oil filler hole 4, second pipeline 3 to the back oil tank 102 of oil tank group 1, through oil filler hole 4, the anterior segment of second pipeline 3 draws air and refuels through fuel sequence control valve 12 and four way connection 11 to the preceding oil tank 101 of first pipeline 2 to oil tank group 1, through oil filler hole 4, ball valve 5 draws air and refuels to pressurization oil tank 7, until all oil tank gas clean and fuel fill up.
The same or similar reference numerals in the drawings of the present embodiment correspond to the same or similar components; in the description of the present invention, it is to be understood that the terms "upper", "lower", "left", "right", "inner", "outer", etc. indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of description and simplicity of description, but do not indicate or imply that the referred devices or elements must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, the terms describing the positional relationships in the drawings are only for illustrative purposes and are not to be construed as limitations of the present patent, and specific meanings of the terms may be understood by those skilled in the art according to specific situations.
It should be noted that, in this document, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, 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, article, or apparatus. Without further limitation, an element defined by the phrase "comprising an … …" does not exclude the presence of other like elements in a process, article, or apparatus that comprises the element.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention.
Claims (10)
1. An unmanned aerial vehicle fuel oil supply system is characterized by comprising an oil tank group, a first pipeline, a second pipeline, an oil filling port, a pressurized oil pump, a pressurized oil tank, a controller and an oil supply assembly;
one part of the oil tank group is connected with the pressurized oil pump through a first pipeline respectively;
the pressurized oil pump is connected with the pressurized oil tank through a third pipeline;
the other part of the oil tank group is connected with the oil filling port through a second pipeline respectively;
the pressurized oil tank is connected with the engine through an oil supply assembly;
a four-way joint is arranged between the pressure oil pump and the first pipeline, and one end of the four-way joint is connected with the second pipeline through a fuel sequence control valve;
the controller is respectively connected with the pressurized oil pump, the oil supply assembly and the fuel oil sequence control valve; the controller is also connected with the flight control computer and used for receiving the pressurization command and sending the oil pressure and flow value.
2. The unmanned aerial vehicle fuel supply system of claim 1, further comprising a ball valve, wherein the second pipeline is further connected with a third pipeline through the ball valve, and is used for ground air suction or oil filling.
3. The unmanned aerial vehicle fuel supply system of claim 2, further comprising a pressure monitoring assembly, wherein the other end of the four-way joint is connected with the pressurized fuel tank through the pressure monitoring assembly.
4. The unmanned aerial vehicle fuel oil supply system of claim 3, wherein the pressure monitoring assembly comprises a pressure reducing valve and a pressure detector, the pressure reducing valve is arranged on a pipeline between one end of the four-way joint and the pressurizing oil tank to form a pressure relief loop, the pressure detector is arranged on the pressure reducing valve or a pipeline between the pressure reducing valve and the pressurizing oil tank or other pipelines directly connected with the pressurizing oil tank, and the controller is connected with the pressure detector.
5. The unmanned aerial vehicle fuel oil supply system of any one of claims 1-4, wherein the fuel tank set comprises a front fuel tank and a rear fuel tank, the front fuel tank and the rear fuel tank are both composed of a plurality of sets of vacuum split type soft fuel tanks, the plurality of sets of vacuum split type soft fuel tanks of the front fuel tank are respectively connected with a first pipeline, and the plurality of sets of vacuum split type soft fuel tanks of the rear fuel tank are respectively connected with a second pipeline.
6. The unmanned aerial vehicle fuel oil feeding system of claim 5, characterized in that, the fuel feeding subassembly includes fourth pipeline, oil filter, flowmeter, total oil way solenoid valve, engine main oil pump, the pressurization oil tank passes through the fuel feeding subassembly and is connected with the engine, the fourth pipeline sets gradually flowmeter, total oil way solenoid valve, engine main oil pump along the fuel feeding direction, the oil filter sets up between flowmeter and pressurization oil tank, or between flowmeter and the total oil way solenoid valve, the flowmeter is connected with the controller, total oil way solenoid valve, engine main oil pump are connected with engine controller respectively.
7. The utility model provides an unmanned aerial vehicle fuel feeding system's fuel feeding control method which characterized in that, the method is: at unmanned aerial vehicle early stage flight in-process, the ball valve defaults to be in the closed condition, the controller drive the fuel sequential control valve is closed to the pressurized oil pump, the preceding oil tank of oil tank group supplies oil in to the pressurized oil tank through first pipeline, fuel in the pressurized oil tank passes through fuel feeding assembly and carries to the engine.
8. The fuel supply control method of the fuel supply system of the unmanned aerial vehicle according to claim 7, further comprising: at unmanned aerial vehicle back-phase flight in-process, the ball valve defaults to be in the closed condition, the controller drive the fuel sequence control valve is opened to the pressurized oil pump, the back oil tank of oil tank group passes through second pipeline, pressurized oil pump fuel feeding in to the pressurized oil tank, the fuel in the pressurized oil tank passes through fuel feeding unit and carries to the engine.
9. The fuel supply control method of the fuel supply system of the unmanned aerial vehicle according to claim 8, wherein the pressure detector of the pressure monitoring assembly collects pressure in the pressurized fuel tank, and the controller determines whether to increase or decrease the pressure in the pressurized fuel tank according to the pressure in the pressurized fuel tank.
10. A refueling control method for an unmanned aerial vehicle fuel supply system is characterized by comprising the following steps: bleed and refuel in-process at unmanned aerial vehicle, the manual ball valve of opening, the fuel sequence control valve is opened to the controller, and fuel filling equipment bleeds and refuels through oil filler hole, second pipeline to the back oil tank of oil tank group, bleeds and refuels through the anterior segment of oil filler hole, second pipeline through fuel sequence control valve and four way connection to the preceding oil tank of first pipeline to the oil tank group, bleeds and refuels through oil filler hole, ball valve to the oil tank that pressurizes, until all oil tank gas clean-outs and fuel fill up.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110112374.2A CN112706931A (en) | 2021-01-27 | 2021-01-27 | Unmanned aerial vehicle fuel supply system and fuel supply and refueling control method |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202110112374.2A CN112706931A (en) | 2021-01-27 | 2021-01-27 | Unmanned aerial vehicle fuel supply system and fuel supply and refueling control method |
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| CN112706931A true CN112706931A (en) | 2021-04-27 |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113335536A (en) * | 2021-08-09 | 2021-09-03 | 尚良仲毅(沈阳)高新科技有限公司 | Unmanned aerial vehicle and oil feeding system thereof |
| CN116119014A (en) * | 2023-03-21 | 2023-05-16 | 北京科荣达航空科技股份有限公司 | Supercharged oil tank oil supply system for airplane |
-
2021
- 2021-01-27 CN CN202110112374.2A patent/CN112706931A/en active Pending
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113335536A (en) * | 2021-08-09 | 2021-09-03 | 尚良仲毅(沈阳)高新科技有限公司 | Unmanned aerial vehicle and oil feeding system thereof |
| CN113335536B (en) * | 2021-08-09 | 2021-11-09 | 尚良仲毅(沈阳)高新科技有限公司 | Unmanned aerial vehicle and oil feeding system thereof |
| CN116119014A (en) * | 2023-03-21 | 2023-05-16 | 北京科荣达航空科技股份有限公司 | Supercharged oil tank oil supply system for airplane |
| CN116119014B (en) * | 2023-03-21 | 2024-02-09 | 北京科荣达航空科技股份有限公司 | Supercharged oil tank oil supply system for airplane |
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