CN112706931B - Unmanned aerial vehicle fuel oil supply system and fuel oil supply and refueling control method - Google Patents
Unmanned aerial vehicle fuel oil supply system and fuel oil supply and refueling control method Download PDFInfo
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- CN112706931B CN112706931B CN202110112374.2A CN202110112374A CN112706931B CN 112706931 B CN112706931 B CN 112706931B CN 202110112374 A CN202110112374 A CN 202110112374A CN 112706931 B CN112706931 B CN 112706931B
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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
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- 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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- Combustion & Propulsion (AREA)
- Aviation & Aerospace Engineering (AREA)
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- Loading And Unloading Of Fuel Tanks Or Ships (AREA)
Abstract
本发明公开了一种无人机燃油供油系统及供油、加油控制方法，该系统中油箱组的一部分分别通过第一管路与加压油泵连接；加压油泵通过第三管路与加压油箱连接；油箱组的另一部分分别通过第二管路与加油口连接；加压油箱通过供油组件与发动机连接；加压油泵与第一管路之间设置四通接头，四通接头的一端经燃油顺序控制阀与第二管路连接；控制器分别与加压油泵、供油组件、燃油顺序控制阀连接；控制器还与飞行控制计算机连接，用于接收加压指令，发送油压和流量值。本发明能够保证在0～20000m高度范围内，1～6g的使用过载情况下，供油系统能够保证具有25kpa～50kpa的相对压力，保证顺畅地向发动机供油。
The present invention discloses a fuel supply system for unmanned aerial vehicles and a fuel supply and refueling control method, in which a part of the fuel tank group is connected to the pressurized oil pump through a first pipeline; the pressurized oil pump is connected to the pressurized oil tank through a third pipeline; the other part of the fuel tank group is connected to the refueling port through a second pipeline; the pressurized oil tank is connected to the engine through a fuel supply assembly; a four-way joint is arranged between the pressurized oil pump and the first pipeline, and one end of the four-way joint is connected to the second pipeline through a fuel sequence control valve; a controller is respectively connected to the pressurized oil pump, the fuel supply assembly, and the fuel sequence control valve; the controller is also connected to a flight control computer for receiving pressurization instructions and sending oil pressure and flow values. The present invention can ensure that within the range of 0 to 20,000 m altitude and under the use overload condition of 1 to 6 g, the fuel supply system can ensure a relative pressure of 25 kpa to 50 kpa, ensuring smooth fuel supply to the engine.
Description
Technical Field
The invention belongs to the technical field of unmanned aerial vehicle fuel oil supply equipment, and particularly relates to an unmanned aerial vehicle fuel oil supply system and an oil supply and refueling control method.
Background
The long-endurance unmanned aerial vehicle is a large-maneuver recyclable unmanned aerial vehicle system, has the advantages of stealth, high speed (high subsonic speed to supersonic speed) and large maneuver (stable 6G and instantaneous 9G), and has the layout characteristics of slender fuselage, large oil carrying capacity, and easy generation of severe gravity center change caused by fuel shaking during taking off and flying, particularly during large maneuver flight, and meanwhile, the flying envelope flying height ranges from 0 to 12000 meters, and is severe along with the pressure change of the height, and the engine oil supply end requires constant pressure oil supply.
The design scheme adopted in the prior art of pressure maintaining and oil supplying is that the engine bleed air is pressurized, therefore, the turbojet engines for unmanned aerial vehicles are all designed with engine bleed air ports, namely, a small amount of high-pressure air flow is led out from the back of an engine compressor, and is input into an oil tank cabin to pressurize the inside or the outside of the oil tank, and the oil tank is a rubber soft oil tank, but the pressure (pressure) of the oil tank is required to be borne by a hard shell bearing structure of an aircraft body, and the turbojet engines have large oil consumption, so that the fuel load on the aircraft is large, generally accounting for 25 to 40 percent of the total weight of the aircraft, and the percentage of the volume of the aircraft body is equivalent. With a pressure of 50Kpa, it is meant that a force of 0.5 kg is applied per square centimeter, and for an aircraft structure with a tank area of 1 square meter, the tension to be sustained is 5000 kg.
At present, a composite material structure is basically adopted from a small unmanned aerial vehicle to a large unmanned aerial vehicle, most of the connection between the airframe structures (whether glass fibers, carbon fibers or other composite materials) is made of glue joint, particularly the connection between the airframe skin and airframe frame and beams of an airplane, the peeling strength of the glue joint structure is very low, the input pressure in an oil tank cabin is very high in breaking force, namely peeling force, and once the structural connection is peeled off, the structural strength of the airplane is rapidly reduced, and the airplane is seriously disassembled. Besides the stripping damage, the pressure can cause the relevant aircraft appearance plate to bulge and deform, the aerodynamic appearance of the aircraft is damaged, the aircraft resistance is increased, the flying performance of the aircraft is reduced, in order to ensure that the aircraft structure can bear the inflation pressure, the load must be considered in the structural design, the structural strength is increased outside the structure required by the original aircraft to bear the aerodynamic load, namely, the thickness of the structural plate is increased, and the adhesive joint surface is increased, so that the weight and the materials of the aircraft structure are greatly increased, and the difficulty and the manufacturing cost of the relevant manufacturing process are increased.
In addition, for pressurization, the engine body structure needs to be sealed, the sealing needs to bear the flying pneumatic load and the inflation pressure of inflation, deformation (bending and torsion) of the engine body under various stress conditions can not cause air leakage of the sealed cabin, oil cannot be supplied to the engine once the air leakage occurs, serious accidents of air parking are caused, secondary sealing is difficult during repair, the requirements on the engine body structure design and manufacturing process are high, and meanwhile, the cost is greatly increased.
Disclosure of Invention
Accordingly, the main object of the present invention is to provide an unmanned aerial vehicle fuel supply system and a fuel supply and fueling control method.
In order to achieve the above purpose, the technical scheme of the invention is realized as follows:
The embodiment of the invention provides an unmanned aerial vehicle fuel oil 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;
One part of the oil tank group is connected with a 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 pressurized 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 pressurizing oil pump, the oil supply assembly and the fuel sequence control valve, and is also connected with the flight control computer, receives the pressurizing instruction and sends the oil pressure and the flow value.
In the scheme, the device further comprises a ball valve, and the second pipeline is connected with a third pipeline through the ball valve and used for ground air suction or oil filling.
In the scheme, the four-way joint further comprises a pressure monitoring assembly, and the other end of the four-way joint is connected with the pressurized oil tank through the pressure monitoring assembly.
In the above scheme, the pressure monitoring assembly comprises a pressure reducing valve and a pressure detector, wherein the pressure reducing valve is arranged on a pipeline between one end of the four-way joint and the pressurized oil tank to form a pressure relief loop, the pressure detector is arranged on the pressure reducing valve, or on a pipeline between the pressure reducing valve and the pressurized oil tank, or on other pipelines directly connected with the pressurized oil tank, and the controller is connected with the pressure detector.
In the above scheme, the oil tank group includes preceding oil tank, back oil tank, preceding oil tank, back oil tank are constituteed by a plurality of vacuum split type flexible tank of group, a plurality of vacuum split type flexible tank of preceding oil tank are connected with first pipeline respectively, a plurality of vacuum split type flexible tank of back oil tank are connected with the second pipeline respectively.
In the above-mentioned scheme, oil feeding unit includes fourth pipeline, oil strain, flowmeter, total oil circuit solenoid valve, engine main oil pump, the pressurized oil tank passes through oil feeding unit and is connected with the engine, fourth pipeline sets gradually flowmeter, total oil circuit solenoid valve, engine main oil pump along the oil feeding direction, oil strain sets up between flowmeter and pressurized oil tank, or between flowmeter and the total oil circuit solenoid valve, the flowmeter is connected with the controller, total oil circuit 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 unmanned aerial vehicle fuel oil supply system, which comprises the steps that in the front-stage flight process of the unmanned aerial vehicle, the ball valve is in a closed state by default, the controller drives the pressurized oil pump to close the fuel sequence control valve, the front oil tank of the oil tank group supplies oil to the pressurized oil tank through a first pipeline, and the fuel in the pressurized oil tank is conveyed to an engine through an oil supply assembly.
In the scheme, the method further comprises the step that in the unmanned aerial vehicle post-stage flying process, the ball valve is in a closed state by default, the controller drives the pressurized oil pump, the fuel sequence control valve is opened, the rear oil tank of the oil tank group supplies oil to the pressurized oil tank through the second pipeline and the pressurized oil pump, and the fuel in the pressurized oil tank is conveyed to the engine through the oil supply assembly.
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 fueling control method of the unmanned aerial vehicle fuel supply system, which comprises the steps of manually opening the ball valve in the air suction and fueling process of the unmanned aerial vehicle, opening the fuel sequence control valve by the controller, performing air suction and fueling on a rear fuel tank of the fuel tank group through the fuel inlet and the second pipeline by fueling equipment, performing air suction and fueling on a front fuel tank of the fuel tank group through the fuel sequence control valve and the four-way connector to the first pipeline through the front section of the fuel inlet and the second pipeline, and performing air suction and fueling on a pressurized fuel tank through the fuel inlet and the ball valve until all fuel tank air is completely pumped and fuel is filled.
Compared with the prior art, the oil supply system can ensure that the oil supply system has the relative pressure of 25-50 kpa (or other pressure ranges) in the height range of 0-20000 m under the condition of overload of 1-6 g, and can ensure smooth oil supply 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 embodiments of the invention and together with the description serve to explain 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 oil supply system according to an embodiment of the present invention.
Detailed Description
The present invention will be described in further detail with reference to the drawings and examples, in order to make the objects, technical solutions and advantages of the present invention more apparent. It should be understood that the specific embodiments described herein are for purposes of illustration only and are not intended to limit the scope of the invention.
The embodiment of the invention provides an unmanned aerial vehicle fuel supply system, as shown in fig. 1, which comprises a fuel tank group 1, a first pipeline 2, a second pipeline 3, a fuel filler 4, a pressurized oil pump 6, a pressurized fuel tank 7, a controller 8 and a fuel supply assembly 9;
a part of the oil tank group 1 is connected with a pressurized oil pump 6 through a first pipeline 2 respectively;
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 connected with an oil filler 4 through a second pipeline 3 respectively;
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 pressurized 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 pressurizing oil pump 6, the oil supply assembly 9 and the fuel sequence control valve 12, and the controller 8 is also connected with the flight control computer, receives the pressurizing instruction and sends the oil pressure and the flow value.
The controller 8 is connected with the pressurized oil pump 6 for adjusting the working state of the pressurized oil pump, the controller 8 is connected with the oil supply assembly 9 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 for collecting the pressure in the pressurized oil tank and controlling the rotating speed of the pressurized oil pump by the pressure, and the controller 8 is connected with the fuel sequence control valve 12 for controlling the opening and closing of the pressurized oil pump.
Further, the pressure monitoring assembly 10 is further included, a four-way joint 11 is arranged between the pressurized oil pump 6 and the first pipeline 2, and one end of the four-way joint 11 is connected with the pressurized oil tank 7 through the pressure monitoring assembly 10.
The pressure monitoring assembly 10 comprises a pressure reducing valve 1001 and a pressure detector 1002, wherein 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 on a pipeline between the pressure reducing valve 1001 and the pressurized oil tank 7, or on 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, and may be mounted on the relief valve 1001, in a line between the relief valve 1001 and the pressurized oil tank 7, in a line between the pressurized oil pump 6 and the pressurized oil tank 7, and in a line between the oil filter 91 and the pressurized oil tank 7.
The relief valve 1001 is a mechanical relief valve, the opening pressure of which can be adjusted as required, and which opens automatically when the pressure in the pressurized tank 7 exceeds the design value.
When the pressure in the pressurized fuel tank 7 exceeds the design value, the relief valve 1001 is immediately turned on, so that the fuel in the pressurized fuel tank 7 can flow back to the line of the inlet of the pressurized fuel 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 composed of 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.
The front oil tank 101 and the rear oil tank 102 adopt vacuum split type flexible oil tanks, so that fuel oil shaking in the flight process can be comprehensively restrained, and the influence of the fuel oil shaking on the flight gravity center of the unmanned aerial vehicle is restrained.
The front tank 101 and the rear tank 102 are managed according to the fuel sequence to reduce the change in the center of gravity of the whole engine due to fuel consumption.
The oil supply assembly 9 comprises a fourth pipeline 91, an oil filter 92, a flowmeter 93, a total oil way electromagnetic valve 94 and an engine main oil pump 95, the pressurized oil tank 7 is connected with the engine through the oil supply assembly 9, the fourth pipeline 91 is sequentially provided with the flowmeter 93, the total oil way electromagnetic valve 94 and the engine main oil pump 95 along the oil supply direction, the oil filter 92 is arranged between the flowmeter 93 and the pressurized oil tank 7 or between the flowmeter 93 and the total oil way electromagnetic valve 94, the flowmeter 93 is connected with the controller 8, and the total oil way 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 the oil supply system, when the engine is not in operation, the oil cannot be supplied to the engine, when the engine oil supply pump 95 is not in operation, once a large amount of fuel flows into the engine which is not in operation, the engine cannot be started, therefore, the oil supply system is provided with the electromagnetic valve 94 of the total oil way at the extreme end, and when the engine is started, the oil supply way is opened until the engine is closed after the engine stops operating.
The flow meter 93 meters the amount of fuel flowing out, provides total fuel consumption, and provides a basis for the opening timing of the fuel sequence control valve 12.
As shown in fig. 2, the embodiment of the invention further provides an oil supply control method of the unmanned aerial vehicle fuel oil supply system, which comprises the steps that in the front-stage flight process 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 to close the fuel sequence control valve 12, 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 the engine through the oil supply component 9;
In the unmanned aerial vehicle later stage flight process, the ball valve 5 defaults to be in a closed state, the controller 8 drives the pressurized oil pump 6, the fuel sequence control valve 12 is opened, the rear oil tank 102 of the oil tank group 1 supplies oil to the pressurized oil tank 7 through the second pipeline 3 and the pressurized oil pump 6, and the fuel in the pressurized oil tank 7 is conveyed to the engine through the oil supply assembly 9.
The pressure detector 1002 of the pressure monitoring assembly 10 collects the pressure in the pressurized fuel tank 7, and the controller 8 determines whether to increase or decrease the pressure in the pressurized fuel tank 7 according to the pressure in the pressurized fuel tank 7.
The increase or decrease of the pressure in the pressurized oil tank 7 is achieved by increasing or decreasing the flow rate of the pressurized oil pump 6.
The relief valve 1001 automatically opens the relief once the pressure in the pressurized tank 7 exceeds the design value.
The design value of the embodiment of the invention is 45-50Kpa, and other pressure ranges can be designed according to the requirement.
The gravity center of the aircraft is seriously moved forward after the high-speed target takeoff booster rocket falls off, and the gravity center of the aircraft is moved forward after the cruise booster rocket works, so that the fuel oil in front of the gravity center is firstly used after the aircraft takes off, and the adverse effect caused by the booster rocket is compensated.
The embodiment of the invention also provides a fueling control method of the unmanned aerial vehicle fuel supply system, which comprises the steps of manually opening the ball valve 5 in the air suction and fueling process of the unmanned aerial vehicle, opening the fuel sequence control valve 12 by the controller 8, performing air suction and fueling on the rear fuel tank 102 of the fuel tank group 1 through the fuel filler port 4 and the second pipeline 3 by fueling equipment, performing air suction and fueling on the front fuel tank 101 of the fuel tank group 1 through the fuel sequence control valve 12 and the four-way joint 11 from the front section of the fuel filler port 4 and the second pipeline 3 to the first pipeline 2 by the fuel sequence control valve 12, and performing air suction and fueling on the pressurized fuel tank 7 through the fuel filler port 4 and the ball valve 5 until all fuel tank gases are completely sucked and filled with fuel.
In the description of the present invention, it should be understood that the terms "upper", "lower", "left", "right", "inner", "outer", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are merely for convenience in describing the present invention and simplifying the description, rather than indicating or implying that the apparatus or elements being referred to must have a specific orientation, be constructed and operated in a specific orientation, so that the terms describing the positional relationships in the drawings are merely for exemplary illustration and are not to be construed as limitations of the present patent, and that the specific meanings of the terms described above may be understood by those of ordinary skill in the art according to specific circumstances.
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 one does not exclude the presence of other like elements in a process, article or apparatus that comprises the element.
The foregoing description is only of the preferred embodiments of the present invention, and is not intended to limit the scope of the present invention.
Claims (9)
1. The 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 a 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 pressurized 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 sequential control valve; the controller is also connected with the flight control computer and used for receiving the pressurizing instruction and sending the oil pressure and the flow value, and the controller is connected with the oil supply assembly and used for collecting the fuel consumption and controlling the opening time of the fuel sequence control valve according to the fuel consumption;
The oil tank group comprises a front oil tank and a rear oil tank, wherein the front oil tank and the rear oil tank are composed of 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 are respectively connected with a first pipeline, and the plurality of groups of vacuum split type soft oil tanks of the rear oil tank are respectively connected with a second pipeline.
2. The unmanned aerial vehicle fuel supply system of claim 1, further comprising a ball valve, wherein the second conduit is further connected to a third conduit via the ball valve for use in ground pumping or refueling.
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 connector is connected to a pressurized fuel tank via the pressure monitoring assembly.
4. A fuel supply system according to claim 3, wherein the pressure monitoring assembly comprises a pressure reducing valve arranged on a line between one end of the four-way connection and the pressurized fuel tank to form a pressure relief circuit, and a pressure detector arranged on the pressure reducing valve, or on a line between the pressure reducing valve and the pressurized fuel tank, or on another line directly connected to the pressurized fuel tank, and the controller is connected to the pressure detector.
5. The unmanned aerial vehicle fuel supply system of claim 4, wherein the fuel supply assembly comprises a fourth pipeline, a fuel filter, a flowmeter, a total fuel line solenoid valve and an engine main oil pump, the pressurized fuel tank is connected with the engine through the fuel supply assembly, the fourth pipeline is sequentially provided with the flowmeter, the total fuel line solenoid valve and the engine main oil pump along the fuel supply direction, the fuel filter is arranged between the flowmeter and the pressurized fuel tank or between the flowmeter and the total fuel line solenoid valve, the flowmeter is connected with the controller, and the total fuel line solenoid valve and the engine main oil pump are respectively connected with the engine controller.
6. The fuel supply control method for the unmanned aerial vehicle fuel supply system according to any one of claims 1 to 5, wherein the ball valve is in a closed state by default during the unmanned aerial vehicle front-stage flight, the controller drives the pressurized oil pump to close the fuel sequence control valve, the front oil tank of the oil tank group supplies fuel to the pressurized oil tank through a first pipeline, and the fuel in the pressurized oil tank is conveyed to the engine through the fuel supply assembly;
the front oil tank consists of a plurality of groups of vacuum split type soft oil tanks.
7. The method of claim 6, wherein the ball valve is in a closed state by default during a post-flight of the unmanned aerial vehicle, the controller drives the pressurized oil pump to open the fuel sequence control valve, the rear oil tank of the oil tank group supplies oil to the pressurized oil tank through a second pipeline and the pressurized oil pump, and the fuel in the pressurized oil tank is delivered to the engine through the oil supply assembly.
8. The fuel supply control method of the unmanned aerial vehicle fuel supply system according to claim 7, wherein the pressure detector of the pressure monitoring unit collects the 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 condition in the pressurized fuel tank.
9. A method for controlling the fuel supply of unmanned aerial vehicle according to any one of claims 1 to 5, wherein during the air suction and fuel supply of unmanned aerial vehicle, the controller opens the fuel sequence control valve, the fueling device pumps and charges the rear fuel tank of the fuel tank group through the fuel inlet and the second pipeline, pumps and charges the front fuel tank of the fuel tank group through the fuel sequence control valve and the four-way connector to the first pipeline through the front section of the fuel inlet and the second pipeline, pumps and charges the pressurized fuel tank through the fuel inlet and the ball valve, and the fuel is fully pumped and charged.
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| CN202110112374.2A CN112706931B (en) | 2021-01-27 | 2021-01-27 | Unmanned aerial vehicle fuel oil supply system and fuel oil supply and refueling control method |
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| 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 |
| 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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| CN111137462A (en) * | 2019-12-30 | 2020-05-12 | 航天时代飞鸿技术有限公司 | A large cargo unmanned aerial vehicle fuel system and its control method |
| CN214190133U (en) * | 2021-01-27 | 2021-09-14 | 西安九天航空科技有限公司 | Unmanned aerial vehicle fuel oil feeding system |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7458543B2 (en) * | 2005-06-10 | 2008-12-02 | The Boeing Company | Aerial refueling system |
| CN105438484A (en) * | 2015-11-30 | 2016-03-30 | 中航飞机股份有限公司西安飞机分公司 | Aircraft fuel system |
| CN109625297A (en) * | 2018-12-11 | 2019-04-16 | 石家庄飞机工业有限责任公司 | A kind of fuel system for Small General Aircraft |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111137462A (en) * | 2019-12-30 | 2020-05-12 | 航天时代飞鸿技术有限公司 | A large cargo unmanned aerial vehicle fuel system and its control method |
| CN214190133U (en) * | 2021-01-27 | 2021-09-14 | 西安九天航空科技有限公司 | Unmanned aerial vehicle fuel oil feeding system |
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