CN106081132B - Fuel power multi-rotor unmanned aerial vehicle fuel feeding scheme - Google Patents
Fuel power multi-rotor unmanned aerial vehicle fuel feeding scheme Download PDFInfo
- Publication number
- CN106081132B CN106081132B CN201610594834.9A CN201610594834A CN106081132B CN 106081132 B CN106081132 B CN 106081132B CN 201610594834 A CN201610594834 A CN 201610594834A CN 106081132 B CN106081132 B CN 106081132B
- Authority
- CN
- China
- Prior art keywords
- oil
- fuel
- fuel tank
- point
- pressure regulator
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
- 239000000446 fuel Substances 0.000 title claims abstract description 76
- 239000002828 fuel tank Substances 0.000 claims abstract description 55
- 210000002268 wool Anatomy 0.000 claims abstract description 23
- 238000005192 partition Methods 0.000 claims abstract description 5
- 239000003921 oil Substances 0.000 abstract description 147
- 235000003642 hunger Nutrition 0.000 abstract description 5
- 230000037351 starvation Effects 0.000 abstract description 5
- 239000010705 motor oil Substances 0.000 abstract description 3
- 239000000295 fuel oil Substances 0.000 description 9
- 238000012423 maintenance Methods 0.000 description 5
- 238000010586 diagram Methods 0.000 description 4
- 238000000034 method Methods 0.000 description 4
- 238000005086 pumping Methods 0.000 description 4
- 238000002485 combustion reaction Methods 0.000 description 3
- 238000001914 filtration Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 239000003292 glue Substances 0.000 description 1
- 239000010721 machine oil Substances 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000011435 rock Substances 0.000 description 1
Classifications
-
- 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
- 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
- B64D37/02—Tanks
- B64D37/06—Constructional adaptations thereof
- B64D37/08—Internal partitioning
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02M—SUPPLYING COMBUSTION ENGINES IN GENERAL WITH COMBUSTIBLE MIXTURES OR CONSTITUENTS THEREOF
- F02M61/00—Fuel-injectors not provided for in groups F02M39/00 - F02M57/00 or F02M67/00
- F02M61/16—Details not provided for in, or of interest apart from, the apparatus of groups F02M61/02 - F02M61/14
- F02M61/18—Injection nozzles, e.g. having valve seats; Details of valve member seated ends, not otherwise provided for
- F02M61/1806—Injection nozzles, e.g. having valve seats; Details of valve member seated ends, not otherwise provided for characterised by the arrangement of discharge orifices, e.g. orientation or size
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Cooling, Air Intake And Gas Exhaust, And Fuel Tank Arrangements In Propulsion Units (AREA)
Abstract
Fuel power multi-rotor unmanned aerial vehicle fuel feeding scheme constitutes entire oil supply system using All-in-One fuel tank, oil pump, oily filter, fuel pressure regulator, one point of heavy wool mouth and hold-down support, and the central idea of scheme is All-in-One, more than one point and Combination Design.Fuel tank is designed using All-in-One, i.e., setting does not contact up and down with the upper and lower surface of fuel tank inside fuel tank and height is less than multiple partitions of fuel tank height, and whole fuel tank is divided into multiple not only mutually indepedent but also interconnected small fuel tank.Oil nozzle is used and is designed one point more, i.e., an oil inlet branches out multiple oil outlets.Fuel pressure regulator and one point of heavy wool mouth are combined into one, and do not need specific placement.The present invention solves the problems, such as to be easy to appear certain engine oil starvation when the inclination of fuel power multi-rotor unmanned aerial vehicle, the problem of the problem of every engine of fuel power multi-rotor unmanned aerial vehicle needs to configure a set of oil supply system, the problem of being easy to appear bubble in oil supply system and fuel pressure regulator need individually arrangement.
Description
Technical field
The invention belongs to air vehicle technique fields, more particularly to fuel power multi-rotor unmanned aerial vehicle fuel feeding scheme.
Background technique
Currently, the more rotors of fuel power are not also common, the existing more rotors of fuel power mostly use an engine configuration
The scheme of a set of oil supply system, the disadvantage is that at high cost, weight is big and maintenance is difficult；The fuel tank of some more rotors of fuel power is letter
Single die sinking production is easy to appear inclination when body is motor-driven and causes certain to start without the measure of anti-rock and anti-effluent
The parking of machine oil starvation, and independent plug-in can reduce space utilization rate；Some more rotors of fuel power are not provided with fuel pressure adjusting
Device, the too low then fuel injector not oil spout of oil pressure or oil spout are weak, and oil pressure is excessively high, damages oil circuit or fuel injector；Some fuel powers revolve more
Wing oil circuit arrangement is unreasonable, the modes such as commonly use bundle, ties up, glue to fix, and oil pipe arrangement is also especially in disorder, easy to crimp and generation gas
Bubble.
Summary of the invention
The purpose of the present invention is provide one aiming at the problem that above-described fuel power more rotor oil supply systems and deficiency
Kind is easy to appear certain engine oil starvation parking when being avoided that the inclination of fuel power multi-rotor unmanned aerial vehicle, every engine needs are matched
It sets a set of oil supply system, be easy to appear bubble in oil supply system and the problem of fuel pressure regulator needs individually arrangement.
The technical solution adopted by the present invention is that: a kind of fuel power multi-rotor unmanned aerial vehicle fuel feeding scheme, using All-in-One oil
Case, oil pump, oily filter, fuel pressure regulator, one point of heavy wool mouth and hold-down support constitute entire oil supply system, the middle thought of scheme
Think it is All-in-One, more than one point and Combination Design.
The All-in-One fuel tank is connected by oil pick-up tube with oil pump, and oil pump is connected with oily filter, and oily filter passes through fuel oil pressure
Draught control mechanism is connected with one point of heavy wool mouth, and one point of heavy wool mouth is connected with each engine, and the fuel pressure regulator passes through
Oil return pipe is connected with All-in-One fuel tank；The oil pump, oily filter and one point of heavy wool mouth are screwed on hold-down support；The hold-down support
It is screwed on fuselage；The fuel pressure regulator is screwed onto the fuel pressure regulator support being made of one with one point of heavy wool mouth
On, all components outside oil removal box form a sub-assembly, improve space utilization rate.
The All-in-One fuel tank is designed using All-in-One, i.e., setting does not connect up and down with the upper and lower surface of fuel tank inside fuel tank
Touching and height are less than multiple partitions of fuel tank height, and whole fuel tank is divided into multiple not only mutually indepedent but also interconnected point oil
Case can prevent from shaking, and increase flight safety, but when being avoided that inclination part oil starvation and cause to stop.
One point of heavy wool mouth is used and is designed one point more, i.e., an oil inlet branches out multiple oil outlets, and described is fuel-displaced
Mouth quantity is equal to rotor quantity, guarantees only occur an oily filter, an oil pump and a fuel pressure regulator in oil supply system,
It can reduce weight, reduce cost, improve reliability and reduce maintenance difficulty.
Weight in the All-in-One fuel tank is placed in the lowest part of fuel tank, and the oil pump, oily filter, fuel pressure are adjusted
Device, one point of heavy wool mouth oil outlet be all slightly above the oil inlet of All-in-One fuel tank.
Fuel pressure regulator is set in oil circuit to adjust oil circuit pressure, is combined into one, is not required to one point of heavy wool mouth
Specific placement is wanted, rapid-maintenance and replacement are conducive to.
Working method of the invention are as follows: fly control oil-feed pump and power and send instruction, oil pump starts to pump outward from fuel tank, combustion
Oil first passes around oil pump pressurization, flows into oily filter after oil pump outflow, flows into fuel pressure regulator after filtering, if oil pressure is super
Preset threshold is crossed, then the pressure ball valve of fuel pressure regulator is opened, and extra fuel oil flows back to fuel tank by oil return pipe, works as pressure
When being reduced to preset threshold, pressure ball valve is closed, and stops oil return, and fuel oil is flowed out from fuel pressure regulator, flows into one point of heavy wool
Mouth, only fuel oil flow to each engine full of can just flow out from multiple oil outlets after the hermetic type chamber of one point of heavy wool mouth.
Compared with the oil supply system of the more rotors of existing fuel power, the beneficial effects of the present invention are:
(1) one point of heavy wool mouth is used, it is no longer necessary to which every engine all configures a set of oil supply system, mitigates weight, reduces
Cost, increased reliability reduce maintenance workload；
(2) fuel tank is divided into the multiple small spaces for being not only relatively isolated but also being interconnected, and can mitigate shaking, increases flight
Stability, and it is avoided that when fuselage tilts that being likely to occur fuel distribution unevenness leads to certain engine oil starvation parking；
(3) setting fuel pressure regulator guarantees oil circuit safety, and fuel pressure regulator is combined with one point of heavy wool mouth
Integrally, it does not need additionally to arrange, space utilization rate is high
(4) all components outside oil removal box form a sub-assembly, and Combination Design is reasonable to be replaced in rapid-maintenance；
(5) oil outlet of oil pump, oily filter, fuel pressure regulator, one point of heavy wool mouth described in is all slightly above oil inlet, keeps away
Exempt from oil circuit and bubble occurs.
Detailed description of the invention
Fig. 1 is a kind of schematic diagram of the more rotor fuel feeding schemes of fuel power；
Fig. 2 is the structural schematic diagram of the dynamic six rotor oil supply systems of oil；
Fig. 3 is the structural schematic diagram of one fuel tank of the six directions；
Fig. 4 is the cross-sectional view of one fuel tank of the six directions；
Fig. 5 is the sub-assembly of fuel pressure regulator and one point of six oil nozzle；
Fig. 6 is the upper oil nozzle of one point of six oil nozzle；
Fig. 7 is the lower oil nozzle of one point of six oil nozzle；
Fig. 8 is the structural schematic diagram of the dynamic quadrotor oil supply system of oil；
Wherein: 1: one fuel tank of the six directions, 11: pouring orifice, 12: oil pumping mouth, 13: oil return opening, 14: partition, 15: groove, 16: oil
Gage, 17: column slot, 18: divide fuel tank, 2: oil pump, 3: oily filter, 4: fuel pressure regulator, 5: one point of six oil nozzle, 51: upper oil nozzle,
511: oil outlet, 512: oil outlet boss, 513: seal groove, 514: upper die joint, 515: screw hole, 516: type chamber, 52: lower oil
Mouth, 521: oil inlet, 522: lower die joint, 523: fuel pressure regulator support, 6: hold-down support, 7: oil pick-up tube, 8: oil return
Pipe.
Specific embodiment
Technical solution of the present invention is described in detail below by attached drawing, but protection scope of the present invention is not limited to
In the embodiment.
Example one:
As illustrated in fig. 1 and 2, the dynamic six rotor fuel feeding schemes of oil are adjusted by one fuel tank 1 of the six directions, oil pump 2, oily filter 3, fuel pressure
4, one point of six oil nozzle 5 of device, hold-down support 6, oil pick-up tube 7 and oil return pipe 8 form.
One fuel tank 1 of the six directions is connected by oil pick-up tube with oil pump 2, and oil pump 2 is connected with oily filter 3, and oily filter 3 passes through combustion
Oil pressure draught control mechanism 4 is connected with one point of six oil nozzle 5, and one point of six oil nozzle 5 is connected with each engine, and the fuel pressure is adjusted
Device 4 is connected by oil return pipe with one fuel tank 1 of the six directions；The oil pump 2, oily filter 3 and one point of six oil nozzle 5 are screwed on hold-down support 6；
The hold-down support 6 is screwed on fuselage；The fuel pressure regulator 4 is screwed onto the combustion being made of one with one point of six oil nozzle 5
On oil pressure draught control mechanism support 523, all components in addition to one fuel tank 1 of the six directions form a sub-assembly, improve space utilization
Rate.
One fuel tank 1 of the six directions is designed using the six directions one, i.e., setting does not contact up and down with the upper and lower surface of fuel tank inside fuel tank
And height is less than 6 partitions 14 of fuel tank height, and whole fuel tank is divided into and multiple not only mutually indepedent but also interconnected divides fuel tank
18, as shown in Figure 4.
As shown in figure 3, offering 11, oil pumping mouths 12 of a pouring orifice and an oil return opening 13 on one fuel tank 1 of the six directions.
A groove 15 is arranged in the position opposite with oil pumping mouth 12 and oil return opening 13, it is therefore an objective to guarantee unmanned plane in fuel tank oil
Oil mass in groove 15 is only relied on when measuring lower also can normally make a return voyage, and increase the safety of flight.
One fuel tank of the six directions, 1 side is provided with oil mass ruler 16, can be convenient oil mass in observation fuel tank.Among one fuel tank 1 of the six directions
It is provided with column slot 17, column slot 17 and girder (see described in patent 201610370474.4) are clearance fit, and one fuel tank 1 of the six directions is through
It is fixed on girder, improves space utilization rate.
Fuel pressure regulator 4 is set in oil circuit to adjust oil circuit pressure, is combined into one with one point of six oil nozzle 5, no
Specific placement is needed, the oil outlet of fuel pressure regulator 4 is the oil inlet of one point of six oil nozzle 5.
One point of six oil nozzle 5 branches out six oil outlets using one point of six design, i.e. an oil inlet, guarantees in oil supply system
Only there is an oily filter, an oil pump and a fuel pressure regulator；The quantity of oil outlet is equal to the quantity of rotor.
One point of six oil nozzle 5 includes upper oil nozzle 51 and lower oil nozzle 52, as shown in fig. 6, having oil outlet 511 on upper oil nozzle 51, going out
Hydraulic fluid port boss 512, seal groove 513, upper die joint 514, screw hole 515 and type chamber 516；As shown in fig. 7, having oil inlet on lower oil nozzle 52
Mouth 521, lower die joint 522 and fuel pressure regulator support 523.
Oil outlet boss 512 is the button number in order to increase screw thread, improves connection reliability.
Seal groove 513 is used to place O-ring seal, and depth is slightly less than the diameter of O-ring, and width is slightly larger than O-ring
Diameter, sufficient deformation space is reserved to O-ring.Upper die joint 521 and lower die joint 522 interference fit, to form centre
Closed type chamber 516.
Fuel oil is flowed into from the oil inlet on lower oil nozzle 52, and only fuel oil is full of after the hermetic type chamber of one point of six oil nozzle 5
It can be flowed out from six oil outlets 511, flow to each engine.
Weight in one fuel tank 1 of the six directions is placed in the lowest part of fuel tank, oil pump 2, oily filter 3,4, one points of fuel pressure regulator
The oil outlet of heavy wool mouth 5 is all slightly above oil inlet, avoids occurring excessive bubble in oil circuit.
Fuel pressure regulator 4 is screwed on the fuel pressure regulator support 523 being made of one with one point of six oil nozzle 5,
2, one point of six oily filter 3, oil pump oil nozzle 5 are screwed on hold-down support, and hold-down support is screwed onto fuselage (see patent
Described in 201610370474.4) on, all components outside oil removal box form a sub-assembly.
The working method of the present embodiment are as follows: fly control oil-feed pump 2 and power and send instruction, oil pump 2 starts from one fuel tank 1 of the six directions
Oil pumping outward, fuel oil first pass around the pressurization of oil pump 2, flow into oily filter 3 after the outflow of oil pump 2, flow into fuel pressure tune after filtering
Device 4 is saved, if oil pressure is more than preset threshold, the pressure ball valve of fuel pressure regulator 4 is opened, and extra fuel oil passes through oil return
Pipe flows back to one fuel tank 1 of the six directions, and when pressure reduction is to preset threshold, pressure ball valve is closed, and stops oil return, and fuel oil is from fuel pressure
Adjuster 4 flows out, and flows into one point of six oil nozzle 5.
Example two:
It is illustrated in figure 8 the dynamic quadrotor fuel feeding scheme of oil, in addition to using one point of four oil nozzle, described in other structures and example one
It is identical.One point of four oil nozzle branches out four oil outlets using one point of four design, i.e. an oil inlet, guarantees in oil supply system
Only there is an oily filter, an oil pump and a fuel pressure regulator；The quantity of oil outlet is equal to the quantity of rotor.
Above example is merely illustrative of the invention's technical idea, and this does not limit the scope of protection of the present invention, all to press
According to technical idea proposed by the present invention, any changes made on the basis of the technical scheme, each fall within the scope of the present invention it
It is interior.
Claims (4)
1. fuel power multi-rotor unmanned aerial vehicle fuel feeding scheme, which is characterized in that its form include All-in-One fuel tank, an oil pump,
One oily filter, a fuel pressure regulator, one point of heavy wool mouth and hold-down support；The All-in-One fuel tank passes through oil pick-up tube and oil
Pump is connected, and oil pump is connected with oily filter, and oily filter is connected by fuel pressure regulator with one point of heavy wool mouth, one point of heavy wool mouth
It is connected with each engine, the fuel pressure regulator is connected by oil return pipe with All-in-One fuel tank；The oil pump, oily filter and
One point of heavy wool mouth is screwed on hold-down support；The hold-down support is screwed on fuselage；The fuel pressure regulator is screwed onto
On the fuel pressure regulator support being made of one with one point of heavy wool mouth.
2. fuel power multi-rotor unmanned aerial vehicle fuel feeding scheme according to claim 1, which is characterized in that the All-in-One oil
Case is designed using All-in-One, i.e., setting does not contact up and down with the upper and lower surface of fuel tank inside fuel tank and height is less than fuel tank height
Multiple partitions, whole fuel tank is divided into and multiple not only mutually indepedent but also interconnected divides fuel tank.
3. fuel power multi-rotor unmanned aerial vehicle fuel feeding scheme according to claim 1, which is characterized in that one point of heavy wool
Mouth is used and is designed one point more, i.e. an oil inlet branches out multiple oil outlets, and the oil outlet quantity is equal to rotor quantity.
4. fuel power multi-rotor unmanned aerial vehicle fuel feeding scheme according to claim 1, which is characterized in that the All-in-One oil
Weight in case is placed in the lowest part of fuel tank, the oil pump, oily filter, fuel pressure regulator, one point of heavy wool mouth oil outlet
All it is slightly above the oil inlet of All-in-One fuel tank.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610594834.9A CN106081132B (en) | 2016-07-27 | 2016-07-27 | Fuel power multi-rotor unmanned aerial vehicle fuel feeding scheme |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610594834.9A CN106081132B (en) | 2016-07-27 | 2016-07-27 | Fuel power multi-rotor unmanned aerial vehicle fuel feeding scheme |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106081132A CN106081132A (en) | 2016-11-09 |
| CN106081132B true CN106081132B (en) | 2019-06-11 |
Family
ID=57450321
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610594834.9A Expired - Fee Related CN106081132B (en) | 2016-07-27 | 2016-07-27 | Fuel power multi-rotor unmanned aerial vehicle fuel feeding scheme |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106081132B (en) |
Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107150811A (en) * | 2017-04-19 | 2017-09-12 | 中国航空工业集团公司西安飞机设计研究所 | A kind of aircraft oil pumping system |
| CN108252809B (en) * | 2017-12-27 | 2020-07-24 | 深圳常锋信息技术有限公司 | Power control system and aircraft |
| CN108438240A (en) * | 2018-03-23 | 2018-08-24 | 中科灵动航空科技成都有限公司 | A kind of rotor wing unmanned aerial vehicle fuel tank |
| CN109677626A (en) * | 2018-12-29 | 2019-04-26 | 一飞智控(天津)科技有限公司 | Unmanned plane fueller and unmanned plane |
| CN112949076B (en) * | 2021-03-15 | 2021-11-26 | 湖北大学 | Optimal oil supply strategy calculation method for multi-oil-tank aircraft |
| 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 |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8876055B2 (en) * | 2006-03-28 | 2014-11-04 | Airbus Operations Limited | Aircraft refuelling system |
| CN104986328A (en) * | 2015-06-24 | 2015-10-21 | 辽宁锐翔通用航空有限公司 | Variable-propeller-pitch multi-rotor aircraft driven by multiple oil engines |
| CN205260185U (en) * | 2015-11-17 | 2016-05-25 | 石家庄益科创新科技有限公司 | Model aeroplane and model ship and for unmanned aerial vehicle engine electric control oil supply unit |
| CN105644793A (en) * | 2016-02-26 | 2016-06-08 | 辽宁壮龙无人机科技有限公司 | Fuel drive multi-rotor fuel side flow preventing six-in-one fuel tank |
| CN205293073U (en) * | 2015-10-30 | 2016-06-08 | 深圳常锋信息技术有限公司 | Oil moves and directly drives many rotor crafts |
| CN205837214U (en) * | 2016-07-27 | 2016-12-28 | 辽宁壮龙无人机科技有限公司 | A kind of fuel power many rotor wing unmanned aerial vehicles fuel feeding scheme |
-
2016
- 2016-07-27 CN CN201610594834.9A patent/CN106081132B/en not_active Expired - Fee Related
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8876055B2 (en) * | 2006-03-28 | 2014-11-04 | Airbus Operations Limited | Aircraft refuelling system |
| CN104986328A (en) * | 2015-06-24 | 2015-10-21 | 辽宁锐翔通用航空有限公司 | Variable-propeller-pitch multi-rotor aircraft driven by multiple oil engines |
| CN205293073U (en) * | 2015-10-30 | 2016-06-08 | 深圳常锋信息技术有限公司 | Oil moves and directly drives many rotor crafts |
| CN205260185U (en) * | 2015-11-17 | 2016-05-25 | 石家庄益科创新科技有限公司 | Model aeroplane and model ship and for unmanned aerial vehicle engine electric control oil supply unit |
| CN105644793A (en) * | 2016-02-26 | 2016-06-08 | 辽宁壮龙无人机科技有限公司 | Fuel drive multi-rotor fuel side flow preventing six-in-one fuel tank |
| CN205837214U (en) * | 2016-07-27 | 2016-12-28 | 辽宁壮龙无人机科技有限公司 | A kind of fuel power many rotor wing unmanned aerial vehicles fuel feeding scheme |
Non-Patent Citations (1)
| Title |
|---|
| 发动机多喷嘴流量试验器的研究;郭凤仪，高洪鑫，王喜利，蒲凡;《辽宁工程技术大学学报（自然科学版）》;20160531;第35卷(第5期);正文第538-542页 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106081132A (en) | 2016-11-09 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106081132B (en) | Fuel power multi-rotor unmanned aerial vehicle fuel feeding scheme | |
| US10654581B2 (en) | Aircraft fuel system | |
| CN103487101B (en) | The system that a kind of testing laboratory diesel consumption is measured and controlled | |
| CN205837214U (en) | A kind of fuel power many rotor wing unmanned aerial vehicles fuel feeding scheme | |
| CA2754183A1 (en) | Module for managing mass flow and dampening pressure pulsations in a gaseous fuel supply line | |
| CN108150291B (en) | A kind of Altitude Long Endurance Unmanned Air Vehicle engine lubrication fuel tank | |
| CN109677626A (en) | Unmanned plane fueller and unmanned plane | |
| CN105749632A (en) | Negative pressure adjustable jet-type oil-mist separator | |
| CN107701445B (en) | A kind of helical-lobe compressor | |
| CN205277946U (en) | Hydraulic pressure station of valve | |
| CN203730188U (en) | Fuel supply device of engine | |
| CN208918704U (en) | Gravity switch unit and aero-engine inverted flight fuel feeding air-breather containing the unit | |
| CN104343601A (en) | Filter head for an exchange or housing filter | |
| CN203614484U (en) | Overflow valve | |
| CN106593968A (en) | Hydraulic pump load control system for one-engine double-pump aero-engine ground test | |
| CN207712317U (en) | A kind of hydraulic car that power source is provided for plane hydraulic system pressure supply | |
| CN203431379U (en) | Multifunctional gas-liquid swivel joint | |
| CN203431260U (en) | Angle type differential pressure valve | |
| CN214836759U (en) | Gasoline engine carburetor suitable for different altitudes and gasoline engine | |
| CN105179344B (en) | Flow divider valve | |
| CN210191836U (en) | Unmanned aerial vehicle oil supply unit and unmanned aerial vehicle | |
| CN202302164U (en) | Piston type air pressure regulating and reducing valve | |
| CN205908399U (en) | Parallelly connected fuel feed system of two oil tanks | |
| CN206092236U (en) | Avoid pressure fuel pump reflowing vortex on high side to fall device of making an uproar | |
| CN204241228U (en) | For the exhaust regulator of engine test stand cooling system |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| CB03 | Change of inventor or designer information |
Inventor after: Jiang Wenhui Inventor after: Guo Xiangqun Inventor after: Zhang He Inventor after: Zhang Yongwei Inventor after: Gan Zidong Inventor before: Jiang Wenhui Inventor before: Chen Hao Inventor before: Guo Xiangqun Inventor before: Zhang He Inventor before: Zhang Yongwei Inventor before: Lv Hui Inventor before: Gan Zidong Inventor before: Zhang Kuiwen Inventor before: Wang Ziqi |
|
| COR | Change of bibliographic data | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20190611 |