CN209258408U - A kind of UAV Fuel system - Google Patents
A kind of UAV Fuel system Download PDFInfo
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- CN209258408U CN209258408U CN201822177530.XU CN201822177530U CN209258408U CN 209258408 U CN209258408 U CN 209258408U CN 201822177530 U CN201822177530 U CN 201822177530U CN 209258408 U CN209258408 U CN 209258408U
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- fuel tank
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- oil
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- 239000000446 fuel Substances 0.000 title claims abstract description 50
- 239000002828 fuel tank Substances 0.000 claims abstract description 114
- 239000003921 oil Substances 0.000 claims abstract description 53
- 239000000295 fuel oil Substances 0.000 claims abstract description 24
- 238000000605 extraction Methods 0.000 claims description 4
- 238000002485 combustion reaction Methods 0.000 claims description 3
- 239000000945 filler Substances 0.000 claims description 3
- 230000005484 gravity Effects 0.000 abstract description 11
- 229920000049 Carbon (fiber) Polymers 0.000 description 11
- 239000004917 carbon fiber Substances 0.000 description 11
- 238000010586 diagram Methods 0.000 description 11
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 10
- 238000010276 construction Methods 0.000 description 8
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical group [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 6
- 229910052799 carbon Inorganic materials 0.000 description 5
- 230000000694 effects Effects 0.000 description 4
- 239000000835 fiber Substances 0.000 description 3
- 230000006872 improvement Effects 0.000 description 3
- 238000009434 installation Methods 0.000 description 3
- 230000007246 mechanism Effects 0.000 description 3
- 239000002131 composite material Substances 0.000 description 2
- 238000001816 cooling Methods 0.000 description 2
- 238000000354 decomposition reaction Methods 0.000 description 2
- 230000007547 defect Effects 0.000 description 2
- 238000005183 dynamical system Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000002787 reinforcement Effects 0.000 description 2
- 208000016261 weight loss Diseases 0.000 description 2
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- 101100495256 Caenorhabditis elegans mat-3 gene Proteins 0.000 description 1
- 230000008901 benefit Effects 0.000 description 1
- 230000002146 bilateral effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 230000000593 degrading effect Effects 0.000 description 1
- 235000013399 edible fruits Nutrition 0.000 description 1
- 230000008030 elimination Effects 0.000 description 1
- 238000003379 elimination reaction Methods 0.000 description 1
- 230000002708 enhancing effect Effects 0.000 description 1
- 230000006870 function Effects 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 208000020442 loss of weight Diseases 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 230000000116 mitigating effect Effects 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000008447 perception Effects 0.000 description 1
- 230000005622 photoelectricity Effects 0.000 description 1
- 238000004781 supercooling Methods 0.000 description 1
- 239000013589 supplement Substances 0.000 description 1
- 230000001502 supplementing effect Effects 0.000 description 1
- 239000002699 waste material Substances 0.000 description 1
Landscapes
- Cooling, Air Intake And Gas Exhaust, And Fuel Tank Arrangements In Propulsion Units (AREA)
Abstract
A kind of UAV Fuel system, including the first fuel tank and the second fuel tank arranged before and after the axis of symmetry along longitudinal direction, first fuel tank and the second fuel tank structure having the same all have the transversal cross-section of the shape of a saddle；Fuel balance pipeline is provided between first fuel tank and the second fuel tank；First fuel tank is provided with the oil returning tube of connection engine；The bottom of first fuel tank is provided with the oil supply pipe of connection engine.The application gets up to two fuel tanks by equalizing main connection, and the expending equilibrium of the fuel oil of two fuel tanks only needs to control balance oil pump, is conducive to be balanced control using center of gravity of the fuel oil to unmanned plane.
Description
Technical field
The utility model relates to air vehicle technique field more particularly to a kind of UAV Fuel systems.
Background technique
Existing unmanned plane generallys use motor or fuel engines driving.Electronic unmanned plane structure is simply easily fabricated,
But voyage is shorter, load level is lower, can not be applied to military big load scout-attack field.205998123 U of CN is public
A kind of vertical layout fuel power quadrotor flying platform is opened, composition includes that rack, dynamical system, navigation and control are
System, electrical system and task platform.Four identical horns, which are docked at two-by-two on the monocogue for be connected with undercarriage, to be formed
Rack；The end of each horn is arranged in dynamical system, provides power and energy for flying platform；Navigation and control system perception
With posture, height and the position of control flying platform；Electrical system has the function of charging, power supply and instruction；Task platform is used for
Different task devices is installed.
For the defect for solving the above-mentioned prior art, present applicant is in the Chinese patent application applied before
In 201711089304.X, a kind of load configuration structure of dynamic unmanned plane of oil, including a pair of main bearing frame, main bearing frame are disclosed
Front and back be each provided with first bearing frame and the second bearing frame, a head bearing frame is arranged in the front of the first bearing frame,
A tail bearing frame, described two main bearing frames, the first bearing frame, the second bearing frame, machine is arranged in the rear of second bearing frame
Head bearing frame and tail bearing frame are connected as one by four main support rods.The above-mentioned load configuration structure of the prior art
It is surrounded by longitudinal main support rod that multiple bearing frames and four are parallel to the axis of symmetry and forms a supporting and space, Ke Yi
It is provided with drive mechanism, provides protection to the various moving components to drive mechanism, and will be various by the supporting and space
Load is separated with drive mechanism, allows load is more flexible to configure.
The prior art effectively overcomes the defect of the prior art, but still has room for improvement.Especially this is existing
There is the fuel tank center of gravity of technology excessively high, and fuel oil shakes in fuel tank with the maneuvering flight of unmanned plane leads to the appearance of unmanned plane
State control is complicated, and elimination fuel oil influence bring fuel tank weight, which becomes larger, is degrading complete machine load, it is therefore desirable to further change
Into.
Utility model content
The technical problem to be solved by the present invention is to provide a kind of UAV Fuel systems, front institute is reduced or avoided
The problem of mentioning.
In order to solve the above technical problems, the utility model proposes a kind of UAV Fuel system, the dynamic unmanned plane of oil
Including fuselage, undercarriage and the engine for being mounted on the oily fuselage interior for moving unmanned plane, there is the fuselage one to be indulged
To the axis of symmetry, the head and tail of the dynamic unmanned plane of oil are each provided with two and are symmetrical with the longitudinal asymmetric axis arrangement
Cantilever, each cantilever are supported by a rotor, in which: the fuel system includes before and after the longitudinal asymmetric axis
The first fuel tank and the second fuel tank of arrangement, first fuel tank and the second fuel tank structure having the same, all have
The transversal cross-section of the shape of a saddle；Fuel balance pipeline is provided between first fuel tank and the second fuel tank；First combustion
Fuel tank is provided with the oil returning tube of connection engine；The bottom of first fuel tank is provided with the fuel feed pump of connection engine
Road；The unmanned plane includes the fuselage support of a full symmetrical configuration；First fuel tank and the second fuel tank are set to institute
In the fuel tank braced frame for stating the top of the undercarriage carrying floor of fuselage support；The fuel tank braced frame has described in support
The crosspiece at the middle part of the shape of a saddle of the first fuel tank and the second fuel tank.
Preferably, it is provided with the fuel oil extraction conveying described the in second fuel tank in the fuel balance pipeline
The balance oil pump of one fuel tank.
Preferably, the oil returning tube is arranged in the fuel balance pipeline side by side.
Preferably, oil feed pump is provided in the oil supply pipe.
Preferably, two side bottoms of the shape of a saddle of first fuel tank and the oil supply pipe are interconnected.
Preferably, first fuel tank and the second fuel tank are respectively arranged with independent oil filler and independent logical
Port.
The UAV Fuel system of the application is got up two fuel tanks by equalizing main connection, from the first fuel tank
Fuel feeding and oil return operation are carried out, the second fuel tank is by balancing oil pump to the first fuel tank fuel feeding, so as to remain two
The oil mass substantial equilibrium of a fuel tank.The expending equilibrium of the fuel oil of two fuel tanks only needs to control balance oil pump, favorably
In being balanced control using center of gravity of the fuel oil to unmanned plane.
Detailed description of the invention
Following drawings are only intended to schematically illustrate and explain the present invention, does not limit the model of the utility model
It encloses.Wherein,
The structural schematic diagram of the unmanned plane of a specific embodiment according to the application is shown in Fig. 1；
Structural schematic diagram after the part-structure removal of unmanned plane shown in Fig. 1 that Fig. 2 is shown；
The fuselage interior structural schematic diagram according to the unmanned plane of the application is shown in Fig. 3；
The housing construction schematic diagram of unmanned plane is shown in Fig. 4；
UAV Fuel system schematic is shown in Fig. 5；
The decomposition diagram of fuel system shown in Fig. 5 is shown in Fig. 6.
Specific embodiment
For a clearer understanding of the technical features, objectives and effects of the utility model, now compareing Detailed description of the invention
Specific embodiment of the present utility model.Wherein, identical component uses identical label.
As described in background, the utility model moves the load configuration knot of unmanned plane for oil disclosed in the prior art
The deficiency of structure proposes a kind of improvement structure, so that the unmanned plane has, lower fuel oil center of gravity, more stably fuel oil is conveyed,
Lighter fuel tank can be used.
Specifically, the UAV Fuel system of the utility model is on the basis of the load configuration structure of the prior art
The further improvement proposed, text of the statement quote the prior art, and those skilled in the art can be based on the prior art
Disclosure understands the other structures in relation to the dynamic unmanned plane of oil.As shown in Figs. 1-2, wherein Fig. 1 is shown practical according to this
The structural schematic diagram of the unmanned plane of a novel specific embodiment；The part-structure of unmanned plane shown in Fig. 1 that Fig. 2 is shown removes
Structural schematic diagram afterwards.
Same as the prior art referring to Fig. 1-2, the unmanned plane of the application equally includes 2, four fuselage 1, undercarriage cantilevers
3 and four rotors 5, fuselage 1 connects four cantilevers 3, and each cantilever 3 is supported by the rotor 5 of a same diameter.Fuselage 1
For the strip of bilateral symmetry, fuselage 1 has a longitudinal asymmetric axis 6, and fuselage 1 is generally elongated to be parallel to institute
State the setting of the axis of symmetry 6.The head and tail of unmanned plane are each provided with two and are symmetrical with the rotor 5 that the axis of symmetry 6 is arranged.
The load such as photoelectric nacelle 7 and arm discharge cylinder 8 are provided with below fuselage 1.The shuttle shape structure of the substantially strip of fuselage 1, machine
The width constriction of head and tail, middle part width maximum is convenient for setting engine 99.The front end of fuselage 1 be provided with can carry photoelectricity hang
The gondola hanging structure in cabin 7, the lower section of fuselage 1 be provided with can carry arm discharge cylinder 8 carry frame.Each rotor 5 surrounds
It is provided with the pod 4 of the identical circular ring shape of a shape.
The specific feature of the fuselage bearing structure of the application is further described referring to Fig. 3-4, wherein Fig. 3 is aobvious
What is shown is the fuselage interior structural schematic diagram of unmanned plane；The housing construction schematic diagram of unmanned plane is shown in Fig. 4.
Such as figure, just it has been observed that the oil of the application moves unmanned plane includes fuselage 1, undercarriage 2 and be mounted on the dynamic unmanned plane of oil
Fuselage 1 inside engine 99, fuselage 1 has a longitudinal asymmetric axis 6, and the head and tail of the dynamic unmanned plane of oil are respectively arranged
There are two the cantilever 3 for being symmetrical with the arrangement of the axis of symmetry 6, each cantilever 3 is supported by a rotor 5.
In diagram specific embodiment, the unmanned plane of the application includes the fuselage support 20 of a full symmetrical configuration, fuselage
Bracket 20 has the lateral symmetry axis 10 for being transversely to the machine direction the axis of symmetry 6.Also that is, the fuselage support 20 of the application, relative to
Longitudinal asymmetric axis 6 is symmetrical, is also symmetrical relative to lateral symmetry axis 10.The benefit of such structure setting
Be it will be apparent that the fuselage support 20 being completed can be carried out regardless of front-rear direction using, installation pressure can be mitigated,
Improve installation effectiveness.
Further, fuselage support 20 include two be symmetrical with longitudinal asymmetric axis 6 setting carbon fiber girders 201, two
A engine bearing floor 202 for being symmetrical with lateral symmetry axis 10 and being arranged, two are symmetrical with what lateral symmetry axis 10 was arranged
Undercarriage carries floor 203, and two cantilever carrying floors 204 for being symmetrical with the lateral symmetry setting of axis 10 and two are symmetrical with
The end that lateral symmetry axis 10 is arranged carries floor 205；Engine bearing floor 202, undercarriage carry floor 203, cantilever
Carry floor 204 and end carry floor 205 from the symmetrical centre of fuselage support 20 along longitudinal direction the axis of symmetry 6 two sides successively
Arrangement.In the present embodiment, fuselage support 20 is the full carbon structure component of full symmetrical configuration, relative to existing technologies, carbon fiber
Dimension girder 201 and each floor 202,203,204,205 are all made of carbon fibre composite and are made, lightweight construction, loss of weight effect
Fruit is obvious.The prior art only has rod-like structure component using carbon fibre composite, and each frame structure is due to antitorque needs, no
Obtaining does not use metal to be made, and construction weight is larger.In a specific embodiment, in order to improve torsional property, the carbon of the application
The cross section of fiber girder 201 be it is I-shaped, each floor 202,203,204,205 also uses box-like structure, can be significantly
The moment of inertia for enhancing fuselage support 20 improves the torsional property of structure, while the thin-wall construction weight of full carbon is lighter, and intensity is more
Greatly.
In a preferred embodiment, the cross section of carbon fiber girder 201 from the symmetrical centre of fuselage support 20 along longitudinal direction
The two sides of the axis of symmetry 6 are gradually reduced, and more balanced strength structure can be obtained with this, can further be obtained more
Excellent weight loss effect, and keep design strength.
The above-mentioned fuselage bearing structure of the application passes through the full carbon fuselage support of full symmetrical configuration, can pass through more low clearance
Web structure obtain enough torsional properties and intensity, while existing metal component can be rejected, significantly mitigation structure weight
Amount.The web structure of more low clearance can obtain lower fuselage height, reduce windage, reduce covering area, have excellent
Weight loss effect.In addition, various parts, can be set to the top of fuselage support, be easily installed by the fuselage support of more low clearance
Maintenance.
In addition, in a specific embodiment, two engine bearing floors 202 are connect with two carbon fiber girders 201
Four points be respectively arranged with support engine 99 four foot props 991.Namely for entire airframe structure, engine
99 be most heavy single component, and engine 99 is preferably arranged in the center of fuselage support 20, and is carbon fiber girder
The maximum position in 201 cross section, and also further foot prop 991 is arranged in engine bearing floor 202 and two carbon fibers
Four points that girder 201 connects are tieed up, to obtain bigger support strength.
In another specific embodiment of the application, the installation of four foot props 991 is located on two carbon fiber girders 201
The carry frame 81 of carry arm discharge cylinder 8 is provided with below point.Due to the weight such as rocket projectile of carry in arm discharge cylinder 8
It is very big, therefore position identical with the support point of engine 99 is arranged in carry frame 81, it avoids setting respectively in more multiposition
It sets reinforcement structure wasting space and increases weight.
In another specific embodiment of the application, cantilever 3 is fixedly connected on the pole bracket on carbon fiber girder 201
On 31, pole bracket 31 is arranged at the connection point of carbon fiber girder 201 and cantilever carrying floor 204.
In another specific embodiment of the application, the fuselage skin below carbon fiber girder 201 is arranged in undercarriage 2
Outside, and by undercarriage carrying floor 203 transmit undercarriage 2 stress.
In addition, also with the reinforcement structure of two undercarriage carrying floors 203 floor 203 can be carried in undercarriage
Top be respectively arranged with a fuel tank braced frame 207, to support the fuel tank of two weight balancings.
In addition, just it has been observed that two ends carry due to the full symmetrical configuration that the fuselage support 20 of the application uses
Floor 205 can arbitrarily be set as the bearing structure of head or tail position, can install fuselage load on fuselage support 20
When, regardless of front-rear direction, improve the convenience of operation.
Further, the upper end of two fuel tank braced frames 207 is respectively connected with the load bearing arm stretched out to the outside of fuselage 1
208, the lower section of load bearing arm 208 is provided with bearing diagonal arm 209, and the lower end setting of bearing diagonal arm 209 carries floor two ends
205 with 201 link position of carbon fiber girder at, as shown in the figure.
Further, as seen in figs. 5-6, that the fuselage 1 of unmanned plane is moved in the oil of the application is internally provided with fuel system,
Wherein, the UAV Fuel system schematic of another specific embodiment according to the present utility model is shown in Fig. 5；Fig. 6 is aobvious
What is shown is the decomposition diagram of fuel system shown in Fig. 5.As shown, the fuel system of the application includes the axis of symmetry along longitudinal direction
The first fuel tank 301 and the second fuel tank 302 that 6 front and backs are arranged, the first fuel tank 301 and the second fuel tank 302 have identical
Structure, all have the transversal cross-section of the shape of a saddle；Fuel balance is provided between first fuel tank 301 and the second fuel tank 302
Pipeline 303；First fuel tank 301 is provided with the oil returning tube 304 of connection engine 99, and its bottom is provided with connection and starts
The oil supply pipe 305 of machine 99.
In addition, being provided in fuel balance pipeline 303 by fuel oil extraction the first fuel tank of conveying in the second fuel tank 302
301 balance oil pump 306, to control fuel oil center of gravity by control system (not shown), to balance whole machine weight.It is similar
, oil feed pump 307 is provided in oil supply pipe 305.
Two fuel tanks are got up by equalizing main connection, are supplied from the first fuel tank by the fuel system of the application
Oil and oil return operation, the second fuel tank is by balancing oil pump to the first fuel tank fuel feeding, so as to remain two fuel oils
The oil mass substantial equilibrium of case.The expending equilibrium of the fuel oil of two fuel tanks only needs to control balance oil pump, is conducive to utilize
Fuel oil is balanced control to the center of gravity of unmanned plane.In addition, due to the fuel tank for using saddle-shaped configuration, so that fuel tank
The no longer overhead top in fuselage support of center of gravity, but the inside of fuselage support can be located at, reduce height of C.G..And horse
In the fuel tank of saddle structure, part fuel oil can not arbitrarily be shaken by the bottom for being contained in two sides is separated, thus can simplify combustion
The control of oily center of gravity shakes the influence to UAV Attitude without having to worry about fuel oil, can be further reduced load weight.
Further, as schemed, oil returning tube 304 is arranged in fuel balance pipeline 303 side by side.A set of can be shared in this way
Support component is supported, with economization construction weight.
Two side bottoms and oil supply pipe 305 of the shape of a saddle of first fuel tank 301 are interconnected, so that the first fuel tank
The fuel consumption of two sides is identical in 301, avoids two sides fuel weight uneven.
Preferably, fuel balance pipeline 303 is connected to the bottom of the second fuel tank 302；Fuel balance pipeline 303 and first
The top of fuel tank 301 is connected to.That is, the fuel oil of the second fuel tank 302 is supplemented into the upper of the first fuel tank 301 from bottom extraction
Portion, the fuel oil of supplement and oil return can balance from the top of the first fuel tank 301 and be distributed in the two of the first fuel tank 301
Side further avoids the unbalanced problem of two sides fuel weight.
In another specific embodiment, a side bottom of the shape of a saddle of fuel balance pipeline 303 and the second fuel tank 302
Connection, the siphon piping of the bottom of the two sides of the shape of a saddle for being internally provided with the second fuel tank 302 of connection of the second fuel tank 302
(not shown).Namely the second fuel tank 302 is mainly used for supplementing fuel oil, as long as setting siphon piping side
Just the fuel oil by 302 two sides of the second fuel tank is persistently extracted out, is not needed that complicated control pipeline is additionally arranged, is advantageously reduced
Construction weight.
In addition, for the ease of rapid refueling, the first fuel tank 301 and the second fuel tank 302 are respectively arranged with independent
Oil filler 308 and independent blow vent 309.Moreover, the bottommost of the first fuel tank 301 and the second fuel tank 302 can be with
Independent fuel outlet is further set, in order to discharge waste oil.
In addition, as previously mentioned, fuselage support 20 has the lateral symmetry axis 10 for being transversely to the machine direction the axis of symmetry 6；This Shen
The first fuel tank 301 and the second fuel tank 302 please is symmetrical with lateral symmetry axis 10 and is set on fuselage support 20.It is specific next
Say be symmetrically disposed on fuselage support 20 relative to lateral symmetry axis 10, front and back, it is arranged in fuselage
In the fuel tank braced frame 207 of the top of the undercarriage carrying floor 203 of bracket 20.In addition, corresponding to the special form of fuel tank
Shape, the fuel tank braced frame 207 of the application have the middle part of the shape of a saddle of the first fuel tank 301 of support and the second fuel tank 302
Crosspiece 310, using crosspiece 301 support fuel tank middle part, avoid fuel tank from shaking, improve the stability of support construction,
And it is just constructed without additional support.
Further, there are two for cooling down dissipating for engine for neighbouring first fuel tank 301 and the setting of the second fuel tank 302
Hot device 300, radiator 300 are provided with air-cooled fan, and the air-cooled fan that can use radiator 300 provides additionally fuel tank
Cooling or heating is also unlikely to high-altitude supercooling, is conducive to engine to keep the temperature of fuel system to be not to overheat
Sustainedly and stably work.
In conclusion the fuel system of the application, two fuel tanks is got up by equalizing main connection, from the first fuel oil
Case carries out fuel feeding and oil return operation, and the second fuel tank is by balancing oil pump to the first fuel tank fuel feeding, so as to remain
The oil mass substantial equilibrium of two fuel tanks.The expending equilibrium of the fuel oil of two fuel tanks only needs to control balance oil pump, has
Control is balanced conducive to using center of gravity of the fuel oil to unmanned plane.In addition, due to the fuel tank for using saddle-shaped configuration, so that
The no longer overhead top in fuselage support of the center of gravity of fuel tank, but the inside of fuselage support can be located at, reduce center of gravity height
Degree.And in the fuel tank of saddle-shaped configuration, part fuel oil can not arbitrarily be shaken by the bottom for being contained in two sides is separated, without load
Heart fuel oil shakes the influence to UAV Attitude, can be further reduced load weight.
The above descriptions are merely exemplary embodiments of the present utility model, the model being not intended to limit the utility model
It encloses.Any those skilled in the art, under the premise of not departing from the conceptions and principles of the utility model made equivalent variations,
Modification and combination, should belong to the range of the utility model protection.
Claims (6)
1. a kind of UAV Fuel system, the dynamic unmanned plane of oil includes fuselage (1), undercarriage (2) and is mounted on the oil
The internal engine (99) of the fuselage (1) of dynamic unmanned plane, the fuselage (1) have a longitudinal asymmetric axis (6), and the oil is dynamic
The head and tail of unmanned plane are each provided with two cantilevers (3) for being symmetrical with the longitudinal asymmetric axis (6) arrangement, each described
Cantilever (3) is supported by a rotor (5), it is characterised in that: the fuel system includes before the longitudinal asymmetric axis (6)
The first fuel tank (301) and the second fuel tank (302) arranged afterwards, first fuel tank (301) and the second fuel tank (302)
Structure having the same all has the transversal cross-section of the shape of a saddle；First fuel tank (301) and the second fuel tank (302) it
Between be provided with fuel balance pipeline (303)；First fuel tank (301) is provided with the oil returning tube of connection engine (99)
(304)；The bottom of first fuel tank (301) is provided with the oil supply pipe (305) of connection engine (99)；The unmanned plane
Fuselage support (20) including a full symmetrical configuration；First fuel tank (301) and the second fuel tank (302) are set to institute
In the fuel tank braced frame (207) for stating the top of undercarriage carrying floor (203) of fuselage support (20)；The fuel tank support frame
Frame (207) has the crosspiece (310) at the middle part for the shape of a saddle for supporting first fuel tank (301) and the second fuel tank (302).
2. UAV Fuel system as described in claim 1, which is characterized in that setting in the fuel balance pipeline (303)
There is the balance oil pump (306) that the fuel oil extraction in second fuel tank (302) is conveyed to first fuel tank (301).
3. UAV Fuel system as described in claim 1, which is characterized in that the oil returning tube (304) is side by side in described
Fuel balance pipeline (303) setting.
4. UAV Fuel system as described in claim 1, which is characterized in that be provided with confession in the oil supply pipe (305)
Oil pump (307).
5. UAV Fuel system as described in claim 1, which is characterized in that the shape of a saddle of first fuel tank (301)
Two side bottoms and the oil supply pipe (305) be interconnected.
6. UAV Fuel system as described in claim 1, which is characterized in that first fuel tank (301) and the second combustion
Fuel tank (302) is respectively arranged with independent oil filler (308) and independent blow vent (309).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822177530.XU CN209258408U (en) | 2018-12-24 | 2018-12-24 | A kind of UAV Fuel system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822177530.XU CN209258408U (en) | 2018-12-24 | 2018-12-24 | A kind of UAV Fuel system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN209258408U true CN209258408U (en) | 2019-08-16 |
Family
ID=67561237
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201822177530.XU Active CN209258408U (en) | 2018-12-24 | 2018-12-24 | A kind of UAV Fuel system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN209258408U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112407304A (en) * | 2020-09-30 | 2021-02-26 | 北京北航天宇长鹰无人机科技有限公司 | Unmanned aerial vehicle oil tank |
| CN112537456A (en) * | 2020-11-24 | 2021-03-23 | 中电科芜湖通用航空产业技术研究院有限公司 | Modular aircraft tank subassembly and aircraft |
| CN112832938A (en) * | 2020-12-31 | 2021-05-25 | 飒摩(苏州)船艇科技有限公司 | Fuel oil distribution system for ship body |
-
2018
- 2018-12-24 CN CN201822177530.XU patent/CN209258408U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112407304A (en) * | 2020-09-30 | 2021-02-26 | 北京北航天宇长鹰无人机科技有限公司 | Unmanned aerial vehicle oil tank |
| CN112407304B (en) * | 2020-09-30 | 2021-07-02 | 北京北航天宇长鹰无人机科技有限公司 | Unmanned aerial vehicle oil tank |
| CN112537456A (en) * | 2020-11-24 | 2021-03-23 | 中电科芜湖通用航空产业技术研究院有限公司 | Modular aircraft tank subassembly and aircraft |
| CN112832938A (en) * | 2020-12-31 | 2021-05-25 | 飒摩(苏州)船艇科技有限公司 | Fuel oil distribution system for ship body |
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