CN212074446U - Large-scale unmanned aerial vehicle high reliability fuel oil system - Google Patents
Large-scale unmanned aerial vehicle high reliability fuel oil system Download PDFInfo
- Publication number
- CN212074446U CN212074446U CN201922359008.8U CN201922359008U CN212074446U CN 212074446 U CN212074446 U CN 212074446U CN 201922359008 U CN201922359008 U CN 201922359008U CN 212074446 U CN212074446 U CN 212074446U
- Authority
- CN
- China
- Prior art keywords
- fuel
- oil
- tank
- fuel tank
- oil tank
- 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.)
- Active
Links
- 239000000295 fuel oil Substances 0.000 title claims abstract description 27
- 239000003921 oil Substances 0.000 claims abstract description 280
- 239000000446 fuel Substances 0.000 claims abstract description 110
- 239000002828 fuel tank Substances 0.000 claims abstract description 69
- 230000005484 gravity Effects 0.000 claims abstract description 51
- 239000000945 filler Substances 0.000 claims abstract description 15
- 239000013049 sediment Substances 0.000 claims description 3
- 238000009423 ventilation Methods 0.000 claims description 2
- 238000012423 maintenance Methods 0.000 abstract description 6
- 238000004519 manufacturing process Methods 0.000 abstract description 5
- 238000012545 processing Methods 0.000 abstract description 4
- 238000013461 design Methods 0.000 abstract description 3
- 238000007726 management method Methods 0.000 description 13
- 230000006870 function Effects 0.000 description 10
- 239000007924 injection Substances 0.000 description 8
- 238000002347 injection Methods 0.000 description 8
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 7
- 238000000034 method Methods 0.000 description 7
- 230000008569 process Effects 0.000 description 5
- 230000002159 abnormal effect Effects 0.000 description 4
- 230000009471 action Effects 0.000 description 3
- 238000004364 calculation method Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012544 monitoring process Methods 0.000 description 2
- 230000032258 transport Effects 0.000 description 2
- 230000008859 change Effects 0.000 description 1
- 238000012938 design process Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 238000001556 precipitation Methods 0.000 description 1
- 238000005086 pumping Methods 0.000 description 1
- 230000009711 regulatory function Effects 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
- 238000001228 spectrum Methods 0.000 description 1
- 238000013022 venting Methods 0.000 description 1
Images
Landscapes
- Loading And Unloading Of Fuel Tanks Or Ships (AREA)
Abstract
A large-scale unmanned aerial vehicle high reliability fuel oil system, including fuel tank system, also include fuel feeding system and oil delivery system communicated with fuel tank system, the fuel tank system includes the middle fuel tank set up in the body gravity position, set up in the front fuel tank of the front side of middle fuel tank and set up in the rear fuel tank of the rear side of middle fuel tank, the middle fuel tank communicates with front fuel tank and rear fuel tank through the oil delivery system separately; the top of the front oil tank is provided with a first gravity filler cap used for filling oil in the whole fuel tank system; the middle oil tank is lowest in the bottom surface in the vertical direction and is used for conveying fuel oil to the engine through an oil supply system; the rear oil tank stores oil and adjusts the balance of the whole machine body. The arrangement of the structure disclosed by the invention adopts a pure mechanical gravity oil transportation technical scheme, the structure is very simple, the processing, the production, the assembly and the maintenance are simple and convenient, and the cost is lower; meanwhile, a redundant design is adopted, the gravity center adjusting function is realized, the reliability of the system is improved, the fuel oil can be conveyed to the maximum, and the unavailable residual oil is less.
Description
Technical Field
The utility model belongs to the aviation field, concretely relates to large-scale unmanned aerial vehicle high reliability fuel oil system.
Background
At present, the large unmanned aerial vehicle is developed at a high speed, and the type spectrum of the large unmanned aerial vehicle is gradually improved. New requirements are provided for the fuel system of the unmanned aerial vehicle. For an unmanned aerial vehicle fuel system, the main realized functions are basically the same as those of an unmanned aerial vehicle. The fuel oil required by the engine is stored, the fuel oil with specified pressure and flow is supplied to the engine according to a certain sequence under all flight states allowed by the airplane, and the gravity center of the airplane is kept within a certain reasonable range. However, in the existing large-scale unmanned aerial vehicle fuel system, the technology of the fuel system of the unmanned aerial vehicle is mostly carried, and some fuel systems of the unmanned aerial vehicle even need manual intervention. At present, to the large-scale unmanned aerial vehicle who does not install the wing oil tank, domestic fuel system technical scheme is mostly: the refueling mode adopts gravity refueling from a middle fuel tank; the fuel conveying mode adopts an injection pump for conveying fuel, injection flow with high flow speed and low pressure is generated after the fuel conveying mode works through a fuel supply pump, and fuel is pumped from each fuel tank to the fuel supply tank; the gravity center control mode is that related parameters such as an oil delivery flow limiting port, pipeline flow resistance, injection capacity of an injection pump, pipeline length and the like are reasonably calculated, fuel is injected to an oil supply tank from each oil tank in proportion, and the general accuracy of the gravity center control range is not high.
From well oil tank gravity refuel comparatively inconvenient, the oil tank all distributes in the wing position among the unmanned aerial vehicle, brings inconvenience for guarantee work such as refuel, maintenance. The injection pump oil transportation can cause that the unusable residual oil in the oil tank is more. The injection pump cannot be installed too low, so that the distance between the oil pumping opening of the injection pump and the outer wall of the oil tank is too short due to too low installation, and the injection effect is influenced; the ejector pump must be installed inside the oil tank, and the production, assembly and maintenance costs are high. Meanwhile, the pipeline is complex and long. If the ejector pump in the oil tank fails, such as the ejector pump or a pipeline in the oil tank is disconnected, fuel cannot be ejected to the oil supply tank, and the fuel in the oil supply tank flows into other oil tanks through the ejection flow, so that the dangerous results of insufficient fuel in the oil supply tank, center-of-gravity shift of an airplane and the like are caused; in addition, the voltage of the onboard generator is unstable, so that the fuel flow pressure at the outlet of the fuel supply pump is unstable, and the operation of the ejector pump is unstable. During fuel oil gravity center control, follow each oil tank to oil supply tank oil transportation with certain proportion, this proportion is generally controlled by the restricted aperture in the ejector pump pipeline, and it is long to draw the pipeline in addition, and the flow resistance is different, leads to the calculation of restricted aperture size more complicated, increases the difficulty in the design process, to different large-scale unmanned aerial vehicle, must carry out redesign calculation, has increased the cost, has reduced the commonality.
Disclosure of Invention
In order to solve the problems, the utility model aims to provide a high-reliability fuel system of a large unmanned aerial vehicle, which adopts a purely mechanical gravity fuel delivery technical scheme through reasonable arrangement of component structures, has very simple structure, simple and convenient processing, production, assembly and maintenance and lower cost; meanwhile, a redundant design is adopted, the gravity center adjusting function is realized, the reliability of the system is improved, the fuel oil can be conveyed to the maximum, and the unavailable residual oil is less.
In order to achieve the above object, the utility model discloses the technical scheme who takes includes:
a large-scale unmanned aerial vehicle high reliability fuel oil system, including fuel tank system, also include fuel feeding system and oil delivery system communicated with fuel tank system, the fuel tank system includes the middle fuel tank set up in the body gravity position, set up in the front fuel tank of the front side of middle fuel tank and set up in the rear fuel tank of the rear side of middle fuel tank, the middle fuel tank communicates with front fuel tank and rear fuel tank through the oil delivery system separately; the top of the front oil tank is provided with a first gravity filler cap used for filling oil in the whole fuel tank system; the middle oil tank is lowest in the bottom surface in the vertical direction and is used for conveying fuel oil to the engine through an oil supply system; the rear oil tank stores oil and adjusts the balance of the whole machine body.
Optionally, the oil transportation system includes a main oil transportation pipeline, and the main oil transportation pipeline transports the fuel oil in the front oil tank to the middle oil tank and the rear oil tank, and communicates the middle oil tank and the rear oil tank.
Optionally, the oil transportation system further includes a redundant oil transportation pipeline, and the redundant oil transportation pipeline transports the fuel oil in the front oil tank and the fuel oil in the rear oil tank to the middle oil tank.
Optionally, the main oil pipeline is connected with a first one-way valve to the middle oil tank through a front oil tank, and is connected with a second one-way valve to the middle oil tank through a rear oil tank; the redundant oil delivery pipeline is connected with a first electromagnetic valve, a third one-way valve and an electric piston pump in sequence through a front oil tank and leads to a middle oil tank, and a rear oil tank is connected with a second electromagnetic valve, a fourth one-way valve and an electric piston pump in sequence and leads to a middle oil tank.
Optionally, the oil delivery system further comprises an oil tank ventilation system communicating the front oil tank, the middle oil tank and the rear oil tank.
Optionally, the oil supply system comprises a double centrifugal pump arranged at the bottom of the middle oil tank in parallel, and the filter, the first oil drain valve, the manual cut-off valve and the flow sensor are sequentially connected in series through an oil supply pipeline to deliver fuel oil to the engine.
Optionally, the bottoms of the middle oil tank and the front oil tank are both planes, and the bottom of the rear oil tank is an inclined plane.
Optionally, a first capacitive oil quantity sensor is arranged at the top of the front oil tank, and a second oil drain valve is arranged at the bottom of the front oil tank; the bottom end of the first capacitance type oil quantity sensor is close to the bottom surface of the front oil tank.
Optionally, a sediment valve, a temperature sensor and a dielectric constant sensor are arranged on the bottom surface of the middle oil tank, a second gravity oil filler cap and a second capacitance type oil mass sensor are arranged on the top of the middle oil tank, and the bottom end of the second capacitance type oil mass sensor is close to the bottom surface of the middle oil tank; the middle oil tank is also provided with a bottom oil level annunciator and an oil pump pressure annunciator, and the oil pump pressure annunciator is internally connected with the double centrifugal pump.
Optionally, the top of the rear oil tank is provided with a third gravity filler cap and two third capacitive oil mass sensors respectively positioned at the front side and the rear side of the rear oil tank, and the bottom end of each third capacitive oil mass sensor is close to the bottom surface of the rear oil tank.
And the fuel management system is controlled by an automatic controller and a fuel computer and is connected with each sensor, the oil pump, the first electromagnetic valve and the second electromagnetic valve through a fuel control cable.
And the flight control computer receives the parameters of the fuel management system, and realizes the control of the fuel system and the adjustment of the gravity center of the airplane.
Compared with the prior art, the utility model, following technological effect has:
(1) the utility model discloses a large-scale unmanned aerial vehicle high reliability fuel oil system adopts pure mechanical type gravity oil transportation technical scheme, and the structure is very simple, and processing, production, assembly and maintenance are simple and convenient, and the cost is lower simultaneously.
(2) The utility model discloses a large-scale unmanned aerial vehicle high reliability fuel oil system, redundant defeated oil pipe way has improved the reliability of system, has realized focus regulatory function simultaneously, under the prerequisite of guaranteeing the function, makes the biggest simplification of system.
(3) The utility model discloses a large-scale unmanned aerial vehicle high reliability fuel oil system introduces focus governing system, makes the aircraft all keep the focus to be in the optimum position at whole flight in-process, has improved the flight quality.
(4) The utility model discloses a large-scale unmanned aerial vehicle high reliability fuel oil system does not adopt the mode of drawing and penetrating the oil transportation for can defeated the fuel maximize, unavailable residual oil is less.
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 principles of the invention and not to limit the invention. In the drawings:
fig. 1 is a schematic structural diagram of a high-reliability fuel system of a large unmanned aerial vehicle according to the present invention;
the reference numerals in the figures denote:
a, a fuel tank system; a1 front oil tank; a11 first capacitance type oil quantity sensor; a12 first gravity filler cap; a13 first oil drain valve; a2 middle oil tank; a21 double centrifugal pump; a22 oil pump pressure annunciator; a23 second gravity filler cap; a24 second capacitance type oil quantity sensor; a25 bottom oil level annunciator; a26 temperature sensor; a27 dielectric constant sensor; a28 discharge valve; a3 rear oil tank; a31 third gravity filler cap; a32 third capacitive oil mass sensor; a33 discharge valve; a4 tank vent system; b, an oil supply system; a B1 filter; b2 second drain valve; b3 manual cut-off valve; b4 flow sensor; a B5 engine; c, an oil transportation system; c1 main oil pipeline; c11 first check valve; a C12 second check valve; c2 redundant oil pipelines; a C21 first solenoid valve; c22 third check valve; c23 fourth check valve; a C24 second solenoid valve; c25 electric piston pump; d, a fuel control cable; e, a fuel management system; e1 automatic controller; e2 fuel computer; f, flying to control the computer.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings, which are provided for illustration and not for limitation of the invention.
A large unmanned aerial vehicle high-reliability fuel system comprises a fuel tank system A, an oil supply system B and a fuel delivery system C which are communicated with the fuel tank system A, wherein the fuel tank system A comprises a middle oil tank A2 arranged at the gravity center of a fuselage, a front oil tank A1 arranged at the front side of a middle oil tank A2 and a rear oil tank A3 arranged at the rear side of the middle oil tank A2, and the middle oil tank A2 is respectively communicated with the front oil tank A1 and the rear oil tank A3 through the fuel delivery system C; the top of the front oil tank A1 is provided with a first gravity filler cap A12 for filling oil to the whole fuel tank system A; the middle oil tank A2 is lowest on the bottom surface in the vertical direction and delivers fuel to an engine B5 through a fuel supply system B; the rear oil tank A3 stores oil and adjusts the balance of the whole fuselage. Well oil tank A2 installs in the unmanned aerial vehicle middle part, and its focus position and unmanned aerial vehicle focus position coincidence or distance are very little. The front oil tank A1 and the rear oil tank A3 are distributed on two sides of the middle oil tank A2, and the volume of the front oil tank A1 is slightly larger than that of the rear oil tank 15. When the oil tank is filled with oil, the three oil tanks can be provided with gravity oil filler caps, and oil can be filled from any oil tank; normally, the oil is filled from the first gravity filler cap A12 of the front oil tank A1, and the front oil tank A1 feeds oil to the middle oil tank A2 and the rear oil tank A3 under the action of gravity and the oil feeding system C, and the oil levels of the three oil tanks are at the same level under the action of gravity. The oil tank A1 refuels convenient and fast before adopting, compares and refuels from middle oil tank A2, and operating personnel need not to stand and operate on the wing, and the setting of three oil tank adjusts the balance of whole fuselage when the volume of producing oil is big, and pure mechanical type gravity oil transportation technical scheme, the structure is very simple, and processing, production, assembly and maintenance, simple and convenient, the cost is lower simultaneously.
The fuel delivery system C comprises a main fuel delivery line C1, and the main fuel delivery line C1 delivers fuel from the front tank A1 to the middle tank A2 and the rear tank A3, and communicates the middle tank A2 with the rear tank A3. The main oil pipeline C1 is connected with a first check valve C11 from a front oil tank A1 to a middle oil tank A2, and the rear oil tank A3 is connected with a second check valve C12 to a middle oil tank A2. In general, the front oil tank A1 is filled with oil from the oil filler cap, the main oil pipeline C1 is used for oil transportation, and the second check valve C12 is closed during oil filling, so that the front oil tank does not have the function of a check valve; the fuel respectively flows to the middle oil tank A2 and the rear oil tank A3 through the first check valve C11 and the second check valve C12, and the second check valve C12 is opened after the fuel is filled, so that the function of the check valves is recovered. The fuel of the front fuel tank A1 and the rear fuel tank A3 is conveyed to the middle fuel tank A2 through the main fuel conveying pipeline C1 under the action of gravity, and two one-way valves on the main fuel conveying pipeline C1 can prevent the fuel from flowing back to the front fuel tank A1 or the rear fuel tank A3 from the middle fuel tank A2 when the attitude angle is generated in the flying process. In addition, the diameter of the main oil conveying pipeline C1 is 40mm, the diameter of the pipeline is extremely large, the strength is high, oil is conveyed to the oil supply tank in a gravity mode, the pipeline is very simple, few parts and finished products are produced, and the reliability is extremely high.
The fuel delivery system C also includes a redundant fuel delivery line C2, the redundant fuel delivery line C2 delivering fuel from the front tank a1 and the rear tank A3 to the middle tank a 2. The redundant oil delivery pipeline C2 is connected with a first electromagnetic valve C21, a third one-way valve C22 and an electric piston pump C25 in sequence from a front oil tank A1 to a middle oil tank A2, and the rear oil tank A3 is connected with a second electromagnetic valve C24, a fourth one-way valve C23 and an electric piston pump C25 in sequence to a middle oil tank A2. When the gravity center of the airplane is changed due to posture change or oil leakage and the like, the redundant oil delivery pipeline C2 starts to work, firstly, the electric piston pump C25 is opened, when the gravity center of the airplane needs to be adjusted forwards, the second electromagnetic valve 24 is opened, and fuel oil in the rear oil tank 15 enters the middle oil tank 12; when the gravity center of the airplane needs to be adjusted backwards, the second electromagnetic valve C24 is opened, and fuel oil in the front oil tank A1 enters the middle oil tank A2, so that the real-time adjustment of the gravity center of the airplane is completed, the gravity center of the airplane is kept at the optimal position in the whole flying process, and the flying quality is improved. When the main oil conveying pipeline C1 is abnormal due to reasons and the main oil conveying function is abnormal, along with the oil consumption of an engine, the fuel oil quantity of each oil tank is abnormal, the gravity center of the fuel oil is also abnormal, and the fuel oil management system E starts a gravity center adjusting program to adjust the gravity center and complete the redundant oil conveying function. The two paths of redundant oil transportation improve the reliability; and the redundant oil transportation function and the gravity center adjusting function share one pipeline, so that the system is simplified to the maximum extent on the premise of ensuring the functions.
The fuel delivery system C also includes a tank vent system A4 communicating the front tank A1, the middle tank A2, and the rear tank A3. The tank venting system a4 may be selected by connecting the front tank a1, the middle tank a2 and the rear tank A3 so that the pressure in the three tanks is uniform and the fuel in the three tanks is always maintained in a flat plane.
The oil supply system B comprises a double-centrifugal pump A21 which is arranged at the bottom of a medium oil tank A2 in parallel, and is sequentially connected with a filter B1, a first oil drain valve B2, a manual cut-off valve B3 and a flow sensor B4 in series through an oil supply pipeline to deliver fuel to an engine B5. When the fuel system normally supplies fuel, the middle fuel tank A2 is driven by the double centrifugal pump A21, filtered by the filter B1 through the fuel supply pipeline, the fuel supply flow is displayed by the flow sensor B4 and then led to the engine B5, and the whole fuel supply process is automatically carried out. In addition, because the ejector pump is not installed, the pressure and the flow of the oil pump cannot be divided into parts for the ejector pump, so that a centrifugal pump with low power is selected, and the oil for the engine can be met by a single oil pump. The oil supply system adopts a double-centrifugal-pump redundancy design, improves the reliability of the system, and does not adopt a mode of injecting and transporting oil, so that the fuel oil can be transported to the maximum extent, and the unavailable residual oil is less.
The bottoms of the middle oil tank A2 and the front oil tank A1 are both flat, and the bottom of the rear oil tank A3 is an inclined plane. The bottom inclined plane of the rear oil tank A3 is arranged, so that the residual oil residue can be precipitated at the lowest position, and meanwhile, a precipitation valve A33 is arranged at the lowest position of the bottom inclined plane of the rear oil tank A3, so that the residual oil residue can be conveniently discharged.
The top of the front oil tank A1 is provided with a first capacitance type oil mass sensor A11, and the bottom is provided with a second oil drain valve A13; the bottom end of the first capacitive oil quantity sensor A11 is close to the bottom surface of the front oil tank A1. The bottom surface of the middle oil tank A2 is provided with a sediment valve A28, a temperature sensor A26 and a dielectric constant sensor A27, the top of the middle oil tank A2 is provided with a second gravity oil filler cap A23 and a second capacitance type oil mass sensor A24, and the bottom end of the second capacitance type oil mass sensor A24 is close to the bottom surface of the middle oil tank A2; the middle oil tank A2 is also provided with a bottom oil level signal device A25 and an oil pump pressure signal device A22, and the oil pump pressure signal device A22 is connected with a double centrifugal pump A21. The top of the rear oil tank A3 is provided with a third gravity oil filler cap A31 and two third capacitance type oil mass sensors A32 which are respectively positioned at the front side and the rear side of the rear oil tank A3, and the bottom end of the third capacitance type oil mass sensor A32 is close to the bottom surface of the rear oil tank A3.
The fuel management system E is controlled by an automatic controller E1 and a fuel computer E2, and is connected with various sensors, an oil pump, a first electromagnetic valve C21 and a second electromagnetic valve C24 through a fuel control cable D. The aircraft fuel management system further comprises a flight control computer F, and the flight control computer F receives parameters of the fuel management system E to control the fuel system and adjust the gravity center of the aircraft. The fuel management system E is controlled by a fuel computer E2 and an automatic controller E1, and is connected with each sensor, the oil pump and a first electromagnetic valve C21 and a second electromagnetic valve C24 through a fuel control cable D. The method comprises the steps of obtaining relevant information from a first capacitive oil mass sensor A11, a second capacitive oil mass sensor A24, a low oil level signal device A25, an oil pump pressure signal device A22, a third capacitive oil mass sensor A32, a filter B1, a flow sensor B4, a dielectric constant sensor A27 and a temperature sensor A26, obtaining relevant airplane information such as airplane flight attitude and the like from a flight control computer F, receiving a corresponding instruction, and feeding back the working state and various parameters of a fuel system to the flight control computer F. The fuel management system E carries out logic judgment on the acquired information, and then controls the opening or closing of the second electromagnetic valve C24, the electric piston pump C25, the double-centrifugal pump A21 and the first electromagnetic valve C21, so that the control on the fuel system and the adjustment on the gravity center of the airplane are realized.
In the flight process of the unmanned aerial vehicle, the fuel management system E always works automatically, and whether the fuel temperature is normal is monitored through the temperature sensor A26 in real time; the working state of each oil pump is monitored by two oil pump pressure annunciators A22; monitoring whether the fuel flow is normal or not through a flow sensor B4; monitoring the working state of the filter B1 through a signaler on the filter B1; acquiring whether the oil level is low or not through a low oil level signal A25; the oil quantity of each oil tank is collected through each oil tank capacitance type oil quantity sensor, and the oil quantity measuring error is compensated through the dielectric constant sensor A27. Meanwhile, the fuel management system E sends related information to the flight control computer F, the flight control computer F also sends aircraft attitude information to the fuel management system E in real time, and the fuel management system E measures and calculates the gravity center of the aircraft according to the oil quantity of each oil tank and the aircraft attitude information, compares the gravity center with the optimal gravity center of the aircraft and adjusts the gravity center in real time, so that the gravity center of the aircraft is kept at the optimal position in the whole flight process, and the flight quality is improved.
When the flight is finished and oil drainage is needed, oil drainage can be carried out on the oil drainage valves of the front oil tank A1 and the rear oil tank A3 respectively, or the double-centrifugal pump A21 can be opened, and then the first oil drainage valve B2 is opened to drain the whole fuel system.
The preferred embodiments of the present disclosure are described in detail with reference to the accompanying drawings, however, the present disclosure is not limited to the specific details of the above embodiments, and various simple modifications may be made to the technical solution of the present disclosure within the technical idea of the present disclosure, and these simple modifications all belong to the protection scope of the present disclosure.
It should be noted that, in the foregoing embodiments, various features described in the above embodiments may be combined in any suitable manner, and in order to avoid unnecessary repetition, various combinations that are possible in the present disclosure are not described again.
In addition, any combination of the various embodiments of the present disclosure can be made, and the same should be considered as the inventive content of the present disclosure, as long as the combination does not depart from the spirit of the present disclosure.
Claims (10)
1. The utility model provides a large-scale unmanned aerial vehicle high reliability fuel oil system, includes fuel tank system (A), still includes oil feeding system (B) and oil delivery system (C) with fuel tank system (A) intercommunication, its characterized in that, fuel tank system (A) is including establishing well oil tank (A2) of fuselage gravity center level, establishing preceding oil tank (A1) of well oil tank (A2) front side and establishing back oil tank (A3) of well oil tank (A2) rear side, well oil tank (A2) communicates with preceding oil tank (A1) and back oil tank (A3) through oil delivery system (C) respectively;
the top of the front oil tank (A1) is provided with a first gravity filler cap (A12) used for filling oil in the whole fuel tank system (A);
the middle oil tank (A2) is lowest on the bottom surface in the vertical direction and is used for delivering fuel to an engine (B5) through an oil supply system (B);
the rear oil tank (A3) stores oil and adjusts the balance of the whole fuselage.
2. A large unmanned aerial vehicle high reliability fuel system as claimed in claim 1, wherein the fuel delivery system (C) comprises a main fuel delivery pipeline (C1), the main fuel delivery pipeline (C1) delivers fuel in the front fuel tank (a1) to the middle fuel tank (a2) and the rear fuel tank (A3) and connects the middle fuel tank (a2) and the rear fuel tank (A3).
3. The fuel system of large unmanned aerial vehicle with high reliability as set forth in claim 2, wherein the fuel delivery system (C) further comprises a redundant fuel delivery line (C2), the redundant fuel delivery line (C2) delivering fuel from the front fuel tank (a1) and the rear fuel tank (A3) to the middle fuel tank (a 2).
4. A large unmanned aerial vehicle high reliability fuel system as claimed in claim 3, wherein the main fuel pipeline (C1) is connected to the middle fuel tank (a2) from the front fuel tank (a1) through the first check valve (C11), and the rear fuel tank (A3) is connected to the middle fuel tank (a2) through the second check valve (C12);
the redundant oil delivery pipeline (C2) is connected with a first electromagnetic valve (C21), a third one-way valve (C22) and an electric piston pump (C25) from a front oil tank (A1) to lead to a middle oil tank (A2), and the rear oil tank (A3) is connected with a second electromagnetic valve (C24), a fourth one-way valve (C23) and an electric piston pump (C25) to lead to the middle oil tank (A2) in sequence.
5. A large unmanned aerial vehicle high reliability fuel system according to claim 1, wherein the fuel delivery system (C) further comprises a fuel tank ventilation system (a4) communicating the front fuel tank (a1), the middle fuel tank (a2) and the rear fuel tank (A3).
6. The large unmanned aerial vehicle high-reliability fuel system as claimed in claim 1, wherein the fuel supply system (B) comprises a double centrifugal pump (A21) which is arranged at the bottom of a medium fuel tank (A2) in parallel and is used for supplying fuel to the engine (B5) through a fuel supply pipeline which is connected with a filter (B1), a first fuel drain valve (B2), a manual cut-off valve (B3) and a flow sensor (B4) in series.
7. The high-reliability fuel system of the large unmanned aerial vehicle as claimed in claim 1, wherein the bottoms of the middle fuel tank (A2) and the front fuel tank (A1) are both flat, and the bottom of the rear fuel tank (A3) is a slope.
8. The large unmanned aerial vehicle high-reliability fuel system as claimed in any one of claims 1-7, wherein the top of the front fuel tank (A1) is provided with a first capacitive fuel quantity sensor (A11), and the bottom is provided with a second fuel drain valve (A13);
the bottom end of the first capacitance type oil quantity sensor (A11) is close to the bottom surface of the front oil tank (A1).
9. The large unmanned aerial vehicle high-reliability fuel system as claimed in claim 8, wherein a sediment valve (A28), a temperature sensor (A26) and a dielectric constant sensor (A27) are arranged on the bottom surface of the middle fuel tank (A2), a second gravity fuel cap (A23) and a second capacitive fuel sensor (A24) are arranged on the top of the middle fuel tank (A2), and the bottom end of the second capacitive fuel sensor (A24) is close to the bottom surface of the middle fuel tank (A2);
the middle oil tank (A2) is also provided with a bottom oil level annunciator (A25) and an oil pump pressure annunciator (A22), and the oil pump pressure annunciator (A22) is internally connected with the double centrifugal pump (A21).
10. The large unmanned aerial vehicle high-reliability fuel system as claimed in claim 9, wherein a third heavy fuel filler cap (a31) and two third capacitive fuel sensors (a32) respectively located at the front side and the rear side of the rear fuel tank (A3) are arranged at the top of the rear fuel tank (A3), and the bottom end of the third capacitive fuel sensor (a32) is close to the bottom surface of the rear fuel tank (A3).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922359008.8U CN212074446U (en) | 2019-12-25 | 2019-12-25 | Large-scale unmanned aerial vehicle high reliability fuel oil system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922359008.8U CN212074446U (en) | 2019-12-25 | 2019-12-25 | Large-scale unmanned aerial vehicle high reliability fuel oil system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN212074446U true CN212074446U (en) | 2020-12-04 |
Family
ID=73565309
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201922359008.8U Active CN212074446U (en) | 2019-12-25 | 2019-12-25 | Large-scale unmanned aerial vehicle high reliability fuel oil system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN212074446U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112550738A (en) * | 2020-12-25 | 2021-03-26 | 武汉航空仪表有限责任公司 | Pressure-regulated proportional oil delivery system and method |
-
2019
- 2019-12-25 CN CN201922359008.8U patent/CN212074446U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112550738A (en) * | 2020-12-25 | 2021-03-26 | 武汉航空仪表有限责任公司 | Pressure-regulated proportional oil delivery system and method |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| EP3109165A1 (en) | Continuous fuel tank level control | |
| CN103038133B (en) | A refuel control system and method of refuelling | |
| RU2578843C2 (en) | Systems and methods for maintenance of compliance with requirements to structural load of aircraft extra fuel tank | |
| CN105438484A (en) | Aircraft fuel system | |
| CN103057714A (en) | Auxiliary fuel system | |
| US9409651B2 (en) | Aircraft aerial refuelling system | |
| CN209276141U (en) | A kind of oil filling machine | |
| CN212074446U (en) | Large-scale unmanned aerial vehicle high reliability fuel oil system | |
| CN112644721A (en) | Aircraft oil supply and delivery system and control method thereof | |
| CN107336838A (en) | Oil tank for unmanned aerial vehicle | |
| CA3052168C (en) | Mobile distribution station having pneumatic valves | |
| GB2544080A (en) | An aircraft fuel system | |
| CN111498124B (en) | Aircraft fuel supply system and auxiliary fuel control method | |
| EP3604139A1 (en) | Refuelling system | |
| EP2877400B1 (en) | Fuel transfer system controlled by float valves | |
| CN218703931U (en) | Pressure oiling system and aircraft | |
| CN217374913U (en) | A UAV fuel system | |
| CN216233010U (en) | Oil supply system for unmanned aerial vehicle | |
| CN116331499A (en) | Unmanned aerial vehicle high reliability oil transportation system | |
| CN113335550B (en) | Airplane ground environmental control vehicle with automatic filling function | |
| CN212047910U (en) | Intermediate oil supply device of fuel oil system | |
| CN212535864U (en) | A dual-tank fuel supply system for a micro-turbojet engine test bench | |
| CN107792558A (en) | One kind regulation center of gravity of airplane integration standard fluid reservoir | |
| RU2403179C1 (en) | Method for balancing fuel reserve in aircraft wing tanks during ground operation (versions) | |
| CN209668750U (en) | A kind of automatic constant-pressure tank service truck of PLC control |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |