CN109573071A - A kind of special-shaped distributed pressurization oil supply system of unmanned plane - Google Patents
A kind of special-shaped distributed pressurization oil supply system of unmanned plane Download PDFInfo
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- CN109573071A CN109573071A CN201811639474.5A CN201811639474A CN109573071A CN 109573071 A CN109573071 A CN 109573071A CN 201811639474 A CN201811639474 A CN 201811639474A CN 109573071 A CN109573071 A CN 109573071A
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- unmanned plane
- fuel tank
- fuel
- supply system
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- 239000002828 fuel tank Substances 0.000 claims abstract description 116
- 238000000034 method Methods 0.000 claims abstract description 20
- 230000008569 process Effects 0.000 claims abstract description 15
- 239000003921 oil Substances 0.000 claims description 105
- 239000000446 fuel Substances 0.000 claims description 26
- 239000000295 fuel oil Substances 0.000 claims description 12
- 239000003502 gasoline Substances 0.000 claims description 6
- 238000010276 construction Methods 0.000 claims description 4
- 230000005484 gravity Effects 0.000 claims description 4
- 239000010705 motor oil Substances 0.000 claims description 4
- 230000002159 abnormal effect Effects 0.000 claims description 3
- 239000000314 lubricant Substances 0.000 abstract description 2
- 239000000203 mixture Substances 0.000 description 6
- 238000005086 pumping Methods 0.000 description 5
- 238000010586 diagram Methods 0.000 description 4
- 238000005183 dynamical system Methods 0.000 description 3
- 239000003129 oil well Substances 0.000 description 3
- 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 2
- 238000005273 aeration Methods 0.000 description 2
- 230000007812 deficiency Effects 0.000 description 2
- 230000006870 function Effects 0.000 description 2
- 230000000087 stabilizing effect Effects 0.000 description 2
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- 229910000831 Steel Inorganic materials 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008901 benefit Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 150000001875 compounds Chemical class 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000011152 fibreglass Substances 0.000 description 1
- 239000010763 heavy fuel oil Substances 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 239000010761 intermediate fuel oil Substances 0.000 description 1
- 230000001788 irregular Effects 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 239000000178 monomer Substances 0.000 description 1
- 230000008450 motivation Effects 0.000 description 1
- 229910052755 nonmetal Inorganic materials 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 239000010959 steel 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
- B64D37/005—Accessories not provided for in the groups B64D37/02 - B64D37/28
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Cooling, Air Intake And Gas Exhaust, And Fuel Tank Arrangements In Propulsion Units (AREA)
Abstract
The present invention provides a kind of special-shaped distributed pressurization oil supply systems of unmanned plane, by constructing the more oil tank systems being made of the special-shaped fuel tank conformal with unmanned plane shape, it makes full use of unmanned plane space to increase oil reserve, while designing the control requirement that oil consumption sequence makes oil supply system use process can satisfy unmanned plane to its mass property parameter.Oil supply system function of increasing pressure is realized using unidirectional combination pressure maintaining valve and engine mesohigh gas, fuel tank uses the consistent lubricant pipe and weight of band certain elasticity and hardness simultaneously, increase the connection oil pipe of fuel tank different parts, configure the defoaming fuel tank with exhaust outlet, engine flame-out in flight probability is reduced as far as possible, guarantees unmanned plane during flying smoothly safety.
Description
Technical field
The present invention relates to unmanned plane oil supply system field, the special-shaped distributed pressurization fuel feeding of especially a kind of unmanned plane
System.
Background technique
Fixed-wing unmanned plane mainly by housing construction, dynamical system, landing system, flight control system, airborne measurement and control system with
And the composition such as avionics system.Wherein, oil supply system is the important composition subsystem of fixed-wing unmanned plane dynamical system, is mainly used for
Storage fuel oil simultaneously delivers fuel to engine.Oil supply system mainly includes the components such as fuel tank, fuel oil, valve and pipeline.
Currently, unmanned plane oil supply system generallys use the rigid body structure fuel tank of monomer, there are the following problems for this kind of fuel tank:
1, generally use irregular figure fuel tank, thus be difficult it is conformal with fixed-wing unmanned plane covering, therefore, it is impossible to make full use of nothing
Man-machine inner space stores fuel oil.
2, for unmanned plane, especially actual airplane contracting than unmanned vehicle, the mass propertys parameter such as center of gravity, moments of inertia
It there are certain requirements.With the consumption of fuel oil, especially when unmanned plane is in the high maneuvering flight state such as post stall maneuver, tailspin
When (rotation), single oil box oil supply system is difficult to meet the control requirement of unmanned plane mass property parameter.
3, as flying height increases, the supply capability of atmospheric pressure decline, unmanned plane oil supply system will weaken.And carry out
When high maneuvering flight, the attitudes vibration of unmanned plane may make fuel tank on the lower with respect to oil pump position, i.e., oil pump is higher than oil liquid position,
It further increases as the difficulty of engine pumping fuel, engine misses caused by may cause because of the reasons such as fuel feeding is unsmooth, into
And make unmanned plane flame-out in flight.
4, single fuel tank can generate bubble during oiling and oil consumption, start if bubble sucking engine may cause
Machine is flame-out；
5, when carrying out high maneuvering flight, special-shaped fuel tank may be in any attitude in the sky, and weight in fuel tank may be made to expose oil
Face and oil can not be pumped out, also or make fuel tank fuel feeding unsmooth, lead to engine misses.Unmanned plane high dynamic flight characteristic is to oil
The smooth fuel-displaced reliability of case proposes higher requirement.
Summary of the invention
It is an object of the invention to overcome the deficiencies of the prior art and provide a kind of unmanned plane oil supply systems.It is existing to solve
The problem of with the presence of unmanned plane oil supply system, the present invention provides a kind of special-shaped distributed pressurization oil supply system, by building by
More oil tank systems of conformal special-shaped fuel tank composition, make full use of unmanned plane space to increase oil reserve, together with unmanned plane shape
When design oil consumption sequence make oil supply system use process can satisfy unmanned plane to its mass property parameter control requirement.Benefit
Oil supply system function of increasing pressure is realized with unidirectional combination pressure maintaining valve and engine mesohigh gas, while fuel tank uses the certain elasticity of band
With the consistent lubricant pipe and weight of hardness, increase the connection oil pipe of fuel tank different parts, configures the defoaming fuel tank with exhaust outlet, to the greatest extent
It may be decreased engine flame-out in flight probability, guarantee unmanned plane during flying smoothly safety.
This programme is achieved by the following technical measures:
A kind of unmanned plane with it is special-shaped it is distributed be pressurized oil supply system, including there are four special-shaped fuel tank, unidirectionally combine pressure maintaining valve, pressurization
Air entraining pipe and pressurization tracheae；Four anisotropic fuel tanks are respectively No.1 fuel tank, No. two fuel tanks, No. three fuel tanks and No. four fuel tanks,
And oil pipe is passed sequentially through according to one to No. four sequence and is connected step by step；No.1 top of oil-tank is provided with bleed ports；Bleed ports pass through
Pressurization air entraining pipe combines the connection of pressure maintaining valve gas outlet with unidirectional；The air inlet of unidirectional combination pressure maintaining valve is by being pressurized tracheae and starting
The connection of power traction gas nozzle；What the oil outlet of No. four fuel tanks pumped after being sequentially connected in series three-way connection by oil pipe and switch with engine oil
Oil inlet end connection.
As the preferred of this programme: the shape of special-shaped fuel tank fits closely unmanned plane covering and housing construction shape.
As the preferred of this programme: being provided with the flowline and weight connecting with oil outlet in each abnormal shape fuel tank；It is fuel-displaced
Pipe is with certain elasticity；The low side of flowline is arranged in weight；Flowline with weight can swing in fuel tank and will not
Bending, motion range cover most of space in fuel tank.
As the preferred of this programme: the bottom both ends of No.1 fuel tank and No. three fuel tanks are provided with connection oil pipe.
As the preferred of this programme: unidirectional combination pressure maintaining valve outlet side pressure value is not more than 35Kpa.
As the preferred of this programme: the first end No. four fuel tank oil outlets of connection of three-way connection, second end connection switch, the
Three termination oil filling pipes；The oil filling pipe is successively connected with gasoline pump and fuel reserve tank step by step.
As the preferred of this programme: the center of gravity rear and front end of unmanned plane is arranged in No.1 fuel tank and No. two fuel tanks；Described three
Number fuel tank and No. four fuel tanks are arranged in drone center of unmanned aerial vehicle near zone.
As the preferred of this programme: No. four top of oil-tank are provided with exhaust outlet, are connected with exhaust pipe on exhaust outlet, for arranging
The bubble generated in refueling process except oil supply system.
The technical effects of the invention are that:
(1) oil supply system of the application can better meet the control requirement of unmanned plane mass property parameter.Tradition is single relatively
Fuel tank oil supply system, distributed fuel tank and certain oil consumption sequence using the application, enables to gravity center shift range to meet
The use demand of unmanned plane, while being designed by fuel consumption, unmanned plane can be made when carrying out subject test, quality
Characteristic parameter value meets requirement.
(2) the oil supply system fuel feeding high reliablity of the application.Hair caused by capable of lowering as far as possible because of fuel feed deficiency
Motivation is flame-out.The application passes through setting defoaming fuel tank, the certain elasticity of configuration band and the fuel tank flowline and weight of hardness, configuration
The supercharging device etc. of the compositions such as unidirectional combination pressure charging valve, reduce engine causes to stop working because sucking air and for shortage of oil
A possibility that.
(3) the oil supply system fuel load of the application is big.The fuel tank shape of the application fits closely unmanned plane covering and body
Construction profile increases fuel load to greatest extent.
(4) the oil supply system fuel oil of the application utilizes height.It is connected to by being arranged between No.1 and No. three tank bottoms two sides
The fuel tank flowline and weight of oil pipe and configuration band certain elasticity and hardness, make it possible to make full use of in each fuel tank
Fuel oil, the residual fuel oil of each fuel tank as far as possible in reduction oil supply system use process.
(5) oiling method of the oil supply system of the application can effectively prevent engine rich oil problem occur.By at No. 4
Is sequentially connected in series three-way connection and switch between defoaming fuel tank oil outlet and engine oil pump oil inlet end, when guaranteeing to refuel fuel oil without
Method is entered in engine by oil feed pump, prevents engine from occurring the problem of can not starting because of rich oil.
It can be seen that compared with prior art, the present invention having substantive features and progress, the beneficial effect implemented
It is obvious.
Detailed description of the invention
Fig. 1 is the structural diagram of the present invention.
Fig. 2 is the schematic diagram of internal structure of single special-shaped fuel tank.
Fig. 3 is the structural schematic diagram when present invention is in fueling state.
Fig. 4 is the structural schematic diagram when present invention is in oil pumping state.
In figure, 1 is No.1 fuel tank, and 2 be No. two fuel tanks, and 3 be No. three fuel tanks, and 4 be No. four fuel tanks, and 5 be bleed mouth, and 6 be increasing
Air entraining pipe is pressed, 7 be unidirectional combination pressure maintaining valve, and 8 be pressurization tracheae, and 9 be bleed ports, and 10 be oil pipe, and 11 be connection oil pipe, and 12 be three
Pass joint, 13 be switch, and 14 be oil feed pump, and 15 be engine, and 16 be exhaust outlet, and 17 be exhaust pipe, and 18 be weight, and 19 be abnormal shape
Tank envelope, 20 be oil inlet, and 21 be oil outlet, and 22 be flowline, and 23 be gasoline pump, and 24 be fuel reserve tank, and 25 be oil well pump.
Specific embodiment
All features disclosed in this specification or disclosed all methods or in the process the step of, in addition to mutually exclusive
Feature and/or step other than, can combine in any way.
Any feature disclosed in this specification (including any accessory claim, abstract and attached drawing), except non-specifically chatting
It states, can be replaced by other alternative features that are equivalent or have similar purpose.That is, unless specifically stated, each feature is only
It is an example in a series of equivalent or similar characteristics.
As shown in Figure 1, the dynamical system using the special-shaped distributed pressurization oil supply system of unmanned plane includes: fuel tank
(1-4), unidirectionally combination pressure maintaining valve 7, oil feed pump 14 and engine 15 etc..Bleed mouth 5, unidirectionally combines pressure stabilizing at pressurization air entraining pipe 6
Valve 7 and pressurization tracheae 8 form supercharging device.In addition, flight control computer is by sending and receiving instruction to Engine ECU, to control
The operating of oil feed pump 14 processed, and the state of engine 15 is controled and monitored.Fuel tank (1-4), supercharging device and fuel feeding
Pump one works as engine oil.
As shown in Figure 1, a kind of special-shaped distributed pressurization oil supply system of unmanned plane comprising No.1 fuel tank 1, two
Number fuel tank 2, No. three fuel tanks 3, No. four fuel tanks 4, bleed mouth 5 are pressurized air entraining pipe 6, unidirectional to combine pressure maintaining valve 7, are pressurized tracheae 8, oil
Pipe 10 is connected to oil pipe 11, the composition such as three-way connection 12 and switch 13.
By taking No. two fuel tanks as an example, fuel tank is mainly by weight 18, shell 19, oil inlet 20, oil outlet 21 and 22 groups of flowline
At as shown in Figure 2.Weight 18 is that steel machine adds part, and weight is equipped with inlet port, is connected to fuel tank flowline 22, weight weight energy
Enough so that weight is able to drive flowline as tank attitude variation is freely swung in fuel tank.Shell 19 is compound by glass reinforced plastic
Material is constituted.Oil inlet 20 and oil outlet 21 are that aluminium alloy adds part, and configures sealing ring, with oil-leakage-prevention.Flowline 22 is non-
Metal material tubulation, flowline have certain elasticity, can change in fuel tank with tank attitude and arbitrarily swing, so that weight
The motion range of inlet port can cover fuel tank internal space substantially；Flowline also has certain hardness, will not be because of fuel tank appearance
State variation causes oil pipe to bend, so that fuel feeding is unsmooth.
For No.1, No. three and No. four fuel tanks, composition is similar with No. two fuel tanks, and main difference is:
1) No.1 fuel tank 1 into bleed ports 9 by pressurization tracheae 8 with unidirectionally combine 7 outlet side of pressure maintaining valve and be connected, realization fuel feeding
The function of increasing pressure of system work process.Engine high pressure gas is flowed out from bleed mouth 5, is caused pipe 6 cooling through pressurization, is flow to unidirectional
Combine 7 input terminal of pressure maintaining valve.With that is, unidirectional set close pressure maintaining valve 7 to high pressure gas carry out pressure stabilizing, output end through be pressurized tracheae 8,
The gas of steady pressure is delivered to 1 bleed ports of fuel tank, is reached for fuel-tank pressurization purpose.For ensure in oil supply system fuel tank not because
Pressure is excessive and damages, and the unidirectional 7 output end gas pressure of pressure maintaining valve that combines is not more than 35Kpa.
2) No.1 fuel tank 1 is connected with No. three 3 two sides of the bottom of fuel tank and is connected to oil pipe 11, to guarantee fuel tank two sides Height of oil
Can be consistent during oil consumption, when being exhausted to avoid side oil mass locating for weight, the other side still have compared with multiple fuel not by
It utilizes.
3) No. four fuel tanks 4 are equipped with exhaust outlet 16 and exhaust pipe 17.When refueling to No. four fuel tanks 4, pass through 16 He of exhaust outlet
A large amount of removal of bubbles fuel tanks that the exhaust pipe 17 being attached thereto will generate in refueling process, it is a large amount of empty because sucking to reduce engine
Gas and flame-out probability.
4) No. four fuel tank oil outlets are sequentially connected in series three-way connection 12 and switch 13, pass through the closure and three-way connection of switch 13
Safety oiling and the fuel feeding being closed to realize fuel tank of one end of connected pipes in 12.
A kind of refueling process of the special-shaped distributed pressurization oil supply system of the unmanned plane, as shown in Figure 3.
Switch 13 is placed in off, engine 15 is entered by oil feed pump 14 to prevent fuel oil, causes engine 15 rich
Oil.One termination 23 output end of gasoline pump of 12 connected pipes of three-way connection, 23 input terminal of gasoline pump pass through oil pipe and fuel reserve tank 24
It is connected.No.1 fuel tank bleed ports 9 with unidirectionally combine pressure maintaining valve 7 and disconnects, holding 9 aeration status of No.1 fuel tank bleed ports.It opens
Dynamic gasoline pump 23,24 intermediate fuel oil of fuel reserve tank is extracted out, the fuel tank 2 and one of fuel tank 3, two of No. four fuel tanks 4, three is successively delivered to
Number fuel tank 1.When No.1 fuel tank bleed ports 9 start to overflow fuel oil outward, stop refueling, by connected pipes in three-way connection 12
One end blocks.Switch 13 still maintains closed state, until engine 15 needs to turn on the switch 13 when fuel feeding.In refueling process, four
Number fuel tank exhaust pipe 17 keeps vertical aeration status, and the bubble generated in refueling process is discharged, and its nozzle height is higher than four
4 height of number fuel tank guarantees that fuel oil is not flowed out from No. four fuel tank exhaust pipes 17.After oiling, No. four fuel tank exhaust pipes 17 are blocked.
A kind of oil consumption process of the special-shaped distributed pressurization oil supply system of the unmanned plane, as shown in Figure 1.
Connection No.1 fuel tank bleed ports with unidirectionally combine 7 output end of pressure maintaining valve, turn on the switch 13.Start engine 15, combustion
Oil is delivered to engine chamber by fuel tank by oil feed pump 14.Fuel consumption sequence is the fuel tank 2, three of No.1 fuel tank 1, two
Fuel tank 3 and No. four fuel tanks 4.In Fuel injection system, the high pressure gas that engine 15 generates is in fuel tank by unidirectionally combination pressure maintaining valve 7
Steady pressure is provided, to guarantee fuel tank fuel feeding reliability.
A kind of oil pumping process of the special-shaped distributed pressurization oil supply system of the unmanned plane, as shown in Figure 4.It will switch 13
It is placed in off.Three-way connection connects oil pipe end and connect with 25 input terminal of oil well pump, and oil pumping pump output terminal passes through oil pipe and oil storage
Case 24 connects.Start oil well pump 25, fuel from fuel tank is delivered in fuel reserve tank 24.In oil pumping process, fuel tank can be shaken, with to the greatest extent
Remaining oil mass in fuel tank may be reduced.
The invention is not limited to specific embodiments above-mentioned.The present invention, which expands to, any in the present specification to be disclosed
New feature or any new combination, and disclose any new method or process the step of or any new combination.
Claims (8)
1. a kind of unmanned plane is pressurized oil supply system with special-shaped distribution, it is characterized in that: including that there are four special-shaped fuel tank, unidirectionally combinations
Pressure maintaining valve, pressurization air entraining pipe and pressurization tracheae；Described four anisotropic fuel tanks are respectively No.1 fuel tank, No. two fuel tanks, No. three fuel tanks
With No. four fuel tanks, and oil pipe is passed sequentially through according to one to No. four sequence and is connected step by step；The No.1 top of oil-tank, which is provided with, to be drawn
Port；The bleed ports combine the connection of pressure maintaining valve gas outlet with unidirectional by pressurization air entraining pipe；The unidirectional combination pressure maintaining valve
Air inlet is connect by being pressurized tracheae with engine bleed mouth；The oil outlet of No. four fuel tanks is sequentially connected in series threeway by oil pipe
It is connect after connector and switch with the oil inlet end of engine oil pump.
2. the special-shaped distributed pressurization oil supply system of a kind of unmanned plane according to claim 1, it is characterized in that: the abnormal shape
The shape of fuel tank fits closely unmanned plane covering and housing construction shape.
3. the special-shaped distributed pressurization oil supply system of a kind of unmanned plane according to claim 1, it is characterized in that: each described
The flowline and weight connecting with oil outlet are provided in special-shaped fuel tank；The flowline is with certain elasticity；The weight is set
Set the low side in flowline；Flowline with weight can swing and will not bend in fuel tank, and motion range covers fuel tank
Interior major part space.
4. the special-shaped distributed pressurization oil supply system of a kind of unmanned plane according to claim 1, it is characterized in that: the No.1
The bottom both ends of fuel tank and No. three fuel tanks are provided with connection oil pipe.
5. the special-shaped distributed pressurization oil supply system of a kind of unmanned plane according to claim 1, it is characterized in that: described unidirectional
It combines pressure maintaining valve outlet side pressure value and is not more than 35Kpa.
6. the special-shaped distributed pressurization oil supply system of a kind of unmanned plane according to claim 1, it is characterized in that: the threeway
The first end of connector connects No. four fuel tank oil outlets, second end connection switch, and third terminates oil filling pipe；The oil filling pipe successively with
Gasoline pump and fuel reserve tank are connected step by step.
7. the special-shaped distributed pressurization oil supply system of a kind of unmanned plane according to claim 1, it is characterized in that: the No.1
The center of gravity rear and front end of unmanned plane is arranged in fuel tank and No. two fuel tanks；No. three fuel tanks and No. four fuel tanks are arranged in unmanned plane weight
Heart near zone.
8. the special-shaped distributed pressurization oil supply system of a kind of unmanned plane according to claim 1, it is characterized in that: described No. four
Top of oil-tank is provided with exhaust outlet, is connected with exhaust pipe on exhaust outlet, is generated in refueling process for excluding oil supply system
Bubble.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201811639474.5A CN109573071A (en) | 2018-12-29 | 2018-12-29 | A kind of special-shaped distributed pressurization oil supply system of unmanned plane |
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| CN201811639474.5A CN109573071A (en) | 2018-12-29 | 2018-12-29 | A kind of special-shaped distributed pressurization oil supply system of unmanned plane |
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| CN111520233A (en) * | 2020-06-02 | 2020-08-11 | 中国人民解放军总参谋部第六十研究所 | Aviation oil supply system and oil supply control method |
| CN112188396A (en) * | 2019-07-02 | 2021-01-05 | 中国空气动力研究与发展中心 | Energy-efficient-based flight path and power combined optimization method in unmanned aerial vehicle auxiliary communication network |
| CN113859555A (en) * | 2021-09-08 | 2021-12-31 | 北京航空航天大学 | A oil feeding system for long time of flight unmanned aerial vehicle |
| CN114228975A (en) * | 2022-01-20 | 2022-03-25 | 湖南航天环宇通信科技股份有限公司 | Multi-cabin integral oil tank of unmanned aerial vehicle |
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| CN113859555A (en) * | 2021-09-08 | 2021-12-31 | 北京航空航天大学 | A oil feeding system for long time of flight unmanned aerial vehicle |
| CN114228975A (en) * | 2022-01-20 | 2022-03-25 | 湖南航天环宇通信科技股份有限公司 | Multi-cabin integral oil tank of unmanned aerial vehicle |
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