CN214493352U - Unmanned aerial vehicle double-cavity oil-gas separator - Google Patents
Unmanned aerial vehicle double-cavity oil-gas separator Download PDFInfo
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- CN214493352U CN214493352U CN202022549754.6U CN202022549754U CN214493352U CN 214493352 U CN214493352 U CN 214493352U CN 202022549754 U CN202022549754 U CN 202022549754U CN 214493352 U CN214493352 U CN 214493352U
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Abstract
An outlet of an oil tank in a double-cavity fuel system of the unmanned aerial vehicle is communicated with an oil inlet at the upper end of the oil-gas separator through an oil pump, and an oil outlet at the lower end of the oil-gas separator is externally connected with an engine oil inlet through a one-way valve. An oil inlet and an air outlet are formed in the upper end cover of the oil-gas separator; an oil outlet is formed in the lower portion of the side wall of the oil-gas separator; and a liquid level sensor is arranged on the side wall plate of the upper cavity. The oil-gas separator is divided into an upper cavity and a lower cavity. The fuel system can not only meet the reliable fuel supply of the unmanned aerial vehicle during normal flight, but also adapt to the situation that the unmanned aerial vehicle supplies pure fuel for the engine stably and reliably under the large-maneuvering flight attitude, particularly during the dive flight and the pull-up re-flight, so that the normal work of the engine is ensured, and the influence of the severe shaking of the fuel liquid level on the fuel supply reliability at the oil outlet caused by adverse factors such as yaw, overload and gushing during the flight of the unmanned aerial vehicle can be effectively avoided.
Description
Technical Field
The invention relates to the field of fuel systems of unmanned aerial vehicles, in particular to a fuel system with a double-cavity structure, which is suitable for large-angle attitude dive flight of an unmanned aerial vehicle and can still reliably work after being pulled up.
Background
The fuel system of the unmanned aerial vehicle is used for storing fuel required by an airborne engine and continuously supplying fuel with specified pressure and flow to the engine according to a certain sequence under all flight states and working conditions allowed by the unmanned aerial vehicle. With the rapid development of the unmanned aerial vehicle industry, unmanned aerial vehicles have been widely used in military fields such as technical reconnaissance, patrol surveillance, target attack and the like, and civil fields such as geological mapping, mineral exploration and the like. To unmanned aerial vehicle for most investigation, patrol, survey and drawing, exploration, do not need very strong mobility, also do not have flight states such as wide-angle dive, consequently, this type of unmanned aerial vehicle's fuel oil system adopts the conventional atmospheric hard soft oil tank that leads to mostly, and the during operation fires soft oil tank and directly communicates with the atmosphere, supplies oil through soft oil tank bottom fuel feeding hole. To the unmanned aerial vehicle that possesses very strong mobility requirement such as all kinds of target attack type unmanned aerial vehicle, anti-radiation unmanned aerial vehicle, its fuel oil system just needs carry out the pertinence design according to the mission requirement of fighting of difference, guarantees that the aircraft when diving flight, does not take place oil spilling or the smooth problem of fuel feeding. At present, disclose an unmanned aerial vehicle oil feeding system in utility model patent that publication number is CN205366088U, its soft oil tank top is equipped with air inlet and oil inlet, and the soft oil tank passes through oil pipe and carburetor intercommunication, and the oil pipe end of arranging in the soft oil tank is equipped with the oil hammer. The utility model discloses an advantage lies in, drives the slider motion through promoting the piston rod to the realization reduces the purpose of fuel storage space in the soft oil tank, makes the oil hammer soak in the fuel all the time, guarantees the sustainable stable fuel feeding to the carburetor of soft oil tank, but this fuel oil system can not satisfy the big overload of unmanned aerial vehicle and dive the flight requirement.
An external pressurization oil supply system is disclosed in a utility model patent with the publication number of CN209719944U, and the utility model patent adopts an auxiliary soft oil tank to externally pressurize a main soft oil tank, so as to realize negative pressure oil supply of the main soft oil tank and ensure high altitude oil supply and large maneuvering flight oil supply of an airplane; however, this method requires a large space and weight requirement and requires the introduction of the engine compressed gas, which is not possible with piston or rotor engines.
The propeller type unmanned aerial vehicle on the current market mostly adopts conventional piston engine or rotor engine, and volatile gasoline or aviation kerosene are selected for use to the fuel, and the current conventional hard formula leads to atmosphere fuel oil system and can not satisfy this type of unmanned aerial vehicle wide-angle dive flight.
Disclosure of Invention
In order to overcome the defect that a fuel system in the prior art cannot meet the requirement of normal oil supply during large-angle dive flight of an unmanned aerial vehicle, the invention provides a double-cavity oil-gas separator of the unmanned aerial vehicle.
The double-cavity oil-gas separator of the unmanned aerial vehicle is characterized by comprising an oil-gas separator body and a liquid level sensor; the oil-gas separator body is divided into an upper cavity and a lower cavity; the liquid level sensor is arranged on the side wall plate of the upper cavity; the lower panel of the upper cavity is an inclined plane, the upper panel of the lower cavity is also an inclined plane, a V-shaped opening is formed between the lower panel of the upper cavity and the upper panel of the lower cavity, the upper cavity is communicated with the lower cavity at the root of the V-shaped opening, the root of the V-shaped opening is positioned on one side of the machine head, and the mouth of the V-shaped opening is positioned on one side of the machine tail. The volume of the upper cavity is 1000ml, and the volume of the lower cavity is 500 ml.
An included angle a is formed between the lower panel of the upper cavity and the horizontal plane; the included angle between the upper panel of the lower cavity and the horizontal plane is b; the included angle between the lower panel of the lower cavity and the horizontal plane is c; 18-22 degrees for a, 0-5 degrees for b, and 18-22 degrees for c; the distance from one side wall plate of the head of the oil-gas separator to one side wall plate of the tail of the oil-gas separator is L; the horizontal distance from the bottom of the V-shaped opening to the opening part of the V-shaped opening is L1; l1: l is 0.65 to 0.9.
An oil inlet and an air outlet are formed in the upper end cover of the oil-gas separator; an oil outlet is formed in the lower portion of the side wall of the oil-gas separator; and a liquid level sensor is arranged on the side wall plate of the upper cavity.
An oil inlet at the upper end of the oil-gas separator body is communicated with an outlet of a soft oil tank in an unmanned aerial vehicle fuel system through a pipeline, and an oil pump is connected to the pipeline; an oil outlet at the lower end of the oil-gas separator body is externally connected with an oil inlet of an engine through a pipeline, and the pipeline is connected with a one-way valve; the exhaust port at the upper end of the oil-gas separator body is communicated with the outside atmosphere through a pipeline, and an exhaust electromagnetic valve is connected to the pipeline. The distance between the center of the exhaust port and the outer surface of the wall plate at one side of the tail of the oil-gas separator is 10 mm; the distance between the center of the oil outlet and the upper surface of the bottom plate of the oil-gas separator is 12 mm; the distance from the center of the liquid level sensor to the outer surface of a side wall plate of the tail of the oil-gas separator is 12mm, and the distance from the center of the liquid level sensor to the upper surface of the oil-gas separator is 10 mm.
And the outlet of the one-way valve is communicated with the oil inlet of the engine.
The invention is suitable for the conventional unmanned aerial vehicle with a smaller pitch angle and is also suitable for the attacking unmanned aerial vehicle with the diving flight requirement.
By adopting the technical scheme of the invention, when the plane normally flies, the oil pump sucks the fuel oil in the soft oil tank into the upper cavity of the oil-gas separator through the oil inlet. The lower surface of the upper cavity body is an inclined plane, and oil can further flow into the lower cavity body. The inclination angle of the inclined plane is larger than the maximum pitch angle of the plane during normal level flight and climbing. The upper surface of the lower cavity is also an inclined surface, and gas can further reach the upper cavity; the inclination angle of the inclined plane is smaller than the minimum pitch angle when the airplane normally flies flatly and slides downwards.
In the invention, whether gas exists in the upper cavity of the oil-gas separator is sensed through the liquid level sensor: when gas exists, the exhaust electromagnetic valve is opened, the gas in the upper cavity of the oil-gas separator is exhausted through the exhaust port until the fuel liquid level is higher than the liquid level sensor, and the exhaust electromagnetic valve is closed. When fuel oil in the lower cavity of the oil-gas separator generates gas due to vibration or volatilization, the gas floats to the upper surface of the upper cavity due to the action of gravity.
Only fuel oil in the lower cavity of the oil-gas separator is led to the engine through the oil outlet. When the aircraft flies in a large-angle dive mode, gas in the soft oil tank enters an upper cavity of the oil-gas separator; the oil-gas separator utilizes the self structural characteristics and the exhaust function to block the entering gas in the upper cavity and continuously exhaust the gas through the exhaust port; when the gas is enough and can not be discharged in time, the upper cavity is gradually filled with gas.
When the liquid level in the upper cavity is lower than the communicating opening of the upper cavity and the lower cavity, gas enters the lower cavity. The distance between a wall plate at one side of the machine head of the oil-gas separator and a wall plate at one side of the machine tail is designed to be L; the horizontal distance from the bottom of the V-shaped opening to the opening part of the V-shaped opening is L1; when L1: and when L is 0.65-0.9, the utilization rate of the fuel oil in the upper cavity can be effectively improved.
When the aircraft is pulled up after the aircraft dives, only fuel oil in the soft oil tank enters the upper cavity of the oil-gas separator.
The fuel supply system can meet the reliable fuel supply of the unmanned aerial vehicle during normal flight, and can also adapt to the condition that the unmanned aerial vehicle supplies pure fuel for the engine stably and reliably under the condition of large-maneuvering flight attitude, particularly during dive flight and pull-up re-flight, thereby ensuring the normal work of the engine.
Compared with the prior art, the invention has the beneficial effects that:
1. the double-cavity fuel oil system provided by the invention mainly utilizes the structural characteristics of the upper cavity and the lower cavity of the oil-gas separator, so that fuel oil led to an engine is subjected to oil-gas separation, liquid fuel oil is supplied to the engine, and gas is discharged out of the engine, and the fuel oil system can supply fuel oil with specified flow uninterruptedly when an unmanned aerial vehicle is in large-angle dive and is pulled up for re-flight.
2. The double-cavity oil-gas separator provided by the invention keeps the liquid level of the fuel in the upper cavity, and can effectively avoid the influence of severe shaking of the liquid level of the fuel on the reliability of oil supply at an oil outlet caused by adverse factors such as yaw, overload, sudden wind and the like when an unmanned aerial vehicle flies.
3. The included angle a between the lower panel of the upper cavity and the horizontal plane is theta1+2 ° and the angle b between the upper panel of the lower cavity and the horizontal plane is θ2-2 ° and the angle c ═ θ between the lower face plate of the lower cavity and the horizontal plane1+2 deg., where theta1Maximum attitude angle theta for unmanned aerial vehicle climbing2The minimum attitude angle when the unmanned aerial vehicle glides. Through the angle of each cavity panel in the reasonable double-cavity oil-gas separator that sets up, when making unmanned aerial vehicle fly at the tie, climb, gliding etc. flight gesture, gas can not be preserved in the oil-gas separator yet, can not form the dead oil region yet, has guaranteed that fuel oil system stabilizes the fuel feeding for a long time.
4. The core component of the invention is the oil-gas separator, and the component has simple structure, convenient maintenance and high reliability.
In order to verify the effect of the invention, the technical scheme of the invention is experimentally verified. In the experiment, according to the flight requirement of the unmanned aerial vehicle, the maximum climbing attitude angle of the airplane is 18 degrees, the minimum gliding attitude angle is-1 degrees, the diving time T of the airplane is less than or equal to 120s, and the maximum oil consumption flow Q of the engine1The physical parameters are designed and obtained as follows: go up cavity 11 volume 1000ml, cavity 12 volume 500ml down, the contained angle a between panel and the horizontal plane down in the middle and upper cavity of last cavity 11 is 20, and the contained angle b between lower cavity upper panel and the horizontal plane is-3 in the lower cavity 12, and contained angle c between panel and the horizontal plane down is 20 down the cavity, L1: l is 0.85, and the opening pressure of the one-way valve is18 KPa. When the flat flight test is carried out, the fuel system can stably work for a long time, and the phenomenon of unsmooth fuel supply or interruption is avoided; when a dive flight test is carried out, the dive angle is in a-90-degree state, at the moment, the fuel system can dive and fly for at least 360s, the fuel system is pulled up to fly again after dive flight, and the phenomenon of unsmooth fuel supply or interruption of fuel supply of the fuel system is avoided.
Drawings
FIG. 1 is a schematic illustration of the fuel system of the present invention;
FIG. 2 is a schematic structural diagram of the dual-cavity oil-gas separator of the present invention.
In the figure: 1. a soft oil tank; 2. an oil pump; 3. an exhaust solenoid valve; 4. a one-way valve; 5. an oil-gas separator; 6. an oil-gas separator body; 7. a liquid level sensor; 8. an oil inlet; 9. an oil outlet; 10. an exhaust port; 11. an upper cavity; 12. and a lower cavity.
Detailed Description
The oil-gas separator that can adapt to unmanned aerial vehicle dive flight that provides in this embodiment.
The oil-gas separator 5 comprises an oil-gas separator body 6 and a liquid level sensor 7. The oil-gas separator body 6 is divided into an upper cavity 11 and a lower cavity 12. The liquid level sensor 7 is installed on the side wall plate of the upper cavity 11.
The lower panel of the upper cavity 11 is an inclined plane, and the upper panel of the lower cavity 12 is also an inclined plane, so that a V-shaped opening is formed between the lower panel of the upper cavity and the upper panel of the lower cavity; the root of the V-shaped opening is positioned on one side of the machine head, the mouth of the V-shaped opening is positioned on one side of the machine tail, and the upper cavity is communicated with the lower cavity at the root of the V-shaped opening. An included angle a is formed between the lower panel of the upper cavity and the horizontal plane; the included angle between the upper panel of the lower cavity and the horizontal plane is b; the included angle between the lower panel of the lower cavity and the horizontal plane is c; 18-22 degrees for a, 0-5 degrees for b, and 18-22 degrees for c. The distance between a wall plate at one side of the machine head and a wall plate at one side of the machine tail of the oil-gas separator body 6 is L; the horizontal distance from the bottom of the V-shaped opening to the opening part of the V-shaped opening is L1; l1: l is 0.65 to 0.9.
An oil inlet 8 and an air outlet 10 are formed in the upper end cover of the oil-gas separator body 6; the distance between the center of the exhaust port 10 and the outer surface of the wall plate at one side of the tail of the oil-gas separator body 6 is 10 mm. An oil outlet 9 is formed in the lower portion of the side wall of the oil-gas separator body, and the distance between the center of the oil outlet and the upper surface of the bottom plate of the oil-gas separator body is 12 mm. The liquid level sensor 7 is arranged on the side wall plate of the upper cavity 11, the distance from the center of the liquid level sensor to the outer surface of the wall plate at the tail side of the oil-gas separator body 6 is 12mm, and the distance from the center of the liquid level sensor to the upper surface of the oil-gas separator body 6 is 10 mm.
In this embodiment, the volume of the upper cavity 11 is 1000ml, and the volume of the lower cavity 12 is 500 ml; the included angle a between the lower panel of the upper cavity body and the horizontal plane is 20 degrees; the included angle b between the upper panel of the lower cavity and the horizontal plane is-3 degrees; the included angle c between the lower panel of the lower cavity and the horizontal plane is 20 degrees; the distance between a wall plate at one side of the machine head and a wall plate at one side of the machine tail of the oil-gas separator body 6 is L; the horizontal distance from the bottom of the V-shaped opening to the opening part of the V-shaped opening is L1; the L1: l is 0.85. In order to ensure that the oil-gas separator can smoothly exhaust, the opening pressure of the check valve 4 is 18 KPa.
When the fuel tank is used, an oil inlet at the upper end of the oil-gas separator body is communicated with an outlet of a soft fuel tank 1 in an unmanned aerial vehicle fuel system through a pipeline; an oil pump 2 is connected to the pipe. An oil outlet 9 at the lower end of the oil-gas separator body is externally connected with an oil inlet of an engine through a pipeline; a check valve 4 is connected to the pipe. An exhaust port 10 at the upper end of the oil-gas separator body is communicated with the outside atmosphere through a pipeline, and exhausts gas through an exhaust solenoid valve 3 connected to the pipeline. In this embodiment, the inner diameter of the oil pipe is 8mm, and the inner diameter of the air pipe is 6 mm.
The soft oil tank 1, the oil pump 2, the exhaust electromagnetic valve 3 and the one-way valve 4 are all the prior art.
Claims (8)
1. The double-cavity oil-gas separator of the unmanned aerial vehicle is characterized by comprising an oil-gas separator body and a liquid level sensor; the oil-gas separator body is divided into an upper cavity and a lower cavity; the liquid level sensor is arranged on the side wall plate of the upper cavity; the lower panel of the upper cavity is an inclined plane, the upper panel of the lower cavity is also an inclined plane, a V-shaped opening is formed between the lower panel of the upper cavity and the upper panel of the lower cavity, and the upper cavity is communicated with the lower cavity at the root of the V-shaped opening.
2. The unmanned aerial vehicle dual-cavity oil-gas separator as claimed in claim 1, wherein the volume of the upper cavity is 1000ml, and the volume of the lower cavity is 500 ml.
3. The unmanned aerial vehicle dual-cavity oil-gas separator as claimed in claim 1, wherein an included angle between a lower panel of the upper cavity and a horizontal plane is a; the included angle between the upper panel of the lower cavity and the horizontal plane is b; the included angle between the lower panel of the lower cavity and the horizontal plane is c; 18-22 degrees for a, 0-5 degrees for b, and 18-22 degrees for c; the distance from one side wall plate of the head of the oil-gas separator to one side wall plate of the tail of the oil-gas separator is L; the horizontal distance from the bottom of the V-shaped opening to the opening part of the V-shaped opening is L1; l1: l is 0.65 to 0.9.
4. The dual-cavity oil-gas separator for the unmanned aerial vehicle as claimed in claim 1, wherein the root of the V-shaped opening is located on the nose side, and the mouth of the V-shaped opening is located on the tail side.
5. The unmanned aerial vehicle dual-cavity oil-gas separator as claimed in claim 1, wherein an oil inlet and an air outlet are formed in an upper end cover of the oil-gas separator; an oil outlet is formed in the lower portion of the side wall of the oil-gas separator; and a liquid level sensor is arranged on the side wall plate of the upper cavity.
6. The unmanned aerial vehicle dual-cavity oil-gas separator as claimed in claim 1, wherein an oil inlet at the upper end of the oil-gas separator body is communicated with an outlet of a soft oil tank in an unmanned aerial vehicle fuel system through a pipeline, and an oil pump is connected to the pipeline; an oil outlet at the lower end of the oil-gas separator body is externally connected with an oil inlet of an engine through a pipeline, and the pipeline is connected with a one-way valve; the exhaust port at the upper end of the oil-gas separator body is communicated with the outside atmosphere through a pipeline, and an exhaust electromagnetic valve is connected to the pipeline.
7. The unmanned aerial vehicle dual-cavity oil-gas separator as claimed in claim 6, wherein the distance between the center of the exhaust port and the outer surface of the tail side wall plate of the oil-gas separator is 10 mm; the distance between the center of the oil outlet and the upper surface of the bottom plate of the oil-gas separator is 12 mm; the distance from the center of the liquid level sensor to the outer surface of a side wall plate of the tail of the oil-gas separator is 12mm, and the distance from the center of the liquid level sensor to the upper surface of the oil-gas separator is 10 mm.
8. The unmanned aerial vehicle dual-cavity oil and gas separator as claimed in claim 6, wherein an outlet of the check valve is communicated with the engine oil inlet.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202022549754.6U CN214493352U (en) | 2020-11-06 | 2020-11-06 | Unmanned aerial vehicle double-cavity oil-gas separator |
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| CN202022549754.6U CN214493352U (en) | 2020-11-06 | 2020-11-06 | Unmanned aerial vehicle double-cavity oil-gas separator |
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| CN214493352U true CN214493352U (en) | 2021-10-26 |
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| CN202022549754.6U Active CN214493352U (en) | 2020-11-06 | 2020-11-06 | Unmanned aerial vehicle double-cavity oil-gas separator |
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