CN112644721A - Aircraft oil supply and delivery system and control method thereof - Google Patents
Aircraft oil supply and delivery system and control method thereof Download PDFInfo
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- CN112644721A CN112644721A CN202011538896.0A CN202011538896A CN112644721A CN 112644721 A CN112644721 A CN 112644721A CN 202011538896 A CN202011538896 A CN 202011538896A CN 112644721 A CN112644721 A CN 112644721A
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- oil
- valve
- tank
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- booster pump
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D37/00—Arrangements in connection with fuel supply for power plant
- B64D37/02—Tanks
- B64D37/14—Filling or emptying
- B64D37/16—Filling systems
- B64D37/18—Conditioning fuel during filling
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS 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
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Abstract
The invention discloses an aircraft oil supply and delivery system and a control method thereof, relates to the technical field of aircraft oil supply and delivery, and particularly relates to an aircraft oil supply and delivery system and a control method thereof, wherein the aircraft oil supply and delivery system comprises: a buffer tank unit; the buffer tank is divided into two subareas, and the two subareas are used for supplying oil respectively, so that the redundancy design is safer; the two partitions are supplied with oil through two independent booster pumps and two independent check valves respectively, and the two partitions are not interfered with each other. The invention is provided with two oil tanks which are used for storing fuel oil and are mutually backup, four modes of first oil tank and first region oil supply, first oil tank and second region oil supply, second oil tank and first region oil supply, second oil tank and second region oil supply can be formed through the first valve, the second valve, the third valve, the fourth valve and the four-way valve which are communicated with the oil tanks, and the oil supply safety is greatly improved. The invention also provides a control method of the aircraft oil supply and delivery system, different solutions are provided for different working conditions, and the problem of unsafe flight oil supply under most conditions is solved.
Description
Technical Field
The invention relates to the technical field of airplane oil supply and delivery, in particular to an airplane oil supply and delivery system and a control method thereof.
Background
At present, a small airplane, particularly an unmanned aerial vehicle, generally uses an aviation piston engine, and both uses a mechanical carburetor to control and adjust engine fuel supply, and the carburetor oil supply type aviation piston engine has simple requirements on an unmanned aerial vehicle fuel system and has no special requirements on oil supply pressure and airplane zero and load state oil supply.
Along with the continuous improvement to unmanned aerial vehicle performance demand, the aviation piston engine that its adopted changes into and adopts turboprop engine (hereinafter referred to as turboprop engine for short), and turboprop engine is very sensitive to fuel supply pressure, and fuel supply pressure fluctuation can make the engine work unusual, leads to the engine to park even, seriously influences unmanned aerial vehicle flight safety. And the aircraft is under zero, the load state, and ordinary fuel oil supply and delivery system can not effectively supply oil, will directly lead to the engine to park, influences unmanned aerial vehicle flight safety.
The invention discloses an authorized publication No. CN 104494835B, which is named as an invention patent of a symmetric oil tank balanced oil transportation system, and provides a symmetric oil tank balanced oil transportation system, which comprises a left wing oil tank, a right wing oil tank, an oil transportation selection switch, a fuel oil control box, an oil transportation selection valve and an oil transportation pipeline; the left wing oil tank and the right wing oil tank are connected through an oil conveying pipeline, an oil conveying selection valve is arranged on the oil conveying pipeline and is respectively connected with the fuel control box and the engine, the left oil mass sensor and the right oil mass sensor are connected with the fuel control box, and meanwhile, the oil conveying selection switch is connected with the oil conveying selection valve. According to the invention, the electric control oil delivery selection valve is combined with the manual control oil delivery selection switch, so that the alternate oil delivery of the left wing oil tank and the right wing oil tank is accurately realized, the phenomenon of uneven oil delivery easily occurring in the oil delivery process of symmetrical oil tanks is avoided, the stability operating characteristic of the airplane is effectively improved, and the service life of the airplane is prolonged.
According to the invention, the oil is directly supplied by the wing oil tank, so that the consideration on the oil supply continuity is less, and the possibility of instantly stopping oil supply exists.
How to provide one kind and possess real time monitoring and display system state, and possess the ability of the multiple problem of solution system, satisfy aircraft zero in the certain time, load condition flight, and supply the fuel supply and delivery system of unmanned aerial vehicle of the redundant backup of oil delivery, be used for guaranteeing that unmanned aerial vehicle fuel supply and delivery system can be for the turboprop engine more reliable and stable required fuel that provides, ensure unmanned aerial vehicle flight safety, be one difficult problem of pendulum in the field technical staff.
Disclosure of Invention
The invention provides an aircraft oil supply and delivery system and a control method thereof, which are used for solving the problem that continuous oil supply and delivery for an engine under a zero-load state cannot be guaranteed in the prior art.
The invention adopts the following technical scheme:
an aircraft oil supply and delivery system comprising: a buffer tank unit;
the buffer tank unit includes: the device comprises a buffer tank, a first booster pump, a second booster pump, a first one-way valve, a second one-way valve and a first tee joint;
the buffer box is a sealed container and comprises a first buffer box area and a second buffer box area, and the first buffer box area is not communicated with the second buffer box area; the first district of baffle-box is equipped with: the first oil inlet, the first air vent and the first oil outlet; the buffer box second zone is provided with: the second oil inlet, the second vent and the second oil outlet;
the oil inlet of the first booster pump is communicated with the first oil outlet, and the oil outlet of the first booster pump is communicated with the first port of the first one-way valve;
the oil inlet of the second booster pump is communicated with the second oil outlet, and the oil outlet of the second booster pump is communicated with the first port of the second one-way valve;
the second port of the first one-way valve is communicated with the first port of the first tee joint, and the second port of the second one-way valve is communicated with the second port of the first tee joint;
further, still include: a first tank unit and a second tank unit; the oil supply unit further includes: a third valve and a fourth valve;
the first tank unit includes: the first oil tank, the first valve and the four-way valve;
the second tank unit includes: a second tank and a second valve;
first oil tank and the second oil tank is sealed container, first oil tank is equipped with: the first oil filling port, the third air vent and the third oil outlet; the second oil tank is provided with: a second oil filling port, a fourth air vent and a fourth oil outlet;
the first valve, the second valve, the third valve and the fourth valve are all two-position two-way valves, a first end of the first valve is communicated with the third oil outlet, and a second end of the first valve is communicated with the four-way first port; the first end of the second valve is communicated with the fourth oil outlet, and the second end of the second valve is communicated with the four-way second port; the first end of the third valve is communicated with a third port of the four-way valve, and the second end of the third valve is communicated with the first oil inlet; the first end of the fourth valve is communicated with a fourth port of the four-way valve, and the second end of the third valve is communicated with the second oil inlet.
Further, still include: a control unit; the control unit includes: the oil quantity sensor comprises a controller, a first oil quantity sensor, a second oil quantity sensor, a flow sensor and a pressure sensor;
the first oil quantity sensor is used for acquiring an oil quantity signal of a first area of the buffer tank; the second oil quantity sensor is used for acquiring an oil quantity signal of a second area of the buffer tank; the flow sensor is used for acquiring a flow signal of a third port of the first tee joint, and the pressure sensor is used for acquiring a pressure signal of the third port of the first tee joint;
the controller selects the first booster pump or the second booster pump to start according to an oil mass signal of a first area of the buffer tank, an oil mass signal of a second area of the buffer tank, a flow signal of a third port of the first tee joint and a pressure signal of the third port of the first tee joint;
the first oil mass sensor, the second oil mass sensor, the flow sensor, the pressure sensor, the first booster pump and the second booster pump are respectively electrically connected with the controller.
Further, the control unit further includes: the oil quantity sensor is used for acquiring an oil quantity signal of the first oil tank, and the fourth oil quantity sensor is used for acquiring an oil quantity signal of the second oil tank;
the controller is further used for controlling the first valve to be communicated or the second valve to be communicated according to the oil mass signal of the first oil tank, the oil mass signal of the second oil tank, the oil mass signal of the first area of the buffer tank, the flow signal of the third port of the first tee joint and the pressure signal of the third port of the first tee joint, and the controller is further used for controlling the third valve to be communicated or the fourth valve to be communicated according to the oil mass signal of the first oil tank, the oil mass signal of the second oil tank, the oil mass signal of the first area of the buffer tank, the oil mass signal of the second area of the buffer tank, the flow signal of the third port of the first tee joint and the pressure signal of the third port of the first tee joint;
the third oil amount sensor, the fourth oil amount sensor, the first valve, the second valve, the third valve, and the fourth valve are electrically connected to the controller, respectively.
Furthermore, the first oil tank is also provided with a fifth oil outlet, and the second oil tank is also provided with a sixth oil outlet;
the first oil tank unit further comprises a second tee joint, and the second oil tank unit further comprises a third tee joint;
a first end of the second tee joint is communicated with the third oil outlet, a second end of the second tee joint is communicated with the fifth oil outlet, and a third end of the second tee joint is communicated with a first end of the first valve;
and a first end of a third tee joint is communicated with the fourth oil outlet, a second end of the third tee joint is communicated with the sixth oil outlet, and a third end of the third tee joint is communicated with a first end of the second valve.
Further, the buffer tank is located below the first oil tank and the second oil tank, and the relative positions satisfy:
h represents the vertical height between the third and fourth outlets and the first or second outlet;
q represents the engine maximum flow demand;
l represents the nominal length of the oil supply line;
d represents the nominal diameter of the oil supply line;
g represents the gravitational acceleration;
a represents the maximum acceleration of the aircraft;
λ represents an on-way drag coefficient;
ζ represents the total local drag coefficient;
alpha represents the maximum elevation angle of the aircraft.
Further, the buffer tank unit further includes: first float switch and second float switch, first oil tank unit still includes: a third float switch, the second tank unit further comprising: a fourth float switch;
first float switch sets up first air vent, second float switch sets up the second air vent, third float switch sets up the third air vent, fourth float switch sets up the fourth air vent.
Further, the buffer box unit further comprises a turn-off switch, the turn-off switch is communicated with a third end of the first tee joint, and the turn-off switch is electrically connected with the controller.
An aircraft oil supply and delivery system control method comprises the following steps:
selecting an oil tank and a buffer tank partition;
opening a valve and a booster pump which are matched with the selected oil tank and the buffer tank in partition;
judging whether the starting requirement of the engine is met or not according to the pressure output by the booster pump, and if the starting requirement is not met, adjusting the pressure output by the booster pump until the preset condition of the output pressure is met;
judging the gravity center according to the two oil tank oil quantity signals, and switching an oil supply tank through opening and closing a valve if the gravity center exceeds a preset condition; judging whether the output of the working booster pump is normal or not according to the pressure output by the booster pump and the flow output by the booster pump, and switching the buffer tank to divide the buffer tank into sections by switching the booster pump and the opening and closing of the valve if the output of the working booster pump exceeds a preset flow condition;
if the oil quantity of one buffer tank partition is lower than the preset condition of the oil quantity lowest position, and the partition is lower than the preset condition of the oil quantity lowest position after a time delay, the buffer tank partition is switched by switching the opening and closing of a booster pump and a valve, and an oil supply tank is unchanged; after a period of time delay, if the switched buffer tank subarea is lower than the preset lowest position again, the oil supply tank is switched by opening and closing the valve, and after a period of time delay, if the switched buffer tank subarea is not lower than the preset lowest position again, the original buffer tank subarea is switched by switching the opening and closing of the booster pump and the valve;
and judging whether the oil supply and delivery system threatens the flight safety or not according to the data of the flight control computer, if so, closing the turn-off switch, and replying to the flight control computer that the turn-off switch is closed.
The invention has the following positive effects:
the device is provided with the buffer tank, the buffer tank is divided into two subareas, the two subareas are used for supplying oil respectively and are backup with each other, and the redundancy design is safer; the two partitions are supplied with oil through two independent booster pumps and two independent check valves respectively, and the two partitions are not interfered with each other. The invention is provided with two oil tanks which are used for storing fuel oil and are mutually backup, four modes of first oil tank and first region oil supply, first oil tank and second region oil supply, second oil tank and first region oil supply, second oil tank and second region oil supply can be formed through the first valve, the second valve, the third valve, the fourth valve and the four-way valve which are communicated with the oil tanks, and the oil supply safety is greatly improved.
The oil supply and delivery system is provided with the controller and the sensor for collecting the oil level signal, the pressure signal of the output pressure of the booster pump and the output flow signal of the booster pump, the controller integrates the signals to control the pump and the valve to switch the oil supply loop according to a preset program, the personnel watching is not needed, the loop is switched quickly and timely, and the continuity and the stability of the oil supply are ensured.
The oil supply and delivery system is provided with the third oil level sensor and the fourth oil level sensor, the oil level signals of the first oil tank and the second oil tank are collected through the two sensors, when the oil level of the oil tank is abnormal, the controller switches the oil supply loop by controlling the start and stop of the first valve, the second valve, the third valve, the first booster pump and the second booster pump, the controller switches the signals quickly and timely, and the continuity of oil supply is guaranteed.
The first oil tank and the second oil tank of the oil supply and delivery system are respectively provided with two oil filling ports, and the two oil filling ports are respectively communicated with the electromagnetic valve through a tee joint. In the flying process of the airplane, the posture is constantly changed, and the height of an oil outlet of an oil tank relative to a buffer tank is constantly changed, so that the continuity of oil supply is influenced. The first oil tank and the second oil tank of the oil supply and delivery system are provided with two oil filling ports which are respectively arranged at two different positions, so that one port can be used for supplying oil instead of the other port, and the safety of oil supply of the oil tanks is improved.
According to the oil supply and delivery system, the float switch is arranged at the air vent of the oil tank and the buffer tank in a partition manner, and the float switch closes the air vent when the attitude of the airplane changes so as to cause the liquid level to approach the air vent, so that the fuel is prevented from overflowing from the air vent, and the safety of fuel supply is improved.
The invention also provides a position relation formula of the buffer tank relative to the oil tank, and the formula is calculated by combining the actual condition of the aircraft oil supply and delivery system according to the Bernoulli fluid mechanics principle. If the position of the buffer tank meets the requirement of a formula, gravity oil supply of the main oil tank to the buffer tank can be realized. The installation of oil supply equipment of a main oil tank can be reduced, the repeated design of an oil supply and delivery system when the piston engine supplied with oil by gravity is replaced with the turboprop engine is avoided, and the replacement cost is reduced. And the use of the buffer tank can greatly shorten the distance between the oil tank and the engine, increase the extra fuel quantity, improve the safety of the oil supply and delivery system of the airplane, and play a certain role in achieving the integral balance of the airplane.
The oil supply and delivery system is also provided with a turn-off switch, the turn-off switch is arranged at the tail end of the oil supply loop and used for turning off the oil supply output under the emergency condition, the turn-off switch is controlled by a controller, and the controller receives external input under the emergency condition.
A control method for an aircraft oil supply and delivery system aims at different working conditions, and for example, when the integral gravity center is unbalanced due to the oil quantity of an oil tank, the gravity center of an aircraft is adjusted by switching an oil supply loop. When output flow of the booster pump exceeds a preset condition, the buffer tank partitions are switched, when the buffer tank partitions are lower than a preset condition of an oil level, the oil tank and the buffer tank are switched to solve the problem that the oil level of the buffer tank partitions is too low, the problem that flying oil supply is unsafe under most conditions can be solved through the scheme, and a reliable solution is provided.
Drawings
FIG. 1 is a schematic diagram of an aircraft fuel supply and delivery system according to an embodiment of the present invention;
FIG. 2 is a functional block diagram of a control unit according to an embodiment of the present invention;
fig. 3 is a flowchart of a control method of an aircraft fuel supply and delivery system according to an embodiment of the invention.
In the figure:
1 a first booster pump;
2 a second booster pump;
3 a first one-way valve;
4 a second one-way valve;
5, a first tee joint;
6 a first oil tank;
7 a first valve;
8, four-way connection;
9 a second oil tank;
10 a second valve;
11 a third valve;
12 a fourth valve;
13 a second tee;
14 a third tee;
15 a first float switch;
16 a second float switch;
17 a third float switch;
18 a fourth float switch;
the switch is turned off 19.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in further detail below with reference to the accompanying drawings and embodiments. It should be understood that the detailed description and specific examples, while indicating the invention, are intended for purposes of illustration only and are not intended to limit the scope of the invention.
As shown in fig. 1-3, an aircraft fuel supply and delivery system includes: a buffer tank unit;
the buffer tank unit includes: the device comprises a buffer tank, a first booster pump 1, a second booster pump 2, a first one-way valve 3, a second one-way valve 4 and a first tee joint 5;
the buffer box is a sealed container and comprises a first buffer box area and a second buffer box area, and the first buffer box area is not communicated with the second buffer box area; the first district of baffle-box is equipped with: the first oil inlet, the first air vent and the first oil outlet; the buffer box second zone is provided with: the second oil inlet, the second vent and the second oil outlet;
an oil inlet of the first booster pump 1 is communicated with the first oil outlet, and an oil outlet of the first booster pump 1 is communicated with a first port of the first one-way valve 3;
an oil inlet of the second booster pump 2 is communicated with the second oil outlet, and an oil outlet of the second booster pump 2 is communicated with a first port of the second one-way valve 4;
the second port of the first one-way valve 3 is communicated with the first port of the first tee joint 5, and the second port of the second one-way valve 4 is communicated with the second port of the first tee joint 5;
further, still include: a first tank unit and a second tank unit; the oil supply unit further includes: a third valve 11 and a fourth valve 12;
the first tank unit includes: a first oil tank 6, a first valve 7 and a four-way valve 8;
the second tank unit includes: a second tank 9 and a second valve 10;
the first valve 7, the second valve 10, the third valve 11 and the fourth valve 12 are all two-position two-way valves, a first end of the first valve 7 is communicated with the third oil outlet, and a second end of the first valve 7 is communicated with a first port of the four-way valve 8; a first end of the second valve 10 is communicated with the fourth oil outlet, and a second end of the second valve 10 is communicated with a second port of the four-way valve 8; a first end of the third valve 11 is communicated with a third port of the four-way valve 8, and a second end of the third valve 11 is communicated with the first oil inlet; and a first end of the fourth valve 12 is communicated with a fourth port of the four-way valve 8, and a second end of the third valve 11 is communicated with the second oil inlet.
More specifically, the surge tank is interim batch oil tank, includes two buffer tank subregion that do not communicate with each other: a first buffer tank zone and a second buffer tank zone. The partition board is arranged in the box body, the box body is divided into two parts, the two parts are identical in structure and are respectively provided with a vent hole, an oil filling port and an oil outlet, the vent hole is used for communicating a subarea with the external atmosphere, obvious negative pressure or positive pressure cannot be generated in the subarea during operation, the oil filling port is a port for flowing in fuel oil, the fuel oil enters from the vent hole, the oil outlet is a port for supplying oil to the subarea outwards, and the oil outlet is provided with a one-way valve which is used for opening the valve when the subarea supplies oil to the outside and closing the valve when the subarea.
In a typical application, during normal operation, the first booster pump 1 is started, the first area is filled with oil from the oil filling port, the oil is discharged from the oil outlet, and the first check valve 3 is opened to supply oil from the first area. The second booster pump 2 does not work, neither oil nor oil is taken out of the second area, and the second check valve 4 is closed.
When the first area is abnormal, if the pressure of the first booster pump 1 is insufficient, the first booster pump 1 stops working, the first one-way valve 3 is closed, the second booster pump 2 is started, the oil is fed into the oil filling port of the second area, the oil is discharged from the oil outlet, and the oil is converted into the oil supply of the second area.
The oil storage tank that provides continuous fuel feeding for the baffle-box is first oil tank 6 and second oil tank 9, and first oil tank 6 is the same with 9 structures of second oil tank, all is equipped with blow vent and oil-out, and the oil-out is equipped with two through-valve control oil tank oil outlets. The four-way valve 8 is used for connecting each branch and is respectively connected with a first valve 7, a second valve 10, a third valve 11 and a fourth valve 12, and the third valve 11 and the fourth valve 12 are respectively used for controlling fuel from the first fuel tank 6 to enter a first area or a second area of the buffer tank.
In a typical application, during normal operation, the first booster pump 1 is activated, the first valve 7 is opened, the second valve 10 is closed, the third valve 11 is opened, and the fourth valve 12 is closed, so that oil from the first tank 6 passes through the first valve 7, the third valve 11, and the four-way valve 8 to enter the first area and is supplied by the first booster pump 1.
When the first oil tank 6 is abnormal, if the liquid level of the first oil tank 6 is low, the first valve 7 is closed, the second valve 10 is opened, the third valve 11 is opened, the fourth valve 12 is closed, the oil in the second oil tank 9 enters the first area through the second valve 10, the third valve 11 and the four-way valve 8, and the first booster pump 1 supplies oil.
The device is provided with the buffer tank, the buffer tank is divided into two subareas, the two subareas are used for supplying oil respectively and are backup with each other, and the redundancy design is safer; the two partitions are supplied with oil through two independent booster pumps and two independent check valves respectively, and the two partitions are not interfered with each other. The invention is provided with two oil tanks which are used for storing fuel oil and are mutually backup, four modes of first oil tank 6 and first region oil supply, first oil tank 6 and second region oil supply, second oil tank 9 and first region oil supply, second oil tank 9 and second region oil supply can be formed through a first valve 7, a second valve 10, a third valve 11, a fourth valve 12 and a four-way valve 8 which are communicated with the oil tanks, and the oil supply safety is greatly improved.
Further, still include: a control unit; the control unit includes: the oil quantity sensor comprises a controller, a first oil quantity sensor, a second oil quantity sensor, a flow sensor and a pressure sensor;
the first oil quantity sensor is used for acquiring an oil quantity signal of a first area of the buffer tank; the second oil quantity sensor is used for acquiring an oil quantity signal of a second area of the buffer tank; the flow sensor is used for acquiring a flow signal of a third port of the first tee joint 5, and the pressure sensor is used for acquiring a pressure signal of the third port of the first tee joint 5;
the controller selects the first booster pump 1 or the second booster pump 2 to start according to an oil quantity signal of the first area of the buffer tank, an oil quantity signal of the second area of the buffer tank, a flow signal of the third port of the first tee joint 5 and a pressure signal of the third port of the first tee joint 5;
the first oil mass sensor, the second oil mass sensor, the flow sensor, the pressure sensor, the first booster pump 1 and the second booster pump 2 are respectively electrically connected with the controller.
More specifically, a first oil quantity sensor and a second oil quantity sensor respectively collect oil levels of a first area and a second area, a flow sensor is used for collecting flow finally output by the booster pump, and a pressure sensor is used for collecting pressure finally output by the booster pump.
The controller judges by combining the signals and switches the buffer tank partitions and the oil supply tank.
In a typical application, during normal operation, the first booster pump 1 is activated, the first valve 7 is opened, the third valve 11 is opened, and the first tank 6 and the first region are supplied with oil.
One abnormal condition is that when the pipelines of the first area and the first booster pump 1 are blocked, the pressure signal and the flow signal are both reduced, and at the moment, the controller controls the second booster pump 2 to start, and oil is supplied by the second area.
When the liquid level in the first area is low and the oil amount fed back by the second oil amount sensor is low, the controller controls the second booster pump 2 to start and the second area supplies oil.
The oil supply and delivery system is provided with the controller and the sensor for collecting the oil level signal, the pressure signal of the output pressure of the booster pump and the output flow signal of the booster pump, the controller integrates the signals to control the pump and the valve to switch the oil supply loop according to a preset program, the personnel watching is not needed, the loop is switched quickly and timely, and the continuity and the stability of the oil supply are ensured.
Further, the control unit further includes: the oil level sensor is used for acquiring an oil level signal of the first oil tank 6, and the fourth oil level sensor is used for acquiring an oil level signal of the second oil tank 9;
the controller is further configured to control the first valve 7 to communicate or the second valve 10 to communicate according to a fuel quantity signal of the first fuel tank 6, a fuel quantity signal of the second fuel tank 9, a fuel quantity signal of a first area of the buffer tank, a flow signal of a third port of the first tee joint 5, and a pressure signal of a third port of the first tee joint 5, and the controller is further configured to control the third valve 11 to communicate or the fourth valve 12 to communicate according to the fuel quantity signal of the first fuel tank 6, the fuel quantity signal of the second fuel tank 9, the fuel quantity signal of the first area of the buffer tank, the fuel quantity signal of the second area of the buffer tank, the flow signal of the third port of the first tee joint 5, and the pressure signal of the third port of the first tee joint 5;
the third oil amount sensor, the fourth oil amount sensor, the first valve 7, the second valve 10, the third valve 11, and the fourth valve 12 are electrically connected to the controller, respectively.
More specifically, third oil mass sensor is used for gathering the oil mass signal of first oil tank 6, fourth oil mass sensor are used for gathering the oil mass signal of second oil tank 9, the controller is synthesized and is come from the oil mass signal of first oil tank 6, the oil mass signal of second oil tank 9, the oil mass signal of the first district of baffle-box, the oil mass signal of baffle-box second district, the flow signal of 5 third mouths of first tee bend and the pressure signal control of 5 third mouths of first tee bend select first district, second district, 6 or 9 fuel supplies of second oil tank.
In a typical application, during normal operation, the first booster pump 1 is activated, the second booster pump 2 is deactivated, the first valve 7 and the third valve 11 are both open, and the second valve 10 and the fourth valve 12 are both closed, and the first tank 6 and the first section are supplied with oil.
One of the abnormalities is that when the oil level in the first oil tank 6 becomes low, the controller switches to supply oil from the second oil tank 9, i.e., switches to start the first booster pump 1, stops the second booster pump 2, closes the first valve 7, communicates the second valve 10, communicates the third valve 11, and closes the fourth valve 12.
In another case, when the oil outlet of the first oil tank 6 is blocked, the liquid level of the first area is lower after a period of time, and at this time, the controller controls the second booster pump 2 to start, the first booster pump 1 to stop, then the first valve 7 is closed, the second valve 10 is communicated, the third valve 11 is closed, the fourth valve 12 is communicated, and oil is supplied by the second oil tank 9 and the second area.
The oil supply and delivery system is provided with the third oil level sensor and the fourth oil level sensor, oil level signals of the first oil tank 6 and the second oil tank 9 are acquired through the two sensors, when the oil level of the oil tank is abnormal, the controller switches an oil supply loop by controlling the start and stop of the first valve 7, the second valve 10, the third valve 11, the first booster pump 1 and the second booster pump 2, and the controller switches signals quickly and timely, so that the continuity of oil supply is guaranteed.
Further, the first oil tank 6 is further provided with a fifth oil outlet, and the second oil tank 9 is further provided with a sixth oil outlet;
the first oil tank unit further comprises a second tee joint 13, and the second oil tank unit further comprises a third tee joint 14;
a first end of the second tee joint 13 is communicated with the third oil outlet, a second end of the second tee joint 13 is communicated with the fifth oil outlet, and a third end of the second tee joint 13 is communicated with a first end of the first valve 7;
a first end of the third tee joint 14 is communicated with the fourth oil outlet, a second end of the third tee joint 14 is communicated with the sixth oil outlet, and a third end of the third tee joint 14 is communicated with a first end of the second valve 10.
More specifically, the first oil tank 6 and the second oil tank 9 of the oil supply and delivery system are respectively provided with two oil filling ports, and the two oil filling ports are respectively communicated with the electromagnetic valve through a tee joint. In the flying process of the airplane, the posture is constantly changed, and the height of an oil outlet of an oil tank relative to a buffer tank is constantly changed, so that the continuity of oil supply is influenced. The first oil tank 6 and the second oil tank 9 of the oil supply and delivery system are provided with two oil filling ports which are respectively arranged at two different positions, so that one port can be used for supplying oil instead of the other port, and the safety of oil supply of the oil tanks is improved.
Further, the buffer tank is located below the first oil tank 6 and the second oil tank 9, and the relative positions satisfy:
h represents the vertical height between the third and fourth outlets and the first or second outlet;
q represents the engine maximum flow demand;
l represents the nominal length of the oil supply line;
d represents the nominal diameter of the oil supply line;
g represents the gravitational acceleration;
a represents the maximum acceleration of the aircraft;
λ represents an on-way drag coefficient;
ζ represents the total local drag coefficient;
alpha represents the maximum elevation angle of the aircraft.
More specifically, the formula is calculated according to the Bernoulli hydrodynamics principle and in combination with the actual situation of the aircraft oil supply and delivery system. If the position of the buffer tank meets the requirement of a formula, gravity oil supply of the main oil tank to the buffer tank can be realized. The installation of oil supply equipment of a main oil tank can be reduced, the repeated design of an oil supply and delivery system when the piston engine supplied with oil by gravity is replaced with the turboprop engine is avoided, and the replacement cost is reduced.
And the use of the buffer tank can greatly shorten the distance between the oil tank and the engine, increase the extra fuel quantity, improve the safety of the oil supply and delivery system of the airplane, and play a certain role in achieving the integral balance of the airplane.
Further, the buffer tank unit further includes: a first float switch 15 and a second float switch 16, the first tank unit further including: a third float switch 17, the second tank unit further including: a fourth float switch 18;
the first float switch 15 is arranged at the first vent, the second float switch 16 is arranged at the second vent, the third float switch 17 is arranged at the third vent, and the fourth float switch 18 is arranged at the fourth vent 8.
More specifically, the oil supply and delivery system is provided with the float switch at the air vent of the oil tank and the buffer tank, and the float switch closes the air vent when the attitude of the airplane changes, so that the liquid level approaches the air vent, the fuel is prevented from overflowing from the air vent, and the safety of oil supply is improved.
Further, the buffer box unit further comprises a turn-off switch 19, the turn-off switch 19 is communicated with the third end of the first tee joint 5, and the turn-off switch 19 is electrically connected with the controller.
More specifically, the oil supply and delivery system of the present invention is further provided with a shutoff switch 19, the shutoff switch 19 is disposed at the extreme end of the oil supply loop and used for shutting off the oil supply output in an emergency, the shutoff switch 19 is controlled by the controller, and in an emergency, the controller receives an external input, for example, in an embodiment, the controller is provided with an emergency button, and when the button is pressed, the shutoff switch 19 is turned off, and the oil supply loop is completely turned off.
An aircraft oil supply and delivery system control method comprises the following steps:
selecting an oil tank and a buffer tank partition;
opening a valve and a booster pump which are matched with the selected oil tank and the buffer tank in partition;
judging whether the starting requirement of the engine is met or not according to the pressure output by the booster pump, and if the starting requirement is not met, adjusting the pressure output by the booster pump until the preset condition of the output pressure is met;
judging the gravity center according to the two oil tank oil quantity signals, and switching an oil supply tank through opening and closing a valve if the gravity center exceeds a preset condition; judging whether the output of the working booster pump is normal or not according to the pressure output by the booster pump and the flow output by the booster pump, and switching the buffer tank to divide the buffer tank into sections by switching the booster pump and the opening and closing of the valve if the output of the working booster pump exceeds a preset flow condition;
if the oil quantity of one buffer tank partition is lower than the preset condition of the oil quantity lowest position, and the partition is lower than the preset condition of the oil quantity lowest position after a time delay, the buffer tank partition is switched by switching the opening and closing of a booster pump and a valve, and an oil supply tank is unchanged; after a period of time delay, if the switched buffer tank subarea is lower than the preset lowest position again, the oil supply tank is switched by opening and closing the valve, and after a period of time delay, if the switched buffer tank subarea is not lower than the preset lowest position again, the original buffer tank subarea is switched by switching the opening and closing of the booster pump and the valve;
and judging whether the oil supply and delivery system threatens the flight safety or not according to the data of the flight control computer, if so, closing the turn-off switch 19, and replying to the flight control computer that the turn-off switch 19 is closed.
A control method for an aircraft oil supply and delivery system aims at different working conditions, and for example, when the integral gravity center is unbalanced due to the oil quantity of an oil tank, the gravity center of an aircraft is adjusted by switching an oil supply loop. When output flow of the booster pump exceeds a preset condition, the buffer tank partitions are switched, when the buffer tank partitions are lower than a preset condition of an oil level, the oil tank and the buffer tank are switched to solve the problem that the oil level of the buffer tank partitions is too low, the problem that flying oil supply is unsafe under most conditions can be solved through the scheme, and a reliable solution is provided.
The embodiments described above are only preferred embodiments of the invention and are not exhaustive of the possible implementations of the invention. Any obvious modifications to the above would be obvious to those of ordinary skill in the art, but would not bring the invention so modified beyond the spirit and scope of the present invention.
Claims (9)
1. An aircraft fuel supply and delivery system, comprising: a buffer tank unit;
the buffer tank unit includes: the device comprises a buffer tank, a first booster pump (1), a second booster pump (2), a first one-way valve (3), a second one-way valve (4) and a first tee joint (5);
the buffer box is a sealed container and comprises a first buffer box area and a second buffer box area, and the first buffer box area is not communicated with the second buffer box area; the first district of baffle-box is equipped with: the first oil inlet, the first air vent and the first oil outlet; the buffer box second zone is provided with: the second oil inlet, the second vent and the second oil outlet;
an oil inlet of the first booster pump (1) is communicated with the first oil outlet, and an oil outlet of the first booster pump (1) is communicated with a first port of the first one-way valve (3);
an oil inlet of the second booster pump (2) is communicated with the second oil outlet, and an oil outlet of the second booster pump (2) is communicated with a first port of the second one-way valve (4);
the second port of the first one-way valve (3) is communicated with the first port of the first tee joint (5), and the second port of the second one-way valve (4) is communicated with the second port of the first tee joint (5).
2. An aircraft oil supply and delivery system according to claim 1, further comprising: a first tank unit and a second tank unit; the oil supply unit further includes: a third valve (11) and a fourth valve (12);
the first tank unit includes: a first oil tank (6), a first valve (7) and a four-way valve (8);
the second tank unit includes: a second tank (9) and a second valve (10);
first oil tank (6) and second oil tank (9) are sealed container, first oil tank (6) are equipped with: the first oil filling port, the third air vent and the third oil outlet; the second oil tank (9) is provided with: a second oil filling port, a fourth passage (8) air port and a fourth oil outlet;
the first valve (7), the second valve (10), the third valve (11) and the fourth valve (12) are two-position two-way valves, a first end of the first valve (7) is communicated with the third oil outlet, and a second end of the first valve (7) is communicated with a first port of the four-way valve (8); the first end of the second valve (10) is communicated with the fourth oil outlet, and the second end of the second valve (10) is communicated with the second port of the four-way valve (8); the first end of the third valve (11) is communicated with the third port of the four-way joint (8), and the second end of the third valve (11) is communicated with the first oil inlet; and the first end of the fourth valve (12) is communicated with a fourth port of the four-way valve (8), and the second end of the third valve (11) is communicated with the second oil inlet.
3. An aircraft oil supply and delivery system according to claim 2, further comprising: a control unit; the control unit includes: the oil quantity sensor comprises a controller, a first oil quantity sensor, a second oil quantity sensor, a flow sensor and a pressure sensor;
the first oil quantity sensor is used for acquiring an oil quantity signal of a first area of the buffer tank; the second oil quantity sensor is used for acquiring an oil quantity signal of a second area of the buffer tank; the flow sensor is used for acquiring a flow signal of a third port of the first tee joint (5), and the pressure sensor is used for acquiring a pressure signal of the third port of the first tee joint (5);
the controller selects the first booster pump (1) or the second booster pump (2) to start according to an oil mass signal of the first area of the buffer tank, an oil mass signal of the second area of the buffer tank, a flow signal of the third port of the first tee joint (5) and a pressure signal of the third port of the first tee joint (5);
the first oil quantity sensor, the second oil quantity sensor, the flow sensor, the pressure sensor, the first booster pump (1) and the second booster pump (2) are respectively electrically connected with the controller.
4. An aircraft oil supply and delivery system according to claim 3, wherein the control unit further comprises: the oil quantity monitoring system comprises a third oil quantity sensor and a fourth oil quantity sensor, wherein the third oil quantity sensor is used for acquiring an oil quantity signal of the first oil tank (6), and the fourth oil quantity sensor is used for acquiring an oil quantity signal of the second oil tank (9);
the controller is also used for controlling the communication of the first valve (7) or the communication of the second valve (10) according to an oil mass signal of the first oil tank (6), an oil mass signal of the second oil tank (9), an oil mass signal of the first area of the buffer tank, an oil mass signal of the second area of the buffer tank, a flow signal of the third port of the first tee joint (5) and a pressure signal of the third port of the first tee joint (5), the controller is also used for controlling the communication of a third valve (11) or the communication of a fourth valve (12) according to an oil mass signal of the first oil tank (6), an oil mass signal of the second oil tank (9), an oil mass signal of a first area of the buffer tank, an oil mass signal of a second area of the buffer tank, a flow signal of a third port of the first tee joint (5) and a pressure signal of a third port of the first tee joint (5);
the third oil amount sensor, the fourth oil amount sensor, the first valve (7), the second valve (10), the third valve (11), and the fourth valve (12) are electrically connected to the controller, respectively.
5. Aircraft oil supply and delivery system according to claim 4, characterized in that said first oil tank (6) is further provided with a fifth oil outlet and said second oil tank (9) is further provided with a sixth oil outlet;
the first oil tank unit further comprises a second tee joint (13), and the second oil tank unit further comprises a third tee joint (14);
a first end of the second tee joint (13) is communicated with the third oil outlet, a second end of the second tee joint (13) is communicated with the fifth oil outlet, and a third end of the second tee joint (13) is communicated with a first end of the first valve (7);
the first end of the third tee joint (14) is communicated with the fourth oil outlet, the second end of the third tee joint (14) is communicated with the sixth oil outlet, and the third end of the third tee joint (14) is communicated with the first end of the second valve (10).
6. An aircraft oil supply and delivery system according to claim 2, wherein the buffer tank is located below the first oil tank (6) and the second oil tank (9) in such a way that the relative positions are:
h represents the vertical height between the third and fourth outlets and the first or second outlet;
q represents the engine maximum flow demand;
l represents the nominal length of the oil supply line;
d represents the nominal diameter of the oil supply line;
g represents the gravitational acceleration;
a represents the maximum acceleration of the aircraft;
λ represents an on-way drag coefficient;
ζ represents the total local drag coefficient;
alpha represents the maximum elevation angle of the aircraft.
7. An aircraft oil supply and delivery system according to claim 6, wherein the surge tank unit further comprises: a first float switch (15) and a second float switch (16), the first tank unit further comprising: a third float switch (17), the second tank unit further comprising: a fourth float switch (18);
first float switch (15) set up first air vent, second float switch (16) set up the second air vent, third float switch (17) set up the third air vent, fourth float switch (18) set up fourth (8) air vent.
8. The aircraft fuel supply and delivery system of claim 7, wherein the buffer tank unit further comprises a shutoff switch (19), the shutoff switch (19) is communicated with a third end of the first tee joint (5), and the shutoff switch (19) is electrically connected with the controller.
9. An aircraft oil supply and delivery system control method is characterized by comprising the following steps:
selecting an oil tank and a buffer tank partition;
opening a valve and a booster pump which are matched with the selected oil tank and the buffer tank in partition;
judging whether the starting requirement of the engine is met or not according to the pressure output by the booster pump, and if the starting requirement is not met, adjusting the pressure output by the booster pump until the preset condition of the output pressure is met;
judging the gravity center according to the two oil tank oil quantity signals, and switching an oil supply tank through opening and closing a valve if the gravity center exceeds a preset condition;
judging whether the output of the working booster pump is normal or not according to the pressure output by the booster pump and the flow output by the booster pump, and switching the buffer tank to divide the buffer tank into sections by switching the booster pump and the opening and closing of the valve if the output of the working booster pump exceeds a preset flow condition;
if the oil quantity of one buffer tank partition is lower than the preset condition of the oil quantity lowest position, and the partition is lower than the preset condition of the oil quantity lowest position after a time delay, the buffer tank partition is switched by switching the opening and closing of a booster pump and a valve, and an oil supply tank is unchanged; after a period of time delay, if the switched buffer tank subarea is lower than the preset lowest position again, the oil supply tank is switched by opening and closing the valve, and after a period of time delay, if the switched buffer tank subarea is not lower than the preset lowest position again, the original buffer tank subarea is switched by switching the opening and closing of the booster pump and the valve;
and judging whether the oil supply and delivery system threatens the flight safety or not according to the data of the flight control computer, if so, closing the turn-off switch (19), and replying to the flight control computer that the turn-off switch (19) is closed.
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| CN115030824A (en) * | 2022-08-11 | 2022-09-09 | 成都凯天电子股份有限公司 | Self-adaptive oil supply system and method under full flight profile of helicopter |
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