Fuel balance system and method for left and right fuel tanks of airplane

Abstract

The invention belongs to the field of fuel tank fuel control, and relates to an aircraft left and right fuel tank fuel balance system and method.The aircraft left and right fuel tank fuel balance system comprises a left fuel unit, a right fuel unit and a control processor, and an isolation valve is arranged between the left fuel unit and the right fuel unit; all electric elements in the left fuel unit and the right fuel unit are controlled through the control processor; the flight control system commands the processor to use different strategies under different conditions, the rapid strategy is used for dealing with the situation that the fuel quantity of the left side and the right side of an airplane has large deviation under the emergency condition, and the fuel on the left side and the right side can be balanced in a short time; the normal strategy of fuel can balance the fuel quantity of the corresponding fuel tanks on the left side and the right side of the aircraft more accurately, so that the gravity center of the aircraft is kept near the symmetry plane, and the flight safety of the aircraft is guaranteed to the maximum extent.

Description

Technical Field

[0001] The present application belongs to the field of fuel tank fuel control, and in particular relates to a fuel balancing system and method for left and right fuel tanks of an aircraft. Background Art

[0002] In the design process of large aircraft, the utilization rate of the interior space is one of the key considerations. In order to maximize the use of the interior space of the aircraft and meet the fuel needs of large aircraft, the aircraft's fuel tanks are usually symmetrically arranged inside the wings. This design has many advantages: first, it improves the aircraft's passenger and cargo transportation capacity; second, the movement of the aircraft's center of gravity is small when fuel is consumed, which is beneficial to the aircraft's flight balance and safety; third, the fuel tanks placed on the wings are far away from the ground, which is relatively safe in special circumstances such as emergency landings.

[0003] Large aircraft usually have multiple sets of fuel tanks symmetrically arranged in the wings to meet the fuel supply needs of the engine. However, the aircraft fuel transmission system has a complex structure and involves many components. As the engine continues to consume the fuel in the tank, the fuel amount in the multiple tanks may deviate greatly. Factors such as the quality of the fuel transfer valve and the installation position of the fuel sensor will lead to the occurrence of an imbalance in the fuel amount of the left and right tanks of the wing, which ultimately greatly affects the stability of the aircraft's flight attitude and poses a serious threat to the safety of the aircraft.

[0004] The most traditional solution to the above-mentioned imbalance in fuel between the left and right tanks of the wing is to use the cross-fueling method. Taking a civil aircraft as an example, the aircraft first detects that the fuel levels of the left and right tanks of the wing are quite different, and issues an alarm signal. The crew manually opens the cross-fueling valve between the left and right tanks of the wing, closes the fuel pump and the fuel valve of the low-fuel tank, and opens the fuel pump and the fuel valve of the high-fuel tank. At this time, the fuel in the high-fuel tank supplies fuel to multiple groups of engines at the same time, so as to achieve the purpose of reducing the fuel level deviation of the left and right tanks of the wing.

[0005] The above-mentioned fuel balancing method requires shutting down the fuel supply pumps of all low-fuel tanks. If the fuel supply pumps fail to restart, the fuel supply safety of the aircraft will be threatened. In addition, this method requires manual operation by the crew, so there are certain limitations. Summary of the invention

[0006] The purpose of the present application is to provide a fuel balancing system and method for left and right fuel tanks of an aircraft to solve or alleviate at least one problem in the background technology.

[0007] The technical solution of the present application is: a left and right fuel tank fuel balancing system for an aircraft, comprising a left fuel unit, a right fuel unit and a control processor, an isolation valve being arranged between the left fuel unit and the right fuel unit; the left fuel unit comprising a left first oil pipeline, a left second oil pipeline, a left first fuel tank and a left second fuel tank; the left first oil pipeline is connected to the inside of the left first fuel tank; the left second oil pipeline is connected to the inside of the left second fuel tank, and the left first oil pipeline and the left second oil pipeline are connected to each other; the right fuel unit comprises a right ... and the left second oil pipeline are connected to each other; the right fuel unit comprises a right first oil pipeline, a left second oil pipeline, a left first fuel tank and a left second fuel tank; the left first oil pipeline and the left second oil pipeline are connected to each other; the left The oil pipe, the right second oil pipe, the right first oil tank and the right second oil tank; the right first oil pipe is connected to the inside of the right first oil tank, the right second oil pipe is connected to the inside of the right second oil tank, and the right first oil pipe and the right second oil pipe are interconnected; the left first oil tank, the left second oil tank, the right first oil tank and the right second oil tank are all provided with electrical components for sensing the oil volume and controlling the oil tank switches, the left second oil pipe is interconnected with the right second oil pipe, and the control processor is electrically connected to all electrical components inside the left fuel unit and the right fuel unit.

[0008] Preferably, a left oil level sensor, a left oil pump and a left transmission valve are installed inside the left oil tank; the left oil pump is located below the fuel liquid level, and the left transmission valve is connected to the left oil pump through a left oil pipe.

[0009] Preferably, a left second oil level sensor, a left second oil pump and a left second transmission valve are installed inside the left second fuel tank; the left second oil pump is located below the fuel liquid level, the left second transmission valve is connected to the left second oil pump through the left second oil pipe, and the left second oil pipe is connected to the isolation valve.

[0010] Preferably, a right oil level sensor, a right oil pump and a right transmission valve are installed inside the right oil tank; the right oil pump is located below the fuel liquid level, and the right transmission valve is connected to the right oil pump through a right oil pipe.

[0011] Preferably, a right second oil level sensor, a right second oil pump and a right second transmission valve are installed inside the right second oil tank; the right second oil pump is located below the fuel liquid level, the right second transmission valve is connected to the right second oil pump through the right second oil pipe, and the right second oil pipe is connected to the isolation valve.

[0012] As a specific implementation, a method for balancing fuel between left and right fuel tanks of an aircraft includes: a flight control system collects current flight data of the aircraft and determines whether the current aircraft has a fault; when the aircraft has no fault, the flight control system commands the control processor to execute a normal strategy, and when the aircraft has a fault, the flight control system commands the control processor to execute a fast strategy;

[0013] When the flight control system determines to execute the fast strategy:

[0014] The control processor first obtains the fuel levels of the first left fuel tank, the second left fuel tank, the second right fuel tank and the first right fuel tank respectively through the first left fuel level sensor, the second left fuel level sensor, the first right fuel level sensor and the second right fuel level sensor;

[0015] Secondly, compare the difference in fuel volume between the left and right tanks, that is, compare the total fuel volume of the left first tank and the left second tank with the total fuel volume of the right second tank and the right first tank, obtain the fuel volume difference and mark it as Q D ;

[0016] Then compare the left tank with the right tank and the right tank, and the left tank with the right tank and the right tank, and find the two tanks with the largest difference in fuel volume on both sides, and mark them as L 左 and L 右 ;

[0017] The control processor turns on L 左 and L 右 The corresponding transfer valve and isolation valve, the other valves remain closed, and control L 左 and L 右 The fuel pump in the tank with the larger amount of fuel starts to work and transfer the fuel;

[0018] The fuel in the tank with a larger oil volume flows through the corresponding transfer valve, oil pipeline and isolation valve, and enters the tank with a smaller oil volume through the opened transfer valve in the tank with a smaller oil volume;

[0019] During the fuel transfer process, the control processor continuously monitors L through the fuel level sensor. 左 and L 右 The amount of fuel in the tank, when the amount of fuel is small, the difference between the transmitted fuel amount and the total fuel amount Q D When the difference is less than or equal to the difference setting value, the corresponding oil pump, transmission valve and isolation valve are closed to complete the rapid balance of the fuel amount in the left and right tanks.

[0020] Preferably, during normal flight of the aircraft, the control processor detects that the difference in fuel volume between the left and right sides exceeds the specified maximum difference Q max When , the normal strategy mode starts to be executed;

[0021] After the total fuel amount on the left and right sides is in a balanced state, the fuel amount difference between the two tanks on the same side is obtained, and the transfer valves in the two tanks on the same side are opened. The fuel pump in the tank with a larger fuel amount starts working. When the transferred fuel amount is about half of the difference, the corresponding fuel pump stops working and the transfer valve is closed at the same time to complete the fuel transfer of the four tanks on the left and right sides.

[0022] Preferably, the maximum difference Q max The sum and difference setting values ​​can be set as required.

[0023] Preferably, a left oil level sensor, a left oil pump and a left transmission valve are installed inside the left oil tank; the left oil pump is located below the fuel liquid level, and the left transmission valve is connected to the left oil pump through a left oil pipe.

[0024] Preferably, a left second oil level sensor, a left second oil pump and a left second transmission valve are installed inside the left second fuel tank; the left second oil pump is located below the fuel liquid level, the left second transmission valve is connected to the left second oil pump through the left second oil pipe, and the left second oil pipe is connected to the isolation valve.

[0025] Preferably, a right oil level sensor, a right oil pump and a right transmission valve are installed inside the right oil tank; the right oil pump is located below the fuel liquid level, and the right transmission valve is connected to the right oil pump through a right oil pipe.

[0026] Preferably, a right second oil level sensor, a right second oil pump and a right second transmission valve are installed inside the right second oil tank; the right second oil pump is located below the fuel liquid level, the right second transmission valve is connected to the right second oil pump through the right second oil pipe, and the right second oil pipe is connected to the isolation valve.

[0027] The aircraft left and right fuel tank fuel balancing system and method of the present application include a left fuel unit, a right fuel unit and a control processor, wherein an isolation valve is provided between the left fuel unit and the right fuel unit; all electrical components inside the left fuel unit and the right fuel unit are controlled by the control processor; the flight control system commands the control processor to use different strategies in different situations, and a fast strategy is used to deal with the situation where there is a large deviation in the fuel amount on the left and right sides of the aircraft in an emergency, and the fuel on the left and right sides can be balanced in a short time; the normal fuel strategy can more accurately balance the fuel amounts in the corresponding tanks on the left and right sides of the aircraft, so that the center of gravity of the aircraft is kept near the symmetry plane, thereby ensuring the flight safety of the aircraft to the greatest extent. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] In order to more clearly illustrate the technical solution provided by the present application, the following is a brief introduction to the accompanying drawings. Obviously, the accompanying drawings described below are only some embodiments of the present application.

[0029] Figure 1 This is a schematic diagram of the overall structure of this application.

[0030] 1. Left first oil pump; 2. Left second oil pump; 3. Right second oil pump; 4. Right first oil pump; 5. Left first transmission valve; 6. Left second transmission valve; 7. Right second transmission valve; 8. Right first transmission valve; 9. Left first oil pipeline; 10. Left second oil pipeline; 11. Right second oil pipeline; 12. Right first oil pipeline; 13. Left first oil level sensor; 14. Left second oil level sensor; 15. Right second oil level sensor; 16. Right first oil level sensor; 17. Control processor; 18. Left first oil tank; 19. Left second oil tank; 20. Right second oil tank; 21. Right first oil tank; 22. Isolation valve. DETAILED DESCRIPTION

[0031] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0032] A fuel balancing system for left and right fuel tanks of an aircraft, such as Figure 1 As shown, it includes a left fuel unit, a right fuel unit and a control processor 17. An isolation valve 22 is provided between the left fuel unit and the right fuel unit. When the isolation valve 22 is opened, the fuels of the left fuel unit and the right fuel unit can flow to each other.

[0033] The left fuel unit includes a left first fuel pipe 9, a left second fuel pipe 10, a left first fuel tank 18 and a left second fuel tank 19. The left first fuel pipe 9 is connected to the inside of the left first fuel tank 18, the left second fuel pipe 10 is connected to the inside of the left second fuel tank 19, and the left first fuel pipe 9 and the left second fuel pipe 10 are connected to each other.

[0034] A left first oil quantity sensor 13, a left first oil pump 1 and a left first transmission valve 5 are installed inside the left first oil tank 18; the left first oil pump 1 is located below the fuel liquid level, and the left first transmission valve 5 is connected to the left first oil pump 1 through the left first oil pipe 9; a left second oil quantity sensor 14, a left second oil pump 2 and a left second transmission valve 6 are installed inside the left second oil tank 19; the left second oil pump 2 is located below the fuel liquid level, the left second transmission valve 6 is connected to the left second oil pump 2 through the left second oil pipe 10, and the left second oil pipe 10 is connected to the isolation valve 22.

[0035] The right fuel unit includes a right first oil pipeline 12, a right second oil pipeline 11, a right first fuel tank 21 and a right second fuel tank 20. The right first oil pipeline 12 is connected to the inside of the right first fuel tank 21, the right second oil pipeline 11 is connected to the inside of the right second fuel tank 20, and the right first oil pipeline 12 and the right second oil pipeline 11 are connected to each other.

[0036] A right first oil quantity sensor 16, a right first oil pump 4 and a right first transmission valve 8 are installed inside the right first oil tank 21; the right first oil pump 4 is located below the fuel liquid level, and the right first transmission valve 8 is connected to the right first oil pump 4 through the right first oil pipe 12; a right second oil quantity sensor 15, a right second oil pump 3 and a right second transmission valve 7 are installed inside the right second oil tank 20; the right second oil pump 3 is located below the fuel liquid level, the right second transmission valve 7 is connected to the right second oil pump 3 through the right second oil pipe 11, and the right second oil pipe 11 is connected to the isolation valve 22.

[0037] The first left fuel tank 18 and the second left fuel tank 19 are left fuel tanks, the first right fuel tank 21 and the second right fuel tank 20 are right fuel tanks, and the second left oil pipeline 10 and the second right oil pipeline 11 are interconnected. The control processor 17 is electrically connected to all electrical components inside the left fuel unit and the right fuel unit, and the electrical components include all oil level sensors, oil pumps and transmission valves.

[0038] The control processor 17 obtains the fuel quantity data of the left first tank 18, the left second tank 19, the right first tank 21 and the right second tank 20 through the left first sensor, the left second sensor, the right first sensor and the right second sensor, and controls the left first oil pump 1, the left first transmission valve 5, the left second oil pump 2, the left second transmission valve 6, the right first oil pump 4, the right first transmission valve 8, the right second oil pump 3, the right second transmission valve 7 and the isolation valve 22, so as to quickly achieve the oil quantity balance of the four tanks.

[0039] As a specific implementation, a fuel balancing method for left and right fuel tanks of an aircraft is provided with two usage strategies according to different situations, specifically including a fast strategy and a normal strategy.

[0040] The fast strategy is used to deal with the situation where there is a large deviation in the fuel amount on the left and right sides of the aircraft in an emergency, and the fuel on the left and right sides can be balanced in a shorter time; the normal fuel strategy can more accurately balance the fuel amount in the corresponding tanks on the left and right sides of the aircraft, so that the center of gravity of the aircraft remains near the symmetry plane, thereby ensuring the flight safety of the aircraft to the greatest extent.

[0041] The normal strategy is specifically the strategy adopted when the aircraft is flying normally, and the fast strategy is specifically the strategy adopted when the aircraft fails. The judgment of executing the normal strategy and the fast strategy is performed in the flight control system. The flight control system collects the current flight data of the aircraft and judges whether the current aircraft has a fault to judge the strategy to be used by the aircraft. When the aircraft has no fault, the flight control system commands the control processor 17 to execute the normal strategy. When the aircraft has a fault, the flight control system commands the control processor 17 to execute the fast strategy.

[0042] There is a drawback in the fast strategy. This mode can only ensure that the total fuel volume on the left and right sides is balanced, but ignores the local balance of fuel. Therefore, another transmission mode is needed to deal with various complex situations. The normal fuel balance mode can solve this problem.

[0043] Under the normal strategy, the total fuel volume on the left and right sides of the aircraft has reached a balanced state. At this time, only the local balance problem of the fuel on both sides needs to be solved. Therefore, the normal mode is an improvement on the fast transmission strategy.

[0044] In order to ensure that the fuel level in each fuel tank remains sufficient during the long-term flight of the aircraft, the fuel level in the tanks on the same side must continue to be balanced, and the normal fuel balance mode of the aircraft must be turned on to ensure that the weight distribution of the aircraft fuel is even.

[0045] When the flight control system determines to execute the fast strategy:

[0046] The control processor first obtains the fuel levels of the first left tank 18, the second left tank 19, the second right tank 20 and the first right tank 21 through the first left tank level sensor 13, the second left tank level sensor 14, the first right tank level sensor 15 and the second right tank level sensor 16 respectively.

[0047] Secondly, compare the difference in fuel volume between the left and right tanks, that is, compare the total fuel volume of the left first tank 18 and the left second tank 19 with the total fuel volume of the right second tank 20 and the right first tank 21, and obtain the fuel volume difference and mark it as Q D .

[0048] Then the left first tank 18 is compared with the right second tank 20 and the right first tank 21, and the left second tank 19 is also compared with the right second tank 20 and the right first tank 21, and the two tanks with the largest oil volume difference on both sides are found and marked as L 左 and L 右 , where L 左 Oil volume greater than L 右 For example.

[0049] The control processor 17 turns on L 左 Transmission valve corresponding to the fuel tank, L 右 The transfer valve and isolation valve 22 corresponding to the oil tank, and the other valves remain closed, while controlling L 左 The fuel transfer pump in the fuel tank starts working to transfer fuel.

[0050] L 左 The fuel in the fuel tank flows through the corresponding transfer valve, the fuel pipe and the isolation valve 22, and passes through the opened L 右 The transfer valve in the tank goes into L 右 In the fuel tank.

[0051] During the fuel transfer process, the control processor 17 continuously monitors L through the fuel level sensor. 左 and L 右 The amount of fuel in the tank, when L 右 The value of the fuel quantity transmitted is close to the total fuel quantity difference Q D When the fuel pressure is half of that in the left and right tanks, specifically when the difference between the two is less than or equal to the difference setting value, the fuel pump, transmission valve and isolation valve are closed to complete the rapid balance of the fuel quantity in the left and right tanks.

[0052] When the flight control system determines to execute the normal strategy:

[0053] During normal flight of the aircraft, the control processor 17 detects that the difference in fuel volume between the left and right sides exceeds the specified maximum difference Q max When Q max Set according to actual needs.

[0054] Get the fuel quantity of the first left tank, the second left tank, the second right tank and the first right tank respectively;

[0055] The fuel volume of the four fuel tanks is divided into two groups for comparison. The total fuel volume of the left first fuel tank and the left second fuel tank is compared with the total fuel volume of the right second fuel tank and the right first fuel tank to obtain a group of total fuel volume difference Q D ;

[0056] Then compare the first fuel tank on the left with the second fuel tank on the right and the first fuel tank on the right, and compare the second fuel tank on the left with the second fuel tank on the right and the first fuel tank on the right, and find the two fuel tanks with the largest difference among the four groups of comparisons.

[0057] The fuel is transferred to the above fuel tanks, the control processor opens the transfer valves and isolation valves in the two fuel tanks, and at the same time, the fuel pump in the fuel tank with a larger amount of fuel starts to work, and the fuel flows into the fuel tank with a smaller amount of fuel through the fuel pipe under the traction of the fuel pump;

[0058] Until the amount of oil transferred is approximately the total oil difference Q D When the fuel volume is halfway, close the valve and the fuel pump to complete the fuel balance of the tank with the largest fuel volume difference;

[0059] At this point, the total fuel volume on the left and right sides is in balance;

[0060] In order to balance the fuel volume in each tank, the fuel volume in the tank on the same side must be balanced. The fuel transfer between the left and right sides can be carried out simultaneously, and the isolation valve is in a closed state, that is, the fuel on one side of the aircraft cannot flow into the other side;

[0061] Obtain the fuel quantity difference between the two fuel tanks on the same side, open the transfer valves in the two fuel tanks on the same side, and the fuel pump in the fuel tank with a larger fuel quantity starts working. When the transferred fuel quantity is approximately half of the difference (i.e., the fuel quantities in the two tanks are similar), the corresponding fuel pump stops working and the transfer valve is closed at the same time to complete the fuel transfer of the four fuel tanks on the left and right sides.

[0062] Preferably, a left oil level sensor 13, a left oil pump 1 and a left transmission valve 5 are installed inside the left oil tank 18; the left oil pump 1 is located below the fuel liquid level, and the left transmission valve 5 is connected to the left oil pump 1 through the left oil pipe 9.

[0063] Preferably, a left second oil level sensor 14, a left second oil pump 2 and a left second transfer valve 6 are installed inside the left second oil tank 19; the left second oil pump 2 is located below the fuel liquid level, and the left second transfer valve 6 is connected to the left second oil pump 2 through the left second oil pipe 10, and the left second oil pipe 10 is connected to the isolation valve 22.

[0064] Preferably, a right oil level sensor 16, a right oil pump 4 and a right transmission valve 8 are installed inside the right oil tank 21; the right oil pump 4 is located below the fuel liquid level, and the right transmission valve 8 is connected to the right oil pump 4 through the right oil pipe 12.

[0065] Preferably, the right second oil tank 20 is internally installed with a right second oil level sensor 15, a right second oil pump 3 and a right second transmission valve 7; the right second oil pump 3 is located below the fuel liquid level, the right second transmission valve 7 is connected to the right second oil pump 3 through the right second oil pipe 11, and the right second oil pipe 11 is connected to the isolation valve 22.

[0066] The following two specific examples are used to illustrate:

[0067] Implementation Case 1;

[0068] The control processor 17 monitors the fuel quantities of the first left tank 18, the second left tank 19, the second right tank 20 and the first right tank 21 through the fuel quantity sensors, which are 3000kg, 2000kg, 5000kg and 2000kg respectively. The fuel quantity difference between the left and right sides is 2000kg, which exceeds the maximum allowable difference of 500kg. The fast balancing mode is activated according to the situation, and the transmission steps are as follows:

[0069] Step 1: Compare the oil levels of the left and right fuel tanks in pairs, where the oil level difference between the left second fuel tank 19 and the right second fuel tank 20 is the largest;

[0070] Step 2: Open the second left transmission valve, the second right transmission valve and the isolation valve, and at the same time, the oil pump in the second right fuel tank 20 starts to work, and the fuel flows through the second right fuel pipe, the isolation valve and the second left fuel pipe into the second left fuel tank in sequence;

[0071] When the amount of fuel delivered by the right second fuel tank 20 reaches half of the total difference of 1000kg on the left and right sides, the right second fuel pump stops working, the fuel delivery valve and the isolation valve are closed, and the fuel on the left and right sides of the aircraft reaches a relatively balanced state;

[0072] Implementation Case 2;

[0073] The fuel amounts of the first left fuel tank 18, the second left fuel tank 19, the second right fuel tank 20 and the first right fuel tank 21 are 2000kg, 5000kg, 6000kg and 3000kg respectively, and the normal fuel transmission mode is started;

[0074] Step 1: The fuel amounts of the first left fuel tank 18 and the second left fuel tank 19 are compared with the fuel amounts of the second right fuel tank 20 and the first right fuel tank 21, respectively. The difference between the first left fuel tank 18 and the second right fuel tank 22 is the largest, and the fuel amount of these fuel tanks is transmitted first;

[0075] Step 2: Open the left first transmission valve, the right second transmission valve and the isolation valve, the right second oil pump starts to work, and the fuel flows through the right second oil pipe, the isolation valve and the left first oil pipe into the left first fuel tank in sequence. When the amount of fuel transferred is about half of the difference of the total fuel amount on both sides of 1000kg, the right second oil pump stops working, and the left first transmission valve, the right second transmission valve and the isolation valve are closed at the same time. The fuel in the left first fuel tank and the right second fuel tank reaches a balanced state, and the total fuel amount on the left and right sides is also in a balanced state;

[0076] Step 3: At this time, the oil volume difference in the fuel tank on the same side is about 2000kg, and the isolation valve remains closed. The fuel transfer on the left and right sides can be carried out simultaneously. Open the second left oil pump and the second right oil pump, as well as the first left transfer valve, the second left transfer valve, the second right transfer valve and the first right transfer valve. When the transferred fuel volume is about 1000kg, the oil pump stops working and the oil valve is closed to complete the fuel transfer on the same side.

[0077] Finally, it should be noted that: the drawings of the embodiments disclosed in the present invention only involve structures related to the embodiments disclosed in the present invention, and other structures can refer to the general design. In the absence of conflict, the same embodiment and different embodiments of the present invention can be combined with each other;

[0078] Finally: The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. A fuel balancing system for left and right fuel tanks of an aircraft, characterized in that: The invention comprises a left fuel unit, a right fuel unit and a control processor (17), wherein an isolation valve (22) is arranged between the left fuel unit and the right fuel unit; the left fuel unit comprises a first left oil pipeline (9), a second left oil pipeline (10), a first left fuel tank (18) and a second left fuel tank (19); the first left oil pipeline (9) is connected to the inside of the first left fuel tank (18), the second left oil pipeline (10) is connected to the inside of the second left fuel tank (19), and the first left oil pipeline (9) and the second left oil pipeline (10) are connected to each other; the right fuel unit comprises a first right oil pipeline (12), a second right oil pipeline (11), the first right fuel tank (21 ) and the right second oil tank (20); the right first oil pipeline (12) is connected to the inside of the right first oil tank (21), the right second oil pipeline (11) is connected to the inside of the right second oil tank (20), and the right first oil pipeline (12) and the right second oil pipeline (11) are interconnected; the left first oil tank (18), the left second oil tank (19), the right first oil tank (21) and the right second oil tank (20) are all provided with electrical components for sensing the oil volume and controlling the oil tank switch, the left second oil pipeline (10) and the right second oil pipeline (11) are interconnected, and the control processor (17) is electrically connected to all electrical components inside the left fuel unit and the right fuel unit.

2. The aircraft left and right fuel tank fuel balancing system as claimed in claim 1, characterized in that: A left oil level sensor (13), a left oil pump (1) and a left transmission valve (5) are installed inside the left oil tank (18); the left oil pump (1) is located below the fuel liquid level, and the left transmission valve (5) is connected to the left oil pump (1) through a left oil pipe (9).

3. The aircraft left and right fuel tank fuel balancing system as claimed in claim 1, characterized in that: The left second oil tank (19) is internally provided with a left second oil quantity sensor (14), a left second oil pump (2) and a left second transmission valve (6); the left second oil pump (2) is located below the fuel liquid level, the left second transmission valve (6) is connected to the left second oil pump (2) via a left second oil pipe (10), and the left second oil pipe (10) is connected to an isolation valve (22).

4. The aircraft left and right fuel tank fuel balancing system as claimed in claim 1, characterized in that: A right oil level sensor (16), a right oil pump (4) and a right transmission valve (8) are installed inside the right oil tank (21); the right oil pump (4) is located below the fuel liquid level, and the right transmission valve (8) is connected to the right oil pump (4) through a right oil pipe (12).

5. The aircraft left and right fuel tank fuel balancing system as claimed in claim 1, characterized in that: The right second oil tank (20) is internally provided with a right second oil quantity sensor (15), a right second oil pump (3) and a right second transmission valve (7); the right second oil pump (3) is located below the fuel liquid level, the right second transmission valve (7) is connected to the right second oil pump (3) through the right second oil pipe (11), and the right second oil pipe (11) is connected to the isolation valve (22).

6. A method for balancing fuel between left and right fuel tanks of an aircraft, using the fuel balancing system according to any one of claims 1 to 5, characterized in that: include: The flight control system collects the current flight data of the aircraft and determines whether the current aircraft has any faults; When the aircraft has no faults, the flight control system commands the control processor (17) to execute a normal strategy, and when the aircraft has faults, the flight control system commands the control processor (17) to execute a fast strategy; When the flight control system determines to execute the fast strategy: The control processor (17) first obtains the fuel amounts of the first left fuel tank (18), the second left fuel tank (19), the second right fuel tank (20) and the first right fuel tank (21) respectively through the first left fuel amount sensor (13), the second left fuel amount sensor (14), the first right fuel amount sensor (16) and the second right fuel amount sensor (15); secondly, the control processor (17) compares the difference in fuel amounts of the left and right fuel tanks, that is, the total fuel amount of the first left fuel tank (18) and the second left fuel tank (19) is compared with the total fuel amount of the second right fuel tank (20) and the first right fuel tank (21), and obtains the fuel amount difference and marks it as Q D ; Then the left first tank (18) is compared with the right second tank (20) and the right first tank (21), and the left second tank (19) is also compared with the right second tank (20) and the right first tank (21), and the two tanks with the largest difference in oil volume are found and marked as L. 左 and L 右 ; The control processor (17) turns on L 左 and L 右 The corresponding transfer valve and isolation valve, the other valves remain closed, and control L 左 and L 右 The fuel pump in the tank with the larger amount of fuel starts to work and transfer the fuel; The fuel in the tank with a larger oil volume flows through the corresponding transfer valve, oil pipeline and isolation valve, and enters the tank with a smaller oil volume through the opened transfer valve in the tank with a smaller oil volume; During the fuel transfer process, the control processor (17) continuously monitors L through the fuel level sensor. 左 and L 右 The amount of fuel in the tank, when the amount of fuel is small, the difference between the transmitted fuel amount and the total fuel amount Q D When the difference is less than or equal to the difference setting value, the corresponding oil pump, transmission valve and isolation valve are closed to complete the rapid balance of the fuel amount in the left and right tanks.

7. The method for balancing fuel between left and right fuel tanks of an aircraft as claimed in claim 6, characterized in that: During normal flight of the aircraft, the control processor (17) detects that the difference in fuel quantity between the left and right sides exceeds the specified maximum difference value Q. max When , the normal strategy mode starts to be executed; After the total fuel amount on the left and right sides is in a balanced state, the fuel amount difference between the two tanks on the same side is obtained, and the transfer valves in the two tanks on the same side are opened. The fuel pump in the tank with a larger fuel amount starts working. When the transferred fuel amount is about half of the difference, the corresponding fuel pump stops working and the transfer valve is closed at the same time to complete the fuel transfer of the four tanks on the left and right sides.

8. The method for balancing fuel between left and right fuel tanks of an aircraft as claimed in claim 7, characterized in that: The maximum difference Q max The sum and difference setting values ​​can be set as required.

9. The aircraft left and right fuel tank fuel balancing method as claimed in claim 6, characterized in that: A left oil level sensor (13), a left oil pump (1) and a left transmission valve (5) are installed inside the left oil tank (18); the left oil pump (1) is located below the fuel liquid level, and the left transmission valve (5) is connected to the left oil pump (1) through a left oil pipe (9).

10. The aircraft left and right fuel tank fuel balancing method as claimed in claim 6, characterized in that: The left second oil tank (19) is internally provided with a left second oil quantity sensor (14), a left second oil pump (2) and a left second transmission valve (6); the left second oil pump (2) is located below the fuel liquid level, the left second transmission valve (6) is connected to the left second oil pump (2) via a left second oil pipe (10), and the left second oil pipe (10) is connected to an isolation valve (22).

11. The aircraft left and right fuel tank fuel balancing method as claimed in claim 6, characterized in that: A right oil level sensor (16), a right oil pump (4) and a right transmission valve (8) are installed inside the right oil tank (21); the right oil pump (4) is located below the fuel liquid level, and the right transmission valve (8) is connected to the right oil pump (4) through a right oil pipe (12).

12. The method for balancing fuel between left and right fuel tanks of an aircraft as claimed in claim 6, characterized in that: The right second oil tank (20) is internally provided with a right second oil quantity sensor (15), a right second oil pump (3) and a right second transmission valve (7); the right second oil pump (3) is located below the fuel liquid level, the right second transmission valve (7) is connected to the right second oil pump (3) through the right second oil pipe (11), and the right second oil pipe (11) is connected to the isolation valve (22).

Images