An automatic fuel balancing system for an aircraft wing tank and method thereof

Abstract

The application belongs to the technical field of aircraft wing tank balance design, and particularly relates to an automatic fuel quantity balance method for aircraft wing tanks, which is implemented based on an automatic fuel quantity balance system for aircraft wing tanks, and automatically balanced by a balance monitor according to a set logic without manual operation. The fuel quantity in three wing tanks can be controlled within an average fuel quantity M plus or minus 300 kg, and the fuel quantity in the other wing tank can be controlled within the average fuel quantity M plus or minus 900 kg in a fast and real-time manner. The balance control precision can be controlled by adjusting a balance adjustment threshold H and a balance control threshold I, so as to meet the precision requirement of different aircrafts for fuel imbalance control.

Description

Technical Field

[0001] The present application belongs to the technical field of aircraft wing fuel tank balancing design, and specifically relates to an automatic fuel balancing system and method in an aircraft wing fuel tank. Background Art

[0002] Large aircraft generally have multiple engines, and each engine group is supplied with fuel by an independent fuel tank. The fuel tanks are usually symmetrically distributed in the left and right wings. Generally, there are two wing fuel tanks in the left and right wings respectively.

[0003] Currently, to maintain a stable center of gravity, cross-fueling or manual fuel transfer is often used to balance the fuel levels in each wing tank. This reduces the workload of flight control, reduces damage to the landing gear during takeoff and landing, and avoids damage to aircraft structural components.

[0004] The cross-fueling method is used to balance the fuel volume in each wing tank. The balancing speed is slow, the fuel balancing relies on the fuel supply pump, and requires the crew to perform tedious operations. The manual fuel transfer method is used to balance the fuel volume in each wing tank, which consumes a lot of crew energy and makes it difficult to control the balancing accuracy.

[0005] This application is proposed in view of the above-mentioned technical defects. Summary of the Invention

[0006] The purpose of the present application is to provide a system and method for automatically balancing the amount of fuel in an aircraft wing tank, so as to overcome or alleviate at least one of the technical deficiencies of the known technologies.

[0007] The technical solution of this application is:

[0008] On the one hand, a system for automatically balancing the amount of fuel in an aircraft wing tank is provided, comprising four balancing oil pumps, four balancing control valves, a balancing transfer pipeline, and a balancing monitor;

[0009] Four balancing oil pumps and balancing control valves are installed in the four wing oil tanks and are connected to the balancing transfer pipelines through pipelines;

[0010] The balance monitor is connected to four balancing oil pumps, a balancing control valve, and the flight control system so that it can obtain the fuel-related parameters in the four wing tanks, thereby calculating the fuel quantity in the four wing tanks. Then, by controlling the four balancing oil pumps and the balancing control valve switches, the fuel quantity in the four wing tanks can be balanced using the balancing transfer pipeline.

[0011] On the one hand, a system for automatically balancing the amount of fuel in an aircraft wing tank is provided, comprising four balancing oil pumps, four balancing control valves, a balancing transfer pipeline, and a balancing monitor;

[0012] Four balancing oil pumps and balancing control valves are installed in the four wing oil tanks and are connected to the balancing transfer pipelines through pipelines;

[0013] The balance monitor is connected to four balancing oil pumps, a balancing control valve, and the flight control system so that it can obtain the fuel-related parameters in the four wing tanks, thereby calculating the fuel quantity in the four wing tanks. Then, by controlling the four balancing oil pumps and the balancing control valve switches, the fuel quantity in the four wing tanks can be balanced using the balancing transfer pipeline.

[0014] Optionally, in the above-mentioned automatic balancing system for fuel in the aircraft wing tanks, the balancing monitor balances the fuel in the four wing tanks specifically as follows:

[0015] Step 1: Calculate the fuel amount in the four wing tanks to obtain the average fuel amount M, and then proceed to step 2;

[0016] Step 2: Determine whether there is a wing tank with low fuel level. If yes, proceed to step 3; if not, proceed to step 6. A wing tank with low fuel level refers to a wing tank whose internal fuel level is less than the average fuel level M, and the amount of the internal fuel level is greater than the balance adjustment threshold H, and the duration of the internal fuel level is greater than the set time S.

[0017] Step 3: Turn off the balancing fuel pump in the wing tank with low fuel level, and open the balancing control valve in the wing tank with low fuel level, and proceed to step 4;

[0018] Step 4: Determine whether the fuel level in the wing tank of the low fuel level is within the range of the average fuel level M ± the balance control threshold I, and whether the duration is greater than the set time S. If so, proceed to step 5; if not, proceed to step 6.

[0019] Step 5: Close the balance control valve in the wing tank with low fuel quantity and proceed to step 6;

[0020] Step 6: Determine whether there is a wing tank with a high fuel level. If so, proceed to step 7; if not, proceed to step 8. A wing tank with a high fuel level refers to a wing tank whose internal fuel level is greater than the average fuel level M, and the amount of the internal fuel level is greater than the balance adjustment threshold H, and the duration of the internal fuel level is greater than the set time S.

[0021] Step 7: Close the balancing control valve in the wing tank with high fuel volume, and open the balancing oil pump in the wing tank with high fuel volume, and proceed to Step 8;

[0022] Step 8: Determine whether the fuel levels in any three wing tanks are within the range of the average fuel level M ± the balancing control threshold I, and for a duration greater than the set time S. If so, close all balancing fuel pumps and balancing control valves to complete the balancing of the fuel levels in the wing tanks. If not, proceed to step 4.

[0023] Optionally, in the above-mentioned automatic balancing system for the amount of fuel in the aircraft wing tank, the balance control threshold I<the balance adjustment threshold H.

[0024] Optionally, in the above-mentioned automatic balancing system for the amount of fuel in the aircraft wing tank, the balancing adjustment threshold H is 300 kg.

[0025] Optionally, in the above-mentioned automatic balancing system for the amount of fuel in the aircraft wing tank, the set time length S is 1 second.

[0026] Optionally, in the above-mentioned automatic balancing system for the fuel amount in the aircraft wing tank, the balance control threshold I is 200 kg.

[0027] Another aspect provides a method for automatically balancing the amount of fuel in an aircraft wing tank, which is implemented based on the above-mentioned automatic balancing system for the amount of fuel in an aircraft wing tank, and includes:

[0028] Step 1: Calculate the fuel amount in the four wing tanks to obtain the average fuel amount M, and then proceed to step 2;

[0029] Step 2: Determine whether there is a wing tank with low fuel level. If yes, proceed to step 3; if not, proceed to step 6. A wing tank with low fuel level refers to a wing tank whose internal fuel level is less than the average fuel level M, and the amount of the internal fuel level is greater than the balance adjustment threshold H, and the duration of the internal fuel level is greater than the set time S.

[0030] Step 3: Turn off the balancing fuel pump in the wing tank with low fuel level, and open the balancing control valve in the wing tank with low fuel level, and proceed to step 4;

[0031] Step 4: Determine whether the fuel level in the wing tank of the low fuel level is within the range of the average fuel level M ± the balance control threshold I, and whether the duration is greater than the set time S. If so, proceed to step 5; if not, proceed to step 6, wherein the balance control threshold I < the balance adjustment threshold H;

[0032] Step 5: Close the balance control valve in the wing tank with low fuel quantity and proceed to step 6;

[0033] Step 6: Determine whether there is a wing tank with a high fuel level. If so, proceed to step 7; if not, proceed to step 8. A wing tank with a high fuel level refers to a wing tank whose internal fuel level is greater than the average fuel level M, and the amount of the internal fuel level is greater than the balance adjustment threshold H, and the duration of the internal fuel level is greater than the set time S.

[0034] Step 7: Close the balancing control valve in the wing tank with high fuel volume, and open the balancing oil pump in the wing tank with high fuel volume, and proceed to Step 8;

[0035] Step 8: Determine whether the fuel levels in any three wing tanks are within the range of the average fuel level M ± the balancing control threshold I, and for a duration greater than the set time S. If so, close all balancing fuel pumps and balancing control valves to complete the balancing of the fuel levels in the wing tanks. If not, proceed to step 4.

[0036] Optionally, in the above-mentioned method for automatically balancing the fuel amount in the aircraft wing tank, the balance adjustment threshold H is 300 kg.

[0037] Optionally, in the above-mentioned method for automatically balancing the amount of fuel in the aircraft wing tank, the set time length S is 1 second.

[0038] Optionally, in the above-mentioned method for automatically balancing the fuel amount in the aircraft wing tank, the balance control threshold I is set to 200 kg.

[0039] This application has at least the following beneficial technical effects:

[0040] Provided is a method for automatically balancing the amount of fuel in aircraft wing tanks. The method is based on an automatic balancing system for the amount of fuel in aircraft wing tanks. A balancing monitor automatically performs balancing according to set logic, without manual intervention. The method can quickly and in real time control the fuel amounts in three wing tanks within an average fuel amount M±300kg, and the fuel amount in the other wing tank within an average fuel amount M±900kg. The method can also control accuracy by adjusting the balance adjustment threshold H and the balance control threshold I, thereby meeting the accuracy requirements of fuel imbalance control for different aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0041] Figure 1 is a schematic diagram of an automatic fuel balancing system in an aircraft wing tank provided by an embodiment of the present application;

[0042] Figure 2 2 is a schematic diagram of a method for automatically balancing the amount of fuel in an aircraft wing tank provided by an embodiment of the present application;

[0043] in:

[0044] 1-Wing fuel tank; 2-Balanced fuel pump; 3-Balanced control valve; 4-Balanced transfer pipeline; 5-Balanced monitor; 6-Flight control system.

[0045] In order to better illustrate this embodiment, some parts of the drawings may be omitted, enlarged or reduced, and do not represent the size of the actual product. In addition, the drawings are only used for illustrative purposes and should not be understood as limiting this application. DETAILED DESCRIPTION

[0046] To make the technical solution and its advantages of this application more clear, the technical solution of this application will be further described in detail below with reference to the accompanying drawings. It should be understood that the specific embodiments described here are only some of the embodiments of this application and are only used to explain this application, not to limit this application. It should be noted that for ease of description, only the parts relevant to this application are shown in the accompanying drawings, and other relevant parts can refer to the general design.

[0047] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application should have the usual meanings understood by those skilled in the art in the field to which this application belongs. The words indicating orientation used in the description of this application are only used to indicate relative directions or positional relationships. When the absolute position of the described object changes, its relative positional relationship may also change accordingly. The word "include" used in the description of this application means that the elements or objects appearing before the word include the elements or objects listed after the word and their equivalents, but does not exclude other elements or objects.

[0048] In addition, it should be noted that, unless otherwise clearly stipulated and limited, the words "installation", "connection" and similar terms used in the description of this application should be understood in a broad sense. For example, the connection can be a fixed connection or a detachable connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium. Technical personnel in the field can understand its specific meaning in this application according to the specific circumstances.

[0049] On one hand, the present application provides an automatic balancing system for the amount of fuel in an aircraft wing tank, wherein there are four wing tanks 1, symmetrically distributed in the left and right wings, and the automatic balancing system for the amount of fuel in the aircraft wing tank includes four balancing oil pumps 2, four balancing control valves 3, a balancing transfer pipeline 4, and a balancing monitor 5. Figure 1 shown.

[0050] Four balancing oil pumps 2 and balancing control valves 3 are arranged in four wing oil tanks 1 and are connected to the balancing transfer pipeline 4 through pipelines respectively.

[0051] The balancing monitor 5 is connected to the four balancing oil pumps 2, the balancing control valve 3, and the flight control system 6 to obtain fuel-related parameters in the four wing tanks 1, such as temperature, pressure, and liquid level, so as to calculate the fuel quantity in the four wing tanks 1. Furthermore, by controlling the switching of the four balancing oil pumps 2 and the balancing control valve 3 and utilizing the balancing transfer pipeline 4, the fuel quantity in the four wing tanks 1 can be quickly balanced.

[0052] On the other hand, the present application provides a method for automatically balancing the amount of fuel in an aircraft wing tank, based on the automatic balancing system for the amount of fuel in an aircraft wing tank disclosed in the above embodiment. Figure 2 Shown, including:

[0053] Step 1: Calculate the fuel quantity in the four wing tanks 1 to obtain the average fuel quantity M, and then proceed to step 2.

[0054] Step 2: Determine whether any wing tank 1 is low on fuel. If so, proceed to Step 3; if not, proceed to Step 6. A wing tank 1 low on fuel refers to one whose internal fuel level is less than the average fuel level M, and the amount of this level of fuel is greater than a balance adjustment threshold H, and the duration of this level of fuel is greater than a set duration S. Specifically, the balance adjustment threshold H can be 300 kg, and the set duration S can be 1 second.

[0055] Step 3: Close the balancing oil pump 2 in the wing tank 1 with low fuel level, and open the balancing control valve 3 in the wing tank 1 with low fuel level, and proceed to step 4.

[0056] Step 4: Determine whether the fuel level in the low-fuel wing tank 1 is within the range of the average fuel level M ± the balance control threshold I, and whether the duration is greater than the set time S. If so, proceed to Step 5; if not, proceed to Step 6. The balance control threshold I is less than the balance adjustment threshold H, which can be 200 kg.

[0057] Step 5: Close the balancing control valve 3 in the wing tank 1 with low fuel quantity and proceed to step 6.

[0058] Step 6: Determine whether there is a wing tank 1 with a high fuel level. If so, proceed to Step 7; if not, proceed to Step 8. A wing tank 1 with a high fuel level refers to a wing tank 1 whose internal fuel level is greater than the average fuel level M, and whose internal fuel level is greater than the balance adjustment threshold H, and whose internal fuel level remains greater than the set time duration S.

[0059] Step 7: Close the balancing control valve 3 in the wing tank 1 with a high fuel volume, and open the balancing oil pump 2 in the wing tank 1 with a high fuel volume to proceed to step 8.

[0060] Step 8: Determine whether the fuel levels in any three wing tanks 1 are within the range of the average fuel level M ± the balancing control threshold I, and for a duration greater than the set time S. If so, close all balancing fuel pumps 2 and balancing control valves 3 to complete the balancing of the fuel levels in the wing tanks 1. If not, proceed to step 4.

[0061] In a specific example, the four wing fuel tanks 1 are fuel tank 1, fuel tank 2, fuel tank 3, and fuel tank 4, respectively, with internal fuel capacities of 11,000 kg, 10,000 kg, 90,000 kg, and 10,000 kg. The automatic fuel balancing method for aircraft wing fuel tanks disclosed in the above embodiment is used for balancing, specifically as follows:

[0062] a. Calculate the fuel quantity in the four wing tanks 1 and obtain the average fuel quantity M = 10,000 kg.

[0063] b. Determine that fuel tank No. 3 is wing tank 1 with low fuel level.

[0064] c. Close the balancing oil pump 2 in the No. 3 oil tank and open the balancing control valve 3 in the No. 3 oil tank.

[0065] d. Determine that the fuel level in tank 3 is not within the average fuel level M ± the balance control threshold I = 200 kg.

[0066] e. Determine that fuel tank No. 1 is wing tank 1 with a high fuel level.

[0067] f. Close the balancing control valve 3 in the No. 1 tank and open the balancing oil pump 2 in the No. 1 tank. At this time, the fuel in the No. 1 tank will be transferred to the No. 3 tank through the balancing transfer pipeline 4.

[0068] g. Determine that the fuel levels in none of the three wing tanks 1 are within the range of the average fuel level M ± the balancing control threshold I for a duration greater than the set duration S = 1 second. Because this duration is too short, continue to transfer the fuel in tank 1 to tank 3 via balancing transfer line 4 until the fuel level in tank 1 reaches 10,300 kg. The fuel levels in tanks 1, 2, 3, and 4 are 10,300 kg, 10,000 kg, 9,700 kg, and 10,000 kg, respectively. Close all balancing pumps 2 and balancing control valves 3, and the balancing monitor 5 reports "Fuel Balanced."

[0069] In another specific example, the four wing fuel tanks 1 are fuel tank 1, fuel tank 2, fuel tank 3, and fuel tank 4, respectively, with internal fuel capacities of 11,000 kg, 9,000 kg, 120,000 kg, and 8,000 kg. The fuel capacities in the wing fuel tanks of an aircraft disclosed in the above embodiment are balanced as follows:

[0070] a. Calculate the fuel quantity in the four wing tanks 1 and obtain the average fuel quantity M = 10,000 kg.

[0071] b. Determine that the No. 2 and No. 4 fuel tanks are low on fuel, and that the wing fuel tank 1 is low on fuel.

[0072] c. Turn off the balancing oil pump 2 in the No. 2 and No. 4 oil tanks, and open the balancing control valve 3 in the No. 2 and No. 4 oil tanks.

[0073] d. Determine whether the fuel levels in tanks 2 and 4 are within the average fuel level M ± the balance control threshold I = 200 kg.

[0074] e. Determine that No. 1 and No. 3 fuel tanks are wing tanks 1 with high fuel levels.

[0075] f. Close the balancing control valve 3 in the No. 1 and No. 3 fuel tanks, and open the balancing oil pump 2 in the No. 1 and No. 3 fuel tanks. At this time, the fuel in the No. 1 and No. 3 fuel tanks will be transferred to the No. 2 and No. 4 fuel tanks through the balancing transfer pipeline 4.

[0076] g. Determine whether the fuel levels in any of the three wing tanks 1 are within the range of the average fuel level M ± the balancing control threshold I for a duration greater than the set duration S = 1 second. Because this duration is too short, fuel must continue to be transferred from tanks 1 and 3 to tanks 2 and 4 via balancing transfer pipeline 4. When the fuel level in tank 2 reaches 9,800 kg, the balancing control valve 3 in tank 2 is closed. When the fuel level in tank 1 reaches 10,300 kg, the balancing pump 2 in tank 2 is closed. When the fuel level in tank 3 reaches 10,300 kg, the balancing pump 2 in tank 3 is closed. At this point, the fuel level in tank 4 is 9,600 kg. All balancing pumps 2 and balancing control valves 3 are closed, and the balancing monitor 5 reports "Fuel Balanced."

[0077] The method for automatically balancing the fuel level in aircraft wing tanks disclosed in the above-mentioned embodiment is implemented based on the automatic balancing system for the fuel level in aircraft wing tanks disclosed in the above-mentioned embodiment. The balancing monitor 5 automatically performs balancing according to a set logic, without manual intervention. The fuel level in three of the wing tanks 1 can be quickly and in real time controlled to within an average fuel level M ± 300 kg, and the fuel level in the other wing tank 1 can be controlled to within an average fuel level M ± 900 kg. The accuracy can also be controlled by adjusting the balance adjustment threshold H and the balance control threshold I to meet the accuracy requirements of fuel imbalance control for different aircraft.

[0078] So far, the technical solution of the present application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of the present application is obviously not limited to these specific embodiments. Without departing from the principles of the present application, those skilled in the art can make equivalent changes or replacements to the relevant technical features, and the technical solutions after these changes or replacements will fall within the scope of protection of the present application.

Claims

1. A method for automatically balancing the amount of fuel in an aircraft wing tank, which is implemented based on an automatic balancing system for the amount of fuel in an aircraft wing tank. The automatic balancing system for the amount of fuel in an aircraft wing tank comprises four balancing oil pumps (2), four balancing control valves (3), a balancing transfer pipeline (4), and a balancing monitor (5); Four balanced oil transfer pumps (2) and balanced control valves (3) are arranged in the four wing oil tanks (1) and are connected to the balanced transfer pipelines (4) through pipelines respectively; The balance monitor (5) is connected to the four balancing oil pumps (2), the balancing control valve (3), and the flight control system (6) so as to obtain the fuel-related parameters in the four wing oil tanks (1), thereby being able to calculate the fuel amount in the four wing oil tanks (1), and then being able to balance the fuel amount in the four wing oil tanks (1) by controlling the switches of the four balancing oil pumps (2) and the balancing control valve (3) and utilizing the balancing transfer pipeline (4); The method for automatically balancing the amount of fuel in an aircraft wing tank is characterized in that: include: Step 1: Calculate the fuel quantity in the four wing fuel tanks (1) to obtain the average fuel quantity M, and proceed to step 2; Step 2: Determine whether there is a wing tank (1) with low fuel level. If yes, proceed to step 3; if not, proceed to step 6, wherein the wing tank (1) with low fuel level refers to a wing tank (1) whose internal fuel level is less than the average fuel level M, and the amount of the internal fuel level is greater than the balance adjustment threshold H, and the duration is greater than the set time length S; Step 3: close the balancing oil pump (2) in the low-fuel wing tank (1), and open the balancing control valve (3) in the low-fuel wing tank (1), and proceed to step 4; Step 4: Determine whether the fuel level in the low-fuel wing tank (1) is within the range of the average fuel level M ± the balance control threshold I, and whether the duration is greater than the set time S. If so, proceed to step 5; if not, proceed to step 6, wherein the balance control threshold I < the balance adjustment threshold H; Step 5: Close the balance control valve (3) in the wing tank (1) with low fuel quantity and proceed to step 6; Step 6: Determine whether there is a wing tank (1) with a high fuel volume. If so, proceed to step 7; if not, proceed to step 8, wherein the wing tank (1) with a high fuel volume refers to a wing tank (1) whose internal fuel volume is greater than the average fuel volume M, and the amount of the fuel volume is greater than the balance adjustment threshold H, and the duration is greater than the set time length S; Step 7: Close the balancing control valve (3) in the wing tank (1) with a high fuel volume, and open the balancing oil pump (2) in the wing tank (1) with a high fuel volume, and proceed to step 8; Step 8: Determine whether the fuel amount in any of the three wing fuel tanks (1) is within the range of the average fuel amount M ± the balance control threshold I, and the duration is greater than the set time S. If so, close all the balancing fuel pumps (2) and the balancing control valves (3) to complete the balancing of the fuel amount in the wing fuel tanks (1). If not, proceed to step 4.

2. The method for automatically balancing the amount of fuel in an aircraft wing tank according to claim 1, characterized in that: The balance adjustment threshold H is 300kg.

3. The method for automatically balancing the amount of fuel in an aircraft wing tank according to claim 2, characterized in that: Set the duration S to 1s.

4. The method for automatically balancing the amount of fuel in an aircraft wing tank according to claim 3, characterized in that: The balance control threshold I is set to 200 kg.

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