Method and system for actively controlling the center of gravity of an aircraft

Abstract

The present invention relates to a method and system for actively controlling the center of gravity of an aircraft. The method comprises: obtaining the heading center of gravity of a rear water tank and a front water tank on the aircraft, and the heading center of gravity of a front waste water tank and a rear waste water tank on the aircraft before the aircraft takes off; setting the target heading center of gravity of the aircraft according to the flight characteristics of the aircraft; during the flight, when the center of gravity of the aircraft changes, calculating the center of gravity difference ΔX between the current heading center of gravity of the aircraft and the target heading center of gravity CG ;When ΔX CG <0, the water in the front water tank is consumed by the user, and the waste water in the user is discharged into the rear waste water tank; when ΔX CG >0, the water in the rear water tank is consumed into the user, and the waste water in the user is discharged into the front waste water tank. According to the above technical scheme, the present invention can achieve the following beneficial technical effects: the method and system are simple and reliable, and it is easy to keep the center of gravity of the aircraft within the expected ideal range.

Description

Technical Field

[0001] The present invention relates to the technical field of overall aircraft design, and in particular to a method and system for actively controlling the center of gravity of an aircraft. Background Art

[0002] The center of gravity of an aircraft is an important parameter of the aircraft, which seriously affects the performance, maneuverability and stability of the aircraft. Controlling the center of gravity of the aircraft is a major link in the aircraft design process. During the flight of the aircraft, controlling the center of gravity of the aircraft to be in the rear area of ​​the center of gravity envelope is conducive to reducing the horizontal tail balance resistance, reducing fuel consumption and improving fuel economy.

[0003] However, in the prior art, the control of the center of gravity of the aircraft is often achieved by setting a counterweight device, which cannot actively control the center of gravity of the aircraft during flight, and it is difficult to keep the center of gravity of the aircraft within the expected ideal range. Summary of the invention

[0004] An object of the present invention is to provide a method and system for actively controlling the center of gravity of an aircraft, which can overcome the deficiencies of the prior art, and the method and system are simple and reliable, and can easily keep the center of gravity of the aircraft within a desired ideal range.

[0005] The above object of the present invention is achieved by a method for actively controlling the center of gravity of an aircraft, the method comprising:

[0006] Step 1: Before the aircraft takes off, obtain the heading center of gravity X of the rear water tank and the front water tank on the aircraft. CG01 and X CG02 , and the heading center of gravity X of the front waste water tank and the rear waste water tank on the aircraft CG03 and X CG04 , wherein the rear water tank is arranged at the rear of the aircraft, the front water tank is arranged at the front of the aircraft, the front waste water tank is arranged at the front of the aircraft, and the rear waste water tank is arranged at the rear of the aircraft;

[0007] Step 2: Set the target heading center of gravity X of the aircraft according to the flight characteristics of the aircraft. CG ;

[0008] Step 3: During flight, when the aircraft's center of gravity changes, obtain the aircraft's current heading center of gravity X CG1 and the total weight W of the aircraft, and calculate the current heading center of gravity X of the aircraft CG1 With the target heading center X CG The difference in center of gravity between CG , where ΔX CG =X CG1 -X CG ;

[0009] Step 41: When ΔX CGWhen the aircraft center of gravity is forward, the water in the front water tank is consumed into the user, and the waste water in the user is discharged into the rear waste water tank;

[0010] Step 42, when ΔX CG >0, the center of gravity of the aircraft moves backward, the water in the rear water tank is consumed into the user, and the waste water in the user is discharged into the front waste water tank.

[0011] According to the above technical scheme, the method of actively controlling the center of gravity of an aircraft of the present invention can achieve the following beneficial technical effects: the method and system are simple and reliable, and it is easy to keep the center of gravity of the aircraft within the expected ideal range, thereby ensuring flight safety while improving the flight performance of the aircraft.

[0012] Preferably, in step 41, the amount of water consumed in the front water tank is W 02 Equal to the amount of waste water W discharged into the rear waste water tank 04 , W 02 and W 04 Calculate using the following moment balance formula

[0013] ΔX CG *W=W 02 *(X CG05 -X CG02 )+W 04 *(X CG04 -X CG05 )

[0014] Among them, X CG05 It is the heading center of gravity of the user on the aircraft;

[0015] In step 42, the amount of water consumed in the rear water tank W 01 Equal to the amount of wastewater W discharged into the front wastewater tank 03 , W 01 and W 03 Calculate using the following moment balance formula

[0016] ΔX CG *W=W 01 *(X CG05 -X CG01 )+W 03 *(X CG03 -X CG05 ).

[0017] According to the above technical solution, the method of actively controlling the center of gravity of an aircraft of the present invention can achieve the following beneficial technical effects: it can more easily actively adjust the center of gravity of the aircraft and more easily keep the center of gravity of the aircraft within the expected ideal range.

[0018] Preferably, when the center of gravity difference ΔX CGThe step 41 or the step 42 is executed only when the absolute value of is greater than the set center of gravity deviation threshold.

[0019] According to the above technical scheme, the method of actively controlling the center of gravity of an aircraft of the present invention can achieve the following beneficial technical effects: during the flight of the aircraft, the center of gravity of the aircraft is controlled to be in the expected ideal area in the center of gravity envelope, which is beneficial to reducing the horizontal tail balancing resistance, reducing fuel consumption, and improving fuel economy; at the same time, a center of gravity deviation threshold is set to achieve active adjustment of the center of gravity of the aircraft without being too frequent, which not only ensures that the center of gravity of the aircraft is maintained within the expected ideal range, but also saves water consumption on the aircraft.

[0020] Preferably, the rear water tank is connected to the user via a rear water supply pipeline, the front water tank is connected to the user via a front water supply pipeline, the front wastewater tank is connected to the user via a front drainage pipeline, and the rear wastewater tank is connected to the user via a rear drainage pipeline.

[0021] According to the above technical scheme, the method of actively controlling the center of gravity of an aircraft of the present invention can achieve the following beneficial technical effects: through suitable water supply pipelines and drainage pipelines, the center of gravity of the aircraft can be better actively adjusted, and it is easier to keep the center of gravity of the aircraft within the expected ideal range.

[0022] Preferably, the amount of water consumed in the front water tank is W 02 The amount of waste water W discharged into the rear waste water tank is controlled by the front water supply flow meter and the front water supply control valve arranged in the front water supply pipeline. 04 Controlled by a rear drainage flow meter and a rear drainage control valve disposed in the rear drainage pipeline;

[0023] The amount of water consumed in the rear water tank W 01 The amount of waste water W discharged into the front waste water tank is controlled by a rear water supply flow meter and a rear water supply control valve arranged in the rear water supply pipeline. 03 It is controlled by a front drainage flow meter and a front drainage control valve arranged in the front drainage pipeline.

[0024] According to the above technical scheme, the method of actively controlling the center of gravity of an aircraft of the present invention can achieve the following beneficial technical effects: through appropriate flow meters and control valves, the center of gravity of the aircraft can be actively adjusted more accurately, and it is easier to keep the center of gravity of the aircraft within the expected ideal range.

[0025] Preferably, the method for actively controlling the center of gravity of the aircraft also includes: step five, checking the center of gravity change result of the movement of water and wastewater by calculating the torque change of each water tank and wastewater tank.

[0026] According to the above technical solution, the method of actively controlling the center of gravity of an aircraft of the present invention can achieve the following beneficial technical effects: by testing the change of the center of gravity, it is further ensured that the center of gravity of the aircraft is maintained within the expected ideal range.

[0027] The above object of the present invention is also achieved by a system for actively controlling the center of gravity of an aircraft, the system comprising:

[0028] The water tank waste water tank center of gravity acquisition module is configured to obtain the heading center of gravity X of the rear water tank and the front water tank on the aircraft before the aircraft takes off. CG01 and X CG02 , and the heading center of gravity X of the front waste water tank and the rear waste water tank on the aircraft CG03 and X CG04 , wherein the rear water tank is arranged at the rear of the aircraft, the front water tank is arranged at the front of the aircraft, the front waste water tank is arranged at the front of the aircraft, and the rear waste water tank is arranged at the rear of the aircraft;

[0029] A target heading center of gravity setting module, wherein the target heading center of gravity setting module is configured to set the target heading center of gravity X of the aircraft according to the flight characteristics of the aircraft. CG ;

[0030] The center of gravity difference calculation module is configured to obtain the current heading center of gravity X of the aircraft when the center of gravity of the aircraft changes during flight. CG1 and the total weight W of the aircraft, and calculate the current heading center of gravity X of the aircraft CG1 With the target heading center X CG The difference in center of gravity between CG , where ΔX CG =X CG1 -X CG ;

[0031] The water and wastewater control module is configured to: CG When the aircraft center of gravity is forward, the water in the front water tank is consumed into the user, and the waste water in the user is discharged into the rear waste water tank;

[0032] When ΔX CG >0, the center of gravity of the aircraft moves backward, the water in the rear water tank is consumed into the user, and the waste water in the user is discharged into the front waste water tank.

[0033] According to the above technical scheme, the system for actively controlling the center of gravity of an aircraft of the present invention can achieve the following beneficial technical effects: the method and system are simple and reliable, and can easily keep the center of gravity of the aircraft within the expected ideal range, thereby ensuring flight safety while improving the flight performance of the aircraft.

[0034] Preferably, when ΔX CG <0, the amount of water consumed in the front water tank W 02 Equal to the amount of waste water W discharged into the rear waste water tank 04 , W 02 and W 04 Calculate using the following moment balance formula

[0035] ΔX CG *W=W 02 *(X CG05 -X CG02 )+W 04 *(X CG04 -X CG05 )

[0036] Among them, X CG05 It is the heading center of gravity of the user on the aircraft;

[0037] When ΔX CG >0, the amount of water consumed in the rear water tank W 01 Equal to the amount of wastewater W discharged into the front wastewater tank 03 , W 01 and W 03 Calculate using the following moment balance formula

[0038] ΔX CG *W=W 01 *(X CG05 -X CG01 )+W 03 *(X CG03 -X CG05 ).

[0039] According to the above technical solution, the system for actively controlling the center of gravity of an aircraft of the present invention can achieve the following beneficial technical effects: it can more easily actively adjust the center of gravity of the aircraft and more easily keep the center of gravity of the aircraft within the expected ideal range.

[0040] Preferably, when the center of gravity difference ΔX CG The water and wastewater volume control module is started only when the absolute value of is greater than the set center of gravity deviation threshold.

[0041] According to the above technical scheme, the system for actively controlling the center of gravity of an aircraft of the present invention can achieve the following beneficial technical effects: during the flight of the aircraft, the center of gravity of the aircraft is controlled to be in the expected ideal area in the center of gravity envelope, which is beneficial to reducing the horizontal tail balancing resistance, reducing fuel consumption, and improving fuel economy; at the same time, a center of gravity deviation threshold is set to achieve active adjustment of the center of gravity of the aircraft without being too frequent, which not only ensures that the center of gravity of the aircraft is maintained within the expected ideal range, but also saves water consumption on the aircraft.

[0042] Preferably, the rear water tank is connected to the user via a rear water supply pipeline, the front water tank is connected to the user via a front water supply pipeline, the front wastewater tank is connected to the user via a front drainage pipeline, and the rear wastewater tank is connected to the user via a rear drainage pipeline.

[0043] According to the above technical scheme, the system for actively controlling the center of gravity of an aircraft of the present invention can achieve the following beneficial technical effects: through suitable water supply pipelines and drainage pipelines, the center of gravity of the aircraft can be better actively adjusted, and it is easier to keep the center of gravity of the aircraft within the expected ideal range.

[0044] Preferably, the amount of water consumed in the front water tank is W 02 The amount of waste water W discharged into the rear waste water tank is controlled by the front water supply flow meter and the front water supply control valve arranged in the front water supply pipeline. 04 Controlled by a rear drainage flow meter and a rear drainage control valve disposed in the rear drainage pipeline;

[0045] The amount of water consumed in the rear water tank W 01 The amount of waste water W discharged into the front waste water tank is controlled by a rear water supply flow meter and a rear water supply control valve arranged in the rear water supply pipeline. 03 It is controlled by a front drainage flow meter and a front drainage control valve arranged in the front drainage pipeline.

[0046] According to the above technical scheme, the system for actively controlling the center of gravity of an aircraft of the present invention can achieve the following beneficial technical effects: through appropriate flow meters and control valves, the center of gravity of the aircraft can be actively adjusted more accurately, and it is easier to keep the center of gravity of the aircraft within the expected ideal range.

[0047] Preferably, the system for actively controlling the center of gravity of the aircraft also includes: a center of gravity change detection module, which is configured to detect the center of gravity change result of water and wastewater movement by calculating the torque change of each water tank and wastewater tank.

[0048] According to the above technical solution, the system for actively controlling the center of gravity of an aircraft of the present invention can achieve the following beneficial technical effects: by testing the change of the center of gravity, it is further ensured that the center of gravity of the aircraft is maintained within the expected ideal range. BRIEF DESCRIPTION OF THE DRAWINGS

[0049] Figure 1A and Figure 1B The present invention is a schematic diagram of the arrangement of a water tank and a waste water tank in a method and system for actively controlling the center of gravity of an aircraft according to an embodiment of the present invention.

[0050] Figure 2 It is a schematic diagram of the pipelines of a water tank and a waste water tank in a method and system for actively controlling the center of gravity of an aircraft according to an embodiment of the present invention.

[0051] Figure 3 The figure is a flow chart of a method for actively controlling the center of gravity of an aircraft according to an embodiment of the present invention.

[0052] Figure 4 Schematic diagram of a system for actively controlling the center of gravity of an aircraft according to an embodiment of the present invention.

[0053] Reference numerals list

[0054] 01. Rear water tank;

[0055] 02. Front water tank;

[0056] 03. Front waste water tank;

[0057] 04. Rear waste water tank;

[0058] 05. User;

[0059] 06. Rear water supply pipeline;

[0060] 07. Rear drainage pipeline;

[0061] 08. Front water supply flow meter;

[0062] 09. Rear water supply flow meter;

[0063] 10. Front drainage flow meter;

[0064] 11. Rear drainage flow meter;

[0065] 12. Front water supply control valve;

[0066] 13. Rear water supply control valve;

[0067] 14. Front drainage control valve;

[0068] 15. Rear drainage control valve;

[0069] 16. Front water supply pipeline;

[0070] 17. Front drainage pipe. DETAILED DESCRIPTION

[0071] The specific embodiments of the present invention will be described below. It should be noted that in the specific description of these embodiments, in order to be concise and clear, this specification cannot provide a detailed description of all the features of the actual embodiments. It should be understood that in the actual implementation of any embodiment, just as in the process of any engineering project or design project, in order to achieve the specific goals of the developer and to meet system-related or business-related restrictions, various specific decisions are often made, and this will also change from one embodiment to another. In addition, it can also be understood that although the efforts made in this development process may be complex and lengthy, for ordinary technicians in the field related to the content disclosed by the present invention, some changes in design, manufacturing or production based on the technical content disclosed in this disclosure are just conventional technical means, and should not be understood as insufficient content of this disclosure.

[0072] Unless otherwise defined, the technical or scientific terms used in the claims and the specification shall have the usual meaning understood by persons with ordinary skills in the technical field to which the invention belongs. The words "first", "second" and similar words used in the patent application specification and the claims of the present invention do not indicate any order, quantity or importance, but are only used to distinguish different components. "One" or "one" and other similar words do not indicate a quantitative limitation, but indicate the existence of at least one. "Include" or "comprises" and other similar words mean that the elements or objects appearing before "include" or "comprises" include the elements or objects listed after "include" or "comprises" and their equivalent elements, and do not exclude other elements or objects. "Connected" or "connected" and other similar words are not limited to physical or mechanical connections, nor are they limited to direct or indirect connections.

[0073] Figure 1A and Figure 1B The present invention is a schematic diagram of the arrangement of a water tank and a waste water tank in a method and system for actively controlling the center of gravity of an aircraft according to an embodiment of the present invention. Figure 2 It is a schematic diagram of the pipelines of a water tank and a waste water tank in a method and system for actively controlling the center of gravity of an aircraft according to an embodiment of the present invention. Figure 3 The figure is a flow chart of a method for actively controlling the center of gravity of an aircraft according to an embodiment of the present invention. Figure 4 Schematic diagram of a system for actively controlling the center of gravity of an aircraft according to an embodiment of the present invention.

[0074] like Figures 1A to 3 As shown, according to one embodiment of the present invention, a method for actively controlling the center of gravity of an aircraft includes:

[0075] Step 1: Before the aircraft takes off, obtain the heading center of gravity X of the rear water tank (also called "rear water supply tank") 01 and the front water tank (also called "front water supply tank") 02 on the aircraft. CG01 and X CG02 , and the heading center of gravity X of the front waste water tank 03 and the rear waste water tank 04 on the aircraft CG03 and X CG04 , wherein the rear water tank 01 is arranged at the rear of the aircraft, the front water tank 02 is arranged at the front of the aircraft, the front waste water tank 03 is arranged at the front of the aircraft, and the rear waste water tank 04 is arranged at the rear of the aircraft;

[0076] Step 2: Set the target heading center of gravity X of the aircraft according to the flight characteristics of the aircraft. CG ;

[0077] Step 3: During flight, when the aircraft's center of gravity changes, obtain the aircraft's current heading center of gravity X CG1 and the total weight W of the aircraft, and calculate the current heading center of gravity X of the aircraft CG1 With the target heading center X CG The difference in center of gravity between CG , where ΔX CG =X CG1 -X CG ;

[0078] Step 41: When ΔX CG When <0, the center of gravity of the aircraft is forward, the water in the front water tank 02 is consumed to the user (also called "user area") 05, and the waste water in the user 05 is discharged to the rear waste water tank 04;

[0079] Step 42, when ΔX CG When >0, the center of gravity of the aircraft moves backward, the water in the rear water tank 01 is consumed into the user 05, and the waste water in the user 05 is discharged into the front waste water tank 03.

[0080] According to the above technical scheme, the method of actively controlling the center of gravity of an aircraft of the present invention can achieve the following beneficial technical effects: the method and system are simple and reliable, and it is easy to keep the center of gravity of the aircraft within the expected ideal range, thereby ensuring flight safety while improving the flight performance of the aircraft.

[0081] Specifically, during flight, when the center of gravity of the aircraft changes, the order, final flow direction and amount of water in the water tank can be adjusted, and the order, final flow direction and amount of waste water discharged into the waste water tank can be adjusted to actively adjust and control the center of gravity of the aircraft, so that the center of gravity of the aircraft is stable within a certain range, and the measurement and calculation are automatically performed; the current heading center of gravity of the aircraft X CG1 With the target heading center X CGFor comparison, if the current center of gravity is forward of the target center of gravity, the center of gravity of the aircraft can be controlled to be stable at the target center of gravity X by consuming the water in the water tank 02 at the front of the aircraft into the user 05 and discharging the waste water in the user 05 into the waste water tank 04 at the rear of the aircraft. CG If the current center of gravity is behind the target center of gravity, the center of gravity of the aircraft can be controlled to stabilize at the target center of gravity X by consuming the water in the water tank 01 at the rear of the aircraft into the user 05 and discharging the waste water in the user 05 into the waste water tank 03 at the front of the aircraft. CG By actively adjusting the aircraft's center of gravity so that it is stable within a certain range, not only can flight safety be ensured, but also trim resistance can be reduced, fuel consumption can be reduced, and fuel economy can be improved.

[0082] In some embodiments, in step 41, the amount of water consumed in the front water tank 02 is W 02 Equal to the amount of waste water W discharged into the rear waste water tank 04 04 , W 02 and W 04 Calculate using the following moment balance formula

[0083] ΔX CG *W=W 02 *(X CG05 -X CG02 )+W 04 *(X CG04 -X CG05 )

[0084] Among them, X CG05 is the heading center of gravity of user 05 on the aircraft;

[0085] In step 42, the amount of water consumed in the rear water tank 01 is W 01 Equal to the amount of waste water W discharged into the front waste water tank 03 03 , W 01 and W 03 Calculate using the following moment balance formula

[0086] ΔX CG *W=W 01 *(X CG05 -X CG01 )+W 03 *(X CG03 -X CG05 ).

[0087] According to the above technical solution, the method of actively controlling the center of gravity of an aircraft of the present invention can achieve the following beneficial technical effects: it can more easily actively adjust the center of gravity of the aircraft and more easily keep the center of gravity of the aircraft within the expected ideal range.

[0088] In some embodiments, Figure 1A and Figure 1B As shown, the rear water tank 01, the front water tank 02, the front waste water tank 03 and the rear waste water tank 04 are arranged in the area of ​​the aircraft that has a greater impact on the center of gravity of the aircraft. According to the above technical solution, the method of actively controlling the center of gravity of the aircraft of the present invention can achieve the following beneficial technical effects: it can more easily actively adjust the center of gravity of the aircraft and more easily keep the center of gravity of the aircraft within the expected ideal range.

[0089] In some embodiments, for example, the front water tank 02 and the front waste water tank 03 are arranged in the front part of the front cargo hold of the aircraft, and the rear water tank 01 and the rear waste water tank 04 are arranged in the rear part of the rear cargo hold of the aircraft; for another example, the front water tank 02 and the front waste water tank 03 are arranged in the front service area of ​​the aircraft passenger cabin, and the rear water tank 01 and the rear waste water tank 04 are arranged in the rear service area of ​​the aircraft passenger cabin; for another example, the front water tank 02 and the front waste water tank 03 are arranged in the aircraft landing gear compartment, and the rear water tank 01 and the rear waste water tank 04 are arranged in the aircraft bulk cargo hold or water waste water tank.

[0090] In some embodiments, the rear water tank 01, the front water tank 02, the front waste water tank 03, and the rear waste water tank 04 are all provided with measuring sensors for measuring the volume of water in each water tank and waste water tank. The measurement results are V 01 、V 02 、V 03 、V 04 ; Multiply the volume of water by the density of water to get the weight of water in each water tank and wastewater tank.

[0091] In some embodiments, when the center of gravity difference ΔX CG Only when the absolute value of is greater than the set center of gravity deviation threshold, step 41 or step 42 is executed. According to the above technical solution, the method of actively controlling the center of gravity of the aircraft of the present invention can achieve the following beneficial technical effects: during the flight of the aircraft, the center of gravity of the aircraft is controlled to be in the expected ideal area in the center of gravity envelope, which is conducive to reducing the horizontal tail balancing resistance, reducing fuel consumption, and improving fuel economy; at the same time, the center of gravity deviation threshold is set to achieve active adjustment of the center of gravity of the aircraft not too frequently, which not only ensures that the center of gravity of the aircraft is kept within the expected ideal range, but also saves the consumption of water on the aircraft.

[0092] In some embodiments, Figure 2 As shown, the rear water tank 01 is connected to the user 05 via the rear water supply pipeline 06, the front water tank 02 is connected to the user 05 via the front water supply pipeline 16, the front waste water tank 03 is connected to the user 05 via the front drainage pipeline 17, and the rear waste water tank 04 is connected to the user 05 via the rear drainage pipeline 07. According to the above technical scheme, the method of actively controlling the center of gravity of the aircraft of the present invention can achieve the following beneficial technical effects: through appropriate water supply pipelines and drainage pipelines, the center of gravity of the aircraft can be better actively adjusted, and it is easier to keep the center of gravity of the aircraft within the expected ideal range.

[0093] In some embodiments, Figure 2 As shown, the amount of water consumed in the front water tank 02 is W 02 The amount of waste water W discharged into the rear waste water tank 04 is controlled by the front water supply flow meter 08 and the front water supply control valve 12 arranged in the front water supply pipeline 16. 04 The amount of water consumed in the rear water tank 01 is controlled by the rear drainage flow meter 11 and the rear drainage control valve 15 set in the rear drainage pipeline 07; 01 The amount of waste water W discharged into the front waste water tank 03 is controlled by the rear water supply flow meter 09 and the rear water supply control valve 13 set in the rear water supply pipeline 06. 03 It is controlled by the front drainage flowmeter 10 and the front drainage control valve 14 arranged in the front drainage pipeline 17. According to the above technical scheme, the method of actively controlling the center of gravity of the aircraft of the present invention can achieve the following beneficial technical effects: through the appropriate flowmeter and control valve, the center of gravity of the aircraft can be actively adjusted more accurately, and it is easier to keep the center of gravity of the aircraft within the expected ideal range.

[0094] In some embodiments, Figure 3 As shown, the method for actively controlling the center of gravity of the aircraft also includes: step 5, checking the center of gravity change result of the movement of water and wastewater by calculating the torque change of each water tank and wastewater tank. According to the above technical solution, the method for actively controlling the center of gravity of the aircraft of the present invention can achieve the following beneficial technical effects: through the center of gravity change test, it is further ensured that the center of gravity of the aircraft is kept within the expected ideal range.

[0095] In some embodiments, water measurement and flow direction are automatically calculated; in other embodiments, manual control by the pilot may also be provided.

[0096] like Figures 1A to 4 As shown, according to one embodiment of the present invention, a system for actively controlling the center of gravity of an aircraft includes:

[0097] The water tank waste water tank center of gravity acquisition module is configured to obtain the heading center of gravity X of the rear water tank 01 and the front water tank 02 on the aircraft before the aircraft takes off. CG01 and X CG02 , and the heading center of gravity X of the front waste water tank 03 and the rear waste water tank 04 on the aircraft CG03 and X CG04 , wherein the rear water tank 01 is arranged at the rear of the aircraft, the front water tank 02 is arranged at the front of the aircraft, the front waste water tank 03 is arranged at the front of the aircraft, and the rear waste water tank 04 is arranged at the rear of the aircraft;

[0098] The target heading center of gravity setting module is configured to set the target heading center of gravity X of the aircraft according to the flight characteristics of the aircraft. CG ;

[0099] The center of gravity difference calculation module is configured to obtain the current heading center of gravity X of the aircraft when the center of gravity of the aircraft changes during flight. CG1 and the total weight W of the aircraft, and calculate the current heading center of gravity X of the aircraft CG1 With the target heading center X CG The difference in center of gravity between CG , where ΔX CG =X CG1 -X CG ;

[0100] The water and wastewater control module is configured to: CG When <0, the center of gravity of the aircraft is forward, the water in the front water tank 02 is consumed into the user 05, and the waste water in the user 05 is discharged into the rear waste water tank 04;

[0101] When ΔX CG When >0, the center of gravity of the aircraft moves backward, the water in the rear water tank 01 is consumed into the user 05, and the waste water in the user 05 is discharged into the front waste water tank 03.

[0102] According to the above technical scheme, the system for actively controlling the center of gravity of an aircraft of the present invention can achieve the following beneficial technical effects: the method and system are simple and reliable, and can easily keep the center of gravity of the aircraft within the expected ideal range, thereby ensuring flight safety while improving the flight performance of the aircraft.

[0103] In some embodiments, when ΔX CG <0, the amount of water consumed in the front water tank 02 W 02 Equal to the amount of waste water W discharged into the rear waste water tank 04 04 , W 02 and W 04 Calculate using the following moment balance formula

[0104] ΔX CG *W=W 02 *(X CG05 -X CG02 )+W 04 *(X CG04 -X CG05 )

[0105] Among them, X CG05 is the heading center of gravity of user 05 on the aircraft;

[0106] When ΔX CG >0, the amount of water consumed in the rear water tank 01 is W01 Equal to the amount of waste water W discharged into the front waste water tank 03 03 , W 01 and W 03 Calculate using the following moment balance formula

[0107] ΔX CG *W=W 01 *(X CG05 -X CG01 )+W 03 *(X CG03 -X CG05 ).

[0108] According to the above technical solution, the system for actively controlling the center of gravity of an aircraft of the present invention can achieve the following beneficial technical effects: it can more easily actively adjust the center of gravity of the aircraft and more easily keep the center of gravity of the aircraft within the expected ideal range.

[0109] In some embodiments, when the center of gravity difference ΔX CG When the absolute value of is greater than the set center of gravity deviation threshold, the water and wastewater control module is started to adjust the order of consuming water in the water tank, the final flow direction and the water volume, and the order of discharging wastewater into the wastewater tank, the final flow direction and the wastewater volume. According to the above technical scheme, the system of actively controlling the center of gravity of the aircraft of the present invention can achieve the following beneficial technical effects: during the flight of the aircraft, the center of gravity of the aircraft is controlled to be in the expected ideal area in the center of gravity envelope, which is conducive to reducing the horizontal tail balancing resistance, reducing fuel consumption, and improving fuel economy; at the same time, the center of gravity deviation threshold is set to achieve active adjustment of the center of gravity of the aircraft not too frequently, which not only ensures that the center of gravity of the aircraft is kept within the expected ideal range, but also saves the consumption of water on the aircraft.

[0110] In some embodiments, Figure 4 As shown, the system for actively controlling the center of gravity of the aircraft also includes: a center of gravity change detection module, which is configured to detect the center of gravity change result of the movement of water and wastewater by calculating the moment change of each water tank and wastewater tank. According to the above technical solution, the system for actively controlling the center of gravity of the aircraft of the present invention can achieve the following beneficial technical effects: through the center of gravity change detection, it is further ensured that the center of gravity of the aircraft is kept within the expected ideal range.

[0111] The above describes the specific embodiments of the present invention, but those skilled in the art will understand that the above specific embodiments do not constitute a limitation of the present invention. Those skilled in the art can make various modifications based on the above disclosure without exceeding the scope of the present invention.

Claims

1. A method for actively controlling the center of gravity of an aircraft, comprising: Step 1: Before the aircraft takes off, obtain the heading center of gravity X of the rear water tank and the front water tank on the aircraft. CG01 and X CG02 , and the heading center of gravity X of the front waste water tank and the rear waste water tank on the aircraft CG03 and X CG04 , wherein the rear water tank is arranged at the rear of the aircraft, the front water tank is arranged at the front of the aircraft, the front waste water tank is arranged at the front of the aircraft, and the rear waste water tank is arranged at the rear of the aircraft; Step 2: Set the target heading center of gravity X of the aircraft according to the flight characteristics of the aircraft. CG ; Step 3: During flight, when the aircraft's center of gravity changes, obtain the aircraft's current heading center of gravity X CG1 and the total weight W of the aircraft, and calculate the current heading center of gravity X of the aircraft CG1 X CG The difference in center of gravity between CG , where ΔX CG =X CG1 -X CG ; Step 41: When ΔX CG When the aircraft center of gravity is forward, the water in the front water tank is consumed into the user, and the waste water in the user is discharged into the rear waste water tank; Step 42, when ΔX CG >0, the center of gravity of the aircraft is backward, the water in the rear water tank is consumed into the user, and the waste water in the user is discharged into the front waste water tank; In step 41, the amount of water consumed in the front water tank W 02 Equal to the amount of waste water W discharged into the rear waste water tank 04 , W 02 and W 04 Calculate using the following moment balance formula ΔX CG *W=W 02 *(X CG05 -X CG02 )+W 04 *(X CG04 -X CG05 ) Among them, X CG05 It is the heading center of gravity of the user on the aircraft; In step 42, the amount of water consumed in the rear water tank W 01 Equal to the amount of wastewater W discharged into the front wastewater tank 03 , W 01 and W 03 Calculate using the following moment balance formula ΔX CG *W=W 01 *(X CG05 -X CG01 )+W 03 *(X CG03 -X CG05 )。 2. The method for actively controlling the center of gravity of an aircraft as claimed in claim 1, characterized in that: When the center of gravity difference ΔX CG The step 41 or the step 42 is executed only when the absolute value of is greater than the set center of gravity deviation threshold.

3. The method for actively controlling the center of gravity of an aircraft as claimed in claim 1, characterized in that: The rear water tank is connected to the user via a rear water supply pipeline, the front water tank is connected to the user via a front water supply pipeline, the front waste water tank is connected to the user via a front drainage pipeline, and the rear waste water tank is connected to the user via a rear drainage pipeline.

4. The method for actively controlling the center of gravity of an aircraft as claimed in claim 3, characterized in that: The amount of water consumed in the front water tank W 02 The amount of waste water W discharged into the rear waste water tank is controlled by the front water supply flow meter and the front water supply control valve arranged in the front water supply pipeline. 04 Controlled by a rear drainage flow meter and a rear drainage control valve disposed in the rear drainage pipeline; The amount of water consumed in the rear water tank W 01 The amount of waste water W discharged into the front waste water tank is controlled by a rear water supply flow meter and a rear water supply control valve arranged in the rear water supply pipeline. 03 It is controlled by a front drainage flow meter and a front drainage control valve arranged in the front drainage pipeline.

5. The method for actively controlling the center of gravity of an aircraft as claimed in claim 1, characterized in that: The method also includes: Step 5, calculating the moment changes of each water tank and waste water tank to check the center of gravity change results of the water and waste water movement.

6. A system for actively controlling the center of gravity of an aircraft, comprising: The water tank waste water tank center of gravity acquisition module is configured to obtain the heading center of gravity X of the rear water tank and the front water tank on the aircraft before the aircraft takes off. CG01 and X CG02 , and the heading center of gravity X of the front waste water tank and the rear waste water tank on the aircraft CG03 and X CG04 , wherein the rear water tank is arranged at the rear of the aircraft, the front water tank is arranged at the front of the aircraft, the front waste water tank is arranged at the front of the aircraft, and the rear waste water tank is arranged at the rear of the aircraft; A target heading center of gravity setting module, wherein the target heading center of gravity setting module is configured to set the target heading center of gravity X of the aircraft according to the flight characteristics of the aircraft. CG ; The center of gravity difference calculation module is configured to obtain the current heading center of gravity X of the aircraft when the center of gravity of the aircraft changes during flight. CG1 and the total weight W of the aircraft, and calculate the current heading center of gravity X of the aircraft CG1 X CG The difference in center of gravity between CG , where ΔX CG =X CG1 -X CG ; The water and wastewater control module is configured to: CG When the aircraft center of gravity is forward, the water in the front water tank is consumed into the user, and the waste water in the user is discharged into the rear waste water tank; When ΔX CG >0, the center of gravity of the aircraft is backward, the water in the rear water tank is consumed into the user, and the waste water in the user is discharged into the front waste water tank; When ΔX CG <0, the amount of water consumed in the front water tank W 02 Equal to the amount of waste water W discharged into the rear waste water tank 04 , W 02 and W 04 Calculate using the following moment balance formula ΔX CG *W=W 02 *(X CG05 -X CG02 )+W 04 *(X CG04 -X CG05 ) Among them, X CG05 It is the heading center of gravity of the user on the aircraft; When ΔX CG >0, the amount of water consumed in the rear water tank W 01 Equal to the amount of wastewater W discharged into the front wastewater tank 03 , W 01 and W 03 Calculate using the following moment balance formula ΔX CG *W=W 01 *(X CG05 -X CG01 )+W 03 *(X CG03 -X CG05 )。 7. The system for actively controlling the center of gravity of an aircraft as claimed in claim 6, characterized in that: When the center of gravity difference ΔX CG The water and wastewater volume control module is started only when the absolute value of is greater than the set center of gravity deviation threshold.

8. The system for actively controlling the center of gravity of an aircraft as claimed in claim 6, characterized in that: The rear water tank is connected to the user via a rear water supply pipeline, the front water tank is connected to the user via a front water supply pipeline, the front waste water tank is connected to the user via a front drainage pipeline, and the rear waste water tank is connected to the user via a rear drainage pipeline.

9. The system for actively controlling the center of gravity of an aircraft as claimed in claim 8, characterized in that: The amount of water consumed in the front water tank W 02 The amount of waste water W discharged into the rear waste water tank is controlled by the front water supply flow meter and the front water supply control valve arranged in the front water supply pipeline. 04 Controlled by a rear drainage flow meter and a rear drainage control valve disposed in the rear drainage pipeline; The amount of water consumed in the rear water tank W 01 The amount of waste water W discharged into the front waste water tank is controlled by a rear water supply flow meter and a rear water supply control valve arranged in the rear water supply pipeline. 03 It is controlled by a front drainage flow meter and a front drainage control valve arranged in the front drainage pipeline.

10. The system for actively controlling the center of gravity of an aircraft as claimed in claim 6, characterized in that: Also includes: A center of gravity change detection module is configured to detect the center of gravity change result of water and wastewater movement by calculating the torque change of each water tank and wastewater tank.

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