WO2024082392A1 - Method and system for actively controlling center of gravity of aircraft - Google Patents
Method and system for actively controlling center of gravity of aircraft Download PDFInfo
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- WO2024082392A1 WO2024082392A1 PCT/CN2022/137115 CN2022137115W WO2024082392A1 WO 2024082392 A1 WO2024082392 A1 WO 2024082392A1 CN 2022137115 W CN2022137115 W CN 2022137115W WO 2024082392 A1 WO2024082392 A1 WO 2024082392A1
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- waste water
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- 230000005484 gravity Effects 0.000 title claims abstract description 246
- 238000000034 method Methods 0.000 title claims abstract description 44
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims abstract description 225
- 239000002351 wastewater Substances 0.000 claims abstract description 163
- 238000012795 verification Methods 0.000 claims 2
- 238000007599 discharging Methods 0.000 abstract description 4
- 230000009286 beneficial effect Effects 0.000 description 25
- 230000000694 effects Effects 0.000 description 23
- 239000000446 fuel Substances 0.000 description 12
- 238000010586 diagram Methods 0.000 description 6
- 238000013461 design Methods 0.000 description 3
- 238000001514 detection method Methods 0.000 description 3
- 238000005259 measurement Methods 0.000 description 3
- 101100012902 Saccharomyces cerevisiae (strain ATCC 204508 / S288c) FIG2 gene Proteins 0.000 description 2
- 101100233916 Saccharomyces cerevisiae (strain ATCC 204508 / S288c) KAR5 gene Proteins 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 238000012360 testing method Methods 0.000 description 2
- 101000827703 Homo sapiens Polyphosphoinositide phosphatase Proteins 0.000 description 1
- 102100023591 Polyphosphoinositide phosphatase Human genes 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000012938 design process Methods 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C17/00—Aircraft stabilisation not otherwise provided for
- B64C17/08—Aircraft stabilisation not otherwise provided for by ballast supply or discharge
Definitions
- 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.
- 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 trim resistance, reducing fuel consumption and improving fuel economy.
- 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.
- 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:
- Step 1 Before the aircraft takes off, obtain the heading center of gravity X CG01 and X CG02 of the rear water tank and the front water tank on the aircraft, as well as the heading center of gravity X CG03 and X CG04 of the front waste water tank and the rear waste water tank on the aircraft, 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 CG of the aircraft according to the flight characteristics of the aircraft;
- Step 41 when ⁇ X CG ⁇ 0, the center of gravity of the aircraft 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 ⁇ X 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.
- 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.
- the amount of water consumed in the front water tank W 02 is equal to the amount of waste water discharged into the rear waste water tank W 04 , and W 02 and W 04 are calculated by the following moment balance formula:
- X CG05 is the heading center of gravity of the user on the aircraft
- step 42 the amount of water consumed in the rear water tank W 01 is equal to the amount of waste water discharged into the front waste water tank W 03 , and W 01 and W 03 are calculated by the following moment balance formula:
- the method 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.
- the step 41 or the step 42 is performed only when the absolute value of the center of gravity difference ⁇ X CG is greater than a set center of gravity deviation threshold.
- 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 ensures that the center of gravity of the aircraft is kept within the expected ideal range and saves water consumption on the aircraft.
- 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
- the rear wastewater tank is connected to the user via a rear drainage pipeline.
- 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.
- the amount of water consumed in the front water tank W 02 is controlled by a front water supply flow meter and a front water supply control valve provided in the front water supply pipeline, and the amount of waste water discharged into the rear waste water tank W 04 is controlled by a rear drainage flow meter and a rear drainage control valve provided in the rear drainage pipeline;
- the amount of water W 01 consumed in the rear water tank is controlled by the rear water supply flowmeter and the rear water supply control valve arranged in the rear water supply pipeline, and the amount of waste water W 03 discharged into the front waste water tank is controlled by the front drainage flowmeter and the front drainage control valve arranged in the front drainage pipeline.
- 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.
- 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.
- the method of actively controlling the center of gravity of an aircraft of the present invention can achieve the following beneficial technical effects: by checking 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.
- a water tank and waste water tank center of gravity acquisition module wherein the water tank and waste water tank center of gravity acquisition module is configured to acquire the heading centers of gravity X CG01 and X CG02 of the rear water tank and the front water tank on the aircraft, and the heading centers of gravity X CG03 and X CG04 of the front waste water tank and the rear waste water tank on the aircraft before the aircraft takes off, 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 CG of the aircraft according to the flight characteristics of the aircraft;
- a water and wastewater control module configured to, when ⁇ X CG ⁇ 0, the center of gravity of the aircraft is forward, consume water in the front water tank into the user, and discharge wastewater in the user into the rear wastewater tank;
- 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.
- the amount of water consumed in the front water tank W 02 is equal to the amount of waste water discharged into the rear waste water tank W 04 , and W 02 and W 04 are calculated by the following moment balance formula:
- X CG05 is the heading center of gravity of the user on the aircraft
- 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.
- the water and wastewater control module is activated only when the absolute value of the center of gravity difference ⁇ X CG is greater than a set center of gravity deviation threshold.
- 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 ensures that the center of gravity of the aircraft is maintained within the expected ideal range and saves water consumption on the aircraft.
- 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
- the rear wastewater tank is connected to the user via a rear drainage pipeline.
- 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.
- the amount of water consumed in the front water tank W 02 is controlled by a front water supply flow meter and a front water supply control valve provided in the front water supply pipeline, and the amount of waste water discharged into the rear waste water tank W 04 is controlled by a rear drainage flow meter and a rear drainage control valve provided in the rear drainage pipeline;
- the amount of water W 01 consumed in the rear water tank is controlled by the rear water supply flowmeter and the rear water supply control valve arranged in the rear water supply pipeline, and the amount of waste water W 03 discharged into the front waste water tank is controlled by the front drainage flowmeter and the front drainage control valve arranged in the front drainage pipeline.
- 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.
- 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.
- 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.
- 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.
- FIGS. 1A and 1B are schematic diagrams showing 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.
- FIG. 2 is a schematic diagram of the piping 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.
- FIG3 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.
- FIG. 4 is a schematic diagram of a system for actively controlling the center of gravity of an aircraft according to an embodiment of the present invention.
- Fig. 1A and Fig. 1B are schematic diagrams of the arrangement of water tanks and waste water tanks in a method and system for actively controlling the center of gravity of an aircraft according to an embodiment of the present invention.
- Fig. 2 is a schematic diagram of the piping of water tanks and waste water tanks in a method and system for actively controlling the center of gravity of an aircraft according to an embodiment of the present invention.
- Fig. 3 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.
- Fig. 4 is a schematic diagram of a system for actively controlling the center of gravity of an aircraft according to an embodiment of the present invention.
- a method for actively controlling the center of gravity of an aircraft includes:
- Step 1 Before the aircraft takes off, obtain the heading center of gravity X CG01 and X CG02 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, as well as the heading center of gravity X CG03 and X CG04 of the front waste water tank 03 and the rear waste water tank 04 on the aircraft, 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;
- Step 2 Set the target heading center of gravity X CG of the aircraft according to the flight characteristics of the aircraft;
- Step 41 when ⁇ X CG ⁇ 0, the center of gravity of the aircraft is forward, the water in the front water tank 02 is consumed into the user (also called “user area") 05, and the waste water in the user 05 is discharged into the rear waste water tank 04;
- Step 42 when ⁇ X CG >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 .
- 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.
- the center of gravity of the aircraft can be actively adjusted and controlled by adjusting the order of consuming water in the water tank, the final flow direction and the amount of water, and the order of discharging waste water into the waste water tank, the final flow direction and the amount of waste water, so that the center of gravity of the aircraft is stabilized within a certain range, and the measurement and calculation are automatically performed; the current heading center of gravity XCG1 of the aircraft can be compared with the target heading center of gravity XCG .
- the water in the water tank 02 at the front of the aircraft can be consumed into the user 05, and the waste water in the user 05 can be discharged into the waste water tank 04 at the rear of the aircraft, so as to control the center of gravity of the aircraft to be stable near the target center of gravity XCG .
- the current center of gravity is farther back than the target center of gravity, the water in the water tank 01 at the rear of the aircraft can be consumed into the user 05, and the waste water in the user 05 can be discharged into the waste water tank 03 at the front of the aircraft, so as to control the center of gravity of the aircraft to be stable at the target center of gravity XCG.
- Near CG by actively adjusting the center of gravity of the aircraft, the center of gravity of the aircraft is stabilized within a certain range, which can not only ensure flight safety, but also reduce balancing resistance, reduce fuel consumption and improve fuel economy.
- step 41 the amount of water consumed in the front water tank 02, W 02, is equal to the amount of waste water discharged into the rear waste water tank 04 , W 02 and W 04 are calculated by the following moment balance formula:
- X CG05 is the heading center of gravity of user 05 on the aircraft;
- step 42 the amount of water consumed in the rear water tank 01, W 01, is equal to the amount of waste water discharged into the front waste water tank 03 , W 01 and W 03 are calculated by the following moment balance formula:
- the method 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.
- 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.
- the method of actively controlling the center of gravity of the aircraft of the present invention can achieve the following beneficial technical effects: it is easier to actively adjust the center of gravity of the aircraft and easier to keep the center of gravity of the aircraft within the expected ideal range.
- 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.
- measuring sensors are arranged in the rear water tank 01, the front water tank 02, the front waste water tank 03, and the rear waste water tank 04 for measuring the volume of water in each water tank and waste water tank, and the measurement results are V 01 , V 02 , V 03 , and V 04 respectively; the weight of water in each water tank and waste water tank is obtained by multiplying the volume of water by the density of water.
- step 41 or step 42 when the absolute value of the center of gravity difference ⁇ X CG is greater than the set center of gravity deviation threshold, step 41 or step 42 is performed.
- 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 trim resistance, reducing fuel consumption, and improving fuel economy; at the same time, the center of gravity deviation threshold is set to achieve the 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.
- 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
- the rear waste water tank 04 is connected to the user 05 via the rear drainage pipeline 07.
- the amount of water W 02 consumed in the front water tank 02 is controlled by the front water supply flow meter 08 and the front water supply control valve 12 disposed in the front water supply pipeline 16, and the amount of waste water W 04 discharged into the rear waste water tank 04 is controlled by the rear water drainage flow meter 11 and the rear water drainage control valve 15 disposed in the rear drainage pipeline 07;
- the amount of water W 01 consumed in the rear water tank 01 is controlled by the rear water supply flow meter 09 and the rear water supply control valve 13 disposed in the rear water supply pipeline 06, and the amount of waste water W 03 discharged into the front waste water tank 03 is controlled by the front drainage flow meter 10 and the front drainage control valve 14 disposed in the front drainage pipeline 17.
- the method 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.
- the method for actively controlling the center of gravity of an aircraft further includes: Step 5, verifying 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.
- Step 5 verifying 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.
- water measurement and flow direction are automatically calculated; in other embodiments, manual control by the pilot may also be provided.
- a system for actively controlling the center of gravity of an aircraft includes:
- a water tank and waste water tank center of gravity acquisition module is configured to acquire the heading centers of gravity X CG01 and X CG02 of the rear water tank 01 and the front water tank 02 on the aircraft, and the heading centers of gravity X CG03 and X CG04 of the front waste water tank 03 and the rear waste water tank 04 on the aircraft before the aircraft takes off, 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;
- a target heading center of gravity setting module is configured to set the target heading center of gravity X CG of the aircraft according to the flight characteristics of the aircraft;
- the water and wastewater control module is configured such that, when ⁇ X CG ⁇ 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 wastewater in the user 05 is discharged into the rear wastewater tank 04;
- 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.
- the amount of water consumed in the front water tank 02 W 02 is equal to the amount of waste water discharged into the rear waste water tank 04 W 04 , and W 02 and W 04 are calculated by the following moment balance formula:
- X CG05 is the heading center of gravity of user 05 on the aircraft;
- 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.
- the water and wastewater control module is activated 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.
- the system for 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 not too frequent active adjustment of the center of gravity of the aircraft, 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.
- the system for actively controlling the center of gravity of the aircraft further 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.
- a center of gravity change detection module 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.
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Abstract
A method and system for actively controlling the center of gravity of an aircraft, the method comprising: before an aircraft takes off, acquiring heading centers of gravity of a rear water tank (01) and a front water tank (02) on the aircraft, and heading centers of gravity of a front wastewater tank (03) and a rear wastewater tank (04) on the aircraft; setting a target heading center of gravity of the aircraft according to flight characteristics of the aircraft; during flight, calculating the difference in center of gravity (ΔXCG) between the current heading center of gravity of the aircraft and the target heading center of gravity when the center of gravity of the aircraft is changed; when ΔXCG is less than 0, water in the front water tank (02) being consumed by a user, and discharging wastewater in the user into the rear wastewater tank (04); and when ΔXCG is greater than 0, water in the rear water tank (01) being consumed by the user, and discharging wastewater in the user into the front wastewater tank (03). The described method and system are simple and reliable, and the center of gravity of an aircraft can be easily kept within an expected ideal range.
Description
本发明涉及飞机总体设计技术领域，尤其涉及主动控制飞机重心的方法和***。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.
飞机重心是飞机的重要参数，严重影响着飞机的性能、操纵性和稳定性，控制飞机重心是飞机设计过程中的主要环节。在飞机飞行过程中，控制飞机重心处于重心包线中偏后的区域，有利于降低平尾配平阻力，降低燃油消耗，提升燃油经济性。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 trim resistance, reducing fuel consumption and improving fuel economy.
然而，在现有技术中，飞机重心的控制往往通过设置配重装置来实现，无法在飞行过程中主动控制飞机重心，很难将飞机重心保持在预期理想的范围内。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.
发明内容Summary of the invention
本发明的一个目的在于，提供一种主动控制飞机重心的方法和***，其能克服现有技术的不足，方法和***简单可靠，易于将飞机重心保持在预期理想的范围内。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.
本发明的以上目的通过一种主动控制飞机重心的方法来实现，所述方法包括：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:
步骤一，在飞机起飞前，获取后部水箱、前部水箱在飞机上的航向重心X
CG01和X
CG02，以及前部废水箱、后部废水箱在飞机上的航向重心X
CG03和X
CG04，其中，所述后部水箱设置在飞机的后部，所述前部水箱设置在飞机的前部，所述前部废水箱设置在飞机的前部，所述后部废水箱设置在飞机的后部；
Step 1: Before the aircraft takes off, obtain the heading center of gravity X CG01 and X CG02 of the rear water tank and the front water tank on the aircraft, as well as the heading center of gravity X CG03 and X CG04 of the front waste water tank and the rear waste water tank on the aircraft, 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;
步骤二，根据飞机的飞行特性，设置飞机的目标航向重心X
CG；
Step 2: Set the target heading center of gravity X CG of the aircraft according to the flight characteristics of the aircraft;
步骤三，在飞行过程中，当飞机重心发生改变时，获取飞机的当前航向重心X
CG1和飞机总重量W，并计算飞机的当前航向重心X
CG1与目标航向重心X
CG之间的重心差值ΔX
CG，其中，ΔX
CG＝X
CG1-X
CG；
Step 3: During the flight, when the center of gravity of the aircraft changes, obtain the current heading center of gravity X CG1 of the aircraft and the total weight W of the aircraft, and calculate the center of gravity difference ΔX CG between the current heading center of gravity X CG1 of the aircraft and the target heading center of gravity X CG , where ΔX CG =X CG1 -X CG ;
步骤四一，当ΔX
CG<0时，飞机重心靠前，消耗所述前部水箱中的水到用户中，并将用户中的废水排放到所述后部废水箱中；
Step 41: when ΔX CG <0, the center of gravity of the aircraft 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;
步骤四二，当ΔX
CG>0时，飞机重心靠后，消耗所述后部水箱中的水到用户中，并将用户中的废水排放到所述前部废水箱中。
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.
根据上述技术方案，本发明的主动控制飞机重心的方法能起到以下有益技术效果：方法和***简单可靠，易于将飞机重心保持在预期理想的范围内，保证飞行安全的同时提升飞机飞行性能。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.
较佳的是，在步骤四一中，所述前部水箱中消耗的水量W
02等于排放到所述后部废水箱中的废水量W
04，W
02和W
04通过以下力矩平衡公式来计算
Preferably, in step 41, the amount of water consumed in the front water tank W 02 is equal to the amount of waste water discharged into the rear waste water tank W 04 , and W 02 and W 04 are calculated by the following moment balance formula:
ΔX
CG*W＝W
02*(X
CG05-X
CG02)+W
04*(X
CG04-X
CG05)
ΔX CG *W＝W 02 *(X CG05 −X CG02 )+W 04 *(X CG04 −X CG05 )
其中，X
CG05为飞机上用户的航向重心；
Among them, X CG05 is the heading center of gravity of the user on the aircraft;
在步骤四二中，所述后部水箱中消耗的水量W
01等于排放到所述前部废水箱中的废水量W
03，W
01和W
03通过以下力矩平衡公式来计算
In step 42, the amount of water consumed in the rear water tank W 01 is equal to the amount of waste water discharged into the front waste water tank W 03 , and W 01 and W 03 are calculated by the following moment balance formula:
ΔX
CG*W＝W
01*(X
CG05-X
CG01)+W
03*(X
CG03-X
CG05)。
ΔX CG *W = W 01 *(X CG05 −X CG01 )+W 03 *(X CG03 −X CG05 ).
根据上述技术方案，本发明的主动控制飞机重心的方法能起到以下有益技术效果：能更容易地主动调节飞机重心，更易于将飞机重心保持在预期理想的范围内。According to the above technical solution, the method 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.
较佳的是，当重心差值ΔX
CG的绝对值大于设定的重心偏差阈值时，才执行所述步骤四一或所述步骤四二。
Preferably, the step 41 or the step 42 is performed only when the absolute value of the center of gravity difference ΔX CG is greater than a set center of gravity deviation threshold.
根据上述技术方案，本发明的主动控制飞机重心的方法能起到以下有益技术效果：在飞机飞行过程中，控制飞机重心处于重心包线中预期理想的区域，有利于降低平尾配平阻力，降低燃油消耗，提升燃油经济性；同时设置重心偏差阈值以实现不过于频繁地主动调节飞机重心，既确保将飞机 重心保持在预期理想的范围内，又节约飞机上水的消耗。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 ensures that the center of gravity of the aircraft is kept within the expected ideal range and saves water consumption on the aircraft.
较佳的是，所述后部水箱通过后部供水管路连接到所述用户，所述前部水箱通过前部供水管路连接到所述用户，所述前部废水箱通过前部排水管路连接到所述用户，所述后部废水箱通过后部排水管路连接到所述用户。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.
根据上述技术方案，本发明的主动控制飞机重心的方法能起到以下有益技术效果：通过适宜的供水管路和排水管路，能更好地主动调节飞机重心，更易于将飞机重心保持在预期理想的范围内。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.
较佳的是，所述前部水箱中消耗的水量W
02通过设置在所述前部供水管路中的前部供水流量计和前部供水控制阀来控制，排放到所述后部废水箱中的废水量W
04通过设置在所述后部排水管路中的后部排水流量计和后部排水控制阀来控制；
Preferably, the amount of water consumed in the front water tank W 02 is controlled by a front water supply flow meter and a front water supply control valve provided in the front water supply pipeline, and the amount of waste water discharged into the rear waste water tank W 04 is controlled by a rear drainage flow meter and a rear drainage control valve provided in the rear drainage pipeline;
所述后部水箱中消耗的水量W
01通过设置在所述后部供水管路中的后部供水流量计和后部供水控制阀来控制，排放到所述前部废水箱中的废水量W
03通过设置在所述前部排水管路中的前部排水流量计和前部排水控制阀来控制。
The amount of water W 01 consumed in the rear water tank is controlled by the rear water supply flowmeter and the rear water supply control valve arranged in the rear water supply pipeline, and the amount of waste water W 03 discharged into the front waste water tank is controlled by the front drainage flowmeter and the front drainage control valve arranged in the front drainage pipeline.
根据上述技术方案，本发明的主动控制飞机重心的方法能起到以下有益技术效果：通过适宜的流量计和控制阀，能更精确地主动调节飞机重心，更易于将飞机重心保持在预期理想的范围内。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.
较佳的是，所述主动控制飞机重心的方法还包括：步骤五，通过计算各水箱、废水箱的力矩变化来检验水、废水移动的重心变化结果。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.
根据上述技术方案，本发明的主动控制飞机重心的方法能起到以下有益技术效果：通过重心变化检验，进一步确保将飞机重心保持在预期理想的范围内。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 checking 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.
本发明的以上目的还通过一种主动控制飞机重心的***来实现，所述***包括：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:
水箱废水箱重心获取模块，所述水箱废水箱重心获取模块配置成在飞机起飞前，获取后部水箱、前部水箱在飞机上的航向重心X
CG01和X
CG02， 以及前部废水箱、后部废水箱在飞机上的航向重心X
CG03和X
CG04，其中，所述后部水箱设置在飞机的后部，所述前部水箱设置在飞机的前部，所述前部废水箱设置在飞机的前部，所述后部废水箱设置在飞机的后部；
a water tank and waste water tank center of gravity acquisition module, wherein the water tank and waste water tank center of gravity acquisition module is configured to acquire the heading centers of gravity X CG01 and X CG02 of the rear water tank and the front water tank on the aircraft, and the heading centers of gravity X CG03 and X CG04 of the front waste water tank and the rear waste water tank on the aircraft before the aircraft takes off, 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;
目标航向重心设置模块，所述目标航向重心设置模块配置成根据飞机的飞行特性，设置飞机的目标航向重心X
CG；
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 CG of the aircraft according to the flight characteristics of the aircraft;
重心差值计算模块，所述重心差值计算模块配置成在飞行过程中，当飞机重心发生改变时，获取飞机的当前航向重心X
CG1和飞机总重量W，并计算飞机的当前航向重心X
CG1与目标航向重心X
CG之间的重心差值ΔX
CG，其中，ΔX
CG＝X
CG1-X
CG；
A center of gravity difference calculation module, wherein the center of gravity difference calculation module is configured to obtain the current heading center of gravity X CG1 of the aircraft and the total weight W of the aircraft when the center of gravity of the aircraft changes during flight, and calculate the center of gravity difference ΔX CG between the current heading center of gravity X CG1 of the aircraft and the target heading center of gravity X CG , wherein ΔX CG =X CG1 -X CG ;
水量废水量控制模块，所述水量废水量控制模块配置成，当ΔX
CG<0时，飞机重心靠前，消耗所述前部水箱中的水到用户中，并将用户中的废水排放到所述后部废水箱中；
a water and wastewater control module, wherein the water and wastewater control module is configured to, when ΔX CG <0, the center of gravity of the aircraft is forward, consume water in the front water tank into the user, and discharge wastewater in the user into the rear wastewater tank;
当ΔX
CG>0时，飞机重心靠后，消耗所述后部水箱中的水到用户中，并将用户中的废水排放到所述前部废水箱中。
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.
根据上述技术方案，本发明的主动控制飞机重心的***能起到以下有益技术效果：方法和***简单可靠，易于将飞机重心保持在预期理想的范围内，保证飞行安全的同时提升飞机飞行性能。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.
较佳的是，当ΔX
CG<0时，所述前部水箱中消耗的水量W
02等于排放到所述后部废水箱中的废水量W
04，W
02和W
04通过以下力矩平衡公式来计算
Preferably, when ΔX CG <0, the amount of water consumed in the front water tank W 02 is equal to the amount of waste water discharged into the rear waste water tank W 04 , and W 02 and W 04 are calculated by the following moment balance formula:
ΔX
CG*W＝W
02*(X
CG05-X
CG02)+W
04*(X
CG04-X
CG05)
ΔX CG *W＝W 02 *(X CG05 −X CG02 )+W 04 *(X CG04 −X CG05 )
其中，X
CG05为飞机上用户的航向重心；
Among them, X CG05 is the heading center of gravity of the user on the aircraft;
当ΔX
CG>0时，所述后部水箱中消耗的水量W
01等于排放到所述前部废水箱中的废水量W
03，W
01和W
03通过以下力矩平衡公式来计算
When ΔX CG > 0, the amount of water consumed in the rear water tank W 01 is equal to the amount of waste water discharged into the front waste water tank W 03 , and W 01 and W 03 are calculated by the following moment balance formula:
ΔX
CG*W＝W
01*(X
CG05-X
CG01)+W
03*(X
CG03-X
CG05)。
ΔX CG *W = W 01 *(X CG05 −X CG01 )+W 03 *(X CG03 −X CG05 ).
根据上述技术方案，本发明的主动控制飞机重心的***能起到以下有益技术效果：能更容易地主动调节飞机重心，更易于将飞机重心保持在预期理想的范围内。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.
较佳的是，当重心差值ΔX
CG的绝对值大于设定的重心偏差阈值时，才启动所述水量废水量控制模块。
Preferably, the water and wastewater control module is activated only when the absolute value of the center of gravity difference ΔX CG is greater than a set center of gravity deviation threshold.
根据上述技术方案，本发明的主动控制飞机重心的***能起到以下有益技术效果：在飞机飞行过程中，控制飞机重心处于重心包线中预期理想的区域，有利于降低平尾配平阻力，降低燃油消耗，提升燃油经济性；同时设置重心偏差阈值以实现不过于频繁地主动调节飞机重心，既确保将飞机重心保持在预期理想的范围内，又节约飞机上水的消耗。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 ensures that the center of gravity of the aircraft is maintained within the expected ideal range and saves water consumption on the aircraft.
较佳的是，所述后部水箱通过后部供水管路连接到所述用户，所述前部水箱通过前部供水管路连接到所述用户，所述前部废水箱通过前部排水管路连接到所述用户，所述后部废水箱通过后部排水管路连接到所述用户。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.
根据上述技术方案，本发明的主动控制飞机重心的***能起到以下有益技术效果：通过适宜的供水管路和排水管路，能更好地主动调节飞机重心，更易于将飞机重心保持在预期理想的范围内。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.
较佳的是，所述前部水箱中消耗的水量W
02通过设置在所述前部供水管路中的前部供水流量计和前部供水控制阀来控制，排放到所述后部废水箱中的废水量W
04通过设置在所述后部排水管路中的后部排水流量计和后部排水控制阀来控制；
Preferably, the amount of water consumed in the front water tank W 02 is controlled by a front water supply flow meter and a front water supply control valve provided in the front water supply pipeline, and the amount of waste water discharged into the rear waste water tank W 04 is controlled by a rear drainage flow meter and a rear drainage control valve provided in the rear drainage pipeline;
所述后部水箱中消耗的水量W
01通过设置在所述后部供水管路中的后部供水流量计和后部供水控制阀来控制，排放到所述前部废水箱中的废水量W
03通过设置在所述前部排水管路中的前部排水流量计和前部排水控制阀来控制。
The amount of water W 01 consumed in the rear water tank is controlled by the rear water supply flowmeter and the rear water supply control valve arranged in the rear water supply pipeline, and the amount of waste water W 03 discharged into the front waste water tank is controlled by the front drainage flowmeter and the front drainage control valve arranged in the front drainage pipeline.
根据上述技术方案，本发明的主动控制飞机重心的***能起到以下有益技术效果：通过适宜的流量计和控制阀，能更精确地主动调节飞机重心，更易于将飞机重心保持在预期理想的范围内。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.
较佳的是，所述主动控制飞机重心的***还包括：重心变化检验模块，所述重心变化检验模块配置成通过计算各水箱、废水箱的力矩变化来检验水、废水移动的重心变化结果。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.
根据上述技术方案，本发明的主动控制飞机重心的***能起到以下有益 技术效果：通过重心变化检验，进一步确保将飞机重心保持在预期理想的范围内。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.
图1A和图1B是本发明一实施例的主动控制飞机重心的方法和***中水箱、废水箱的布置示意图。1A and 1B are schematic diagrams showing 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.
图2是本发明一实施例的主动控制飞机重心的方法和***中水箱、废水箱的管路示意图。2 is a schematic diagram of the piping 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.
图3是本发明一实施例的主动控制飞机重心的方法的流程图。FIG3 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.
图4是本发明一实施例的主动控制飞机重心的***的示意图。FIG. 4 is a schematic diagram of a system for actively controlling the center of gravity of an aircraft according to an embodiment of the present invention.
附图标记列表Reference numerals list
01、后部水箱；01. Rear water tank;
02、前部水箱；02. Front water tank;
03、前部废水箱；03. Front waste water tank;
04、后部废水箱；04. Rear waste water tank;
05、用户；05. User;
06、后部供水管路；06. Rear water supply pipeline;
07、后部排水管路；07. Rear drainage pipeline;
08、前部供水流量计；08. Front water supply flow meter;
09、后部供水流量计；09. Rear water supply flow meter;
10、前部排水流量计；10. Front drainage flow meter;
11、后部排水流量计；11. Rear drainage flow meter;
12、前部供水控制阀；12. Front water supply control valve;
13、后部供水控制阀；13. Rear water supply control valve;
14、前部排水控制阀；14. Front drainage control valve;
15、后部排水控制阀；15. Rear drainage control valve;
16、前部供水管路；16. Front water supply pipeline;
17、前部排水管路。17. Front drainage pipe.
以下将描述本发明的具体实施方式，需要指出的是，在这些实施方式的具体描述过程中，为了进行简明扼要的描述，本说明书不可能对实际的实施方式的所有特征均作详尽的描述。应当可以理解的是，在任意一种实施方式的实际实施过程中，正如在任意一个工程项目或者设计项目的过程中，为了实现开发者的具体目标，为了满足***相关的或者商业相关的限制，常常会做出各种各样的具体决策，而这也会从一种实施方式到另一种实施方式之间发生改变。此外，还可以理解的是，虽然这种开发过程中所作出的努力可能是复杂并且冗长的，然而对于与本发明公开的内容相关的本领域的普通技术人员而言，在本公开揭露的技术内容的基础上进行的一些设计、制造或者生产等变更只是常规的技术手段，不应当理解为本公开的内容不充分。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.
除非另作定义，权利要求书和说明书中使用的技术术语或者科学术语应当为本发明所属技术领域内具有一般技能的人士所理解的通常意义。本发明专利申请说明书以及权利要求书中使用的“第一”、“第二”以及类似的词语并不表示任何顺序、数量或者重要性，而只是用来区分不同的组成部分。“一个”或者“一”等类似词语并不表示数量限制，而是表示存在至少一个。“包括”或者“包含”等类似的词语意指出现在“包括”或者“包含”前面的元件或者物件涵盖出现在“包括”或者“包含”后面列举的元件或者物件及其等同元件，并不排除其他元件或者物件。“连接”或者“相连”等类似的词语并非限定于物理的或者机械的连接，也不限于是直接的还是间接的连接。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. Words such as "one" or "a" and the like do not indicate a quantitative limitation, but indicate the existence of at least one. Words such as "include" or "comprise" and the like mean that the elements or objects appearing before "include" or "comprise" include the elements or objects listed after "include" or "comprise" and their equivalent elements, and do not exclude other elements or objects. Words such as "connect" or "connected" and the like are not limited to physical or mechanical connections, nor are they limited to direct or indirect connections.
图1A和图1B是本发明一实施例的主动控制飞机重心的方法和***中水箱、废水箱的布置示意图。图2是本发明一实施例的主动控制飞机重心的方法和***中水箱、废水箱的管路示意图。图3是本发明一实施例的主动控制飞机重心的方法的流程图。图4是本发明一实施例的主动控制飞机重心的***的示 意图。Fig. 1A and Fig. 1B are schematic diagrams of the arrangement of water tanks and waste water tanks in a method and system for actively controlling the center of gravity of an aircraft according to an embodiment of the present invention. Fig. 2 is a schematic diagram of the piping of water tanks and waste water tanks in a method and system for actively controlling the center of gravity of an aircraft according to an embodiment of the present invention. Fig. 3 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. Fig. 4 is a schematic diagram of a system for actively controlling the center of gravity of an aircraft according to an embodiment of the present invention.
如图1A至图3所示，根据本发明的一实施例，一种主动控制飞机重心的方法包括：As shown in FIG. 1A to FIG. 3 , according to an embodiment of the present invention, a method for actively controlling the center of gravity of an aircraft includes:
步骤一，在飞机起飞前，获取后部水箱(也可称为“后部供水箱”)01、前部水箱(也可称为“前部供水箱”)02在飞机上的航向重心X
CG01和X
CG02，以及前部废水箱03、后部废水箱04在飞机上的航向重心X
CG03和X
CG04，其中，后部水箱01设置在飞机的后部，前部水箱02设置在飞机的前部，前部废水箱03设置在飞机的前部，后部废水箱04设置在飞机的后部；
Step 1: Before the aircraft takes off, obtain the heading center of gravity X CG01 and X CG02 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, as well as the heading center of gravity X CG03 and X CG04 of the front waste water tank 03 and the rear waste water tank 04 on the aircraft, 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;
步骤二，根据飞机的飞行特性，设置飞机的目标航向重心X
CG；
Step 2: Set the target heading center of gravity X CG of the aircraft according to the flight characteristics of the aircraft;
步骤三，在飞行过程中，当飞机重心发生改变时，获取飞机的当前航向重心X
CG1和飞机总重量W，并计算飞机的当前航向重心X
CG1与目标航向重心X
CG之间的重心差值ΔX
CG，其中，ΔX
CG＝X
CG1-X
CG；
Step 3: During the flight, when the center of gravity of the aircraft changes, obtain the current heading center of gravity X CG1 of the aircraft and the total weight W of the aircraft, and calculate the center of gravity difference ΔX CG between the current heading center of gravity X CG1 of the aircraft and the target heading center of gravity X CG , where ΔX CG =X CG1 -X CG ;
步骤四一，当ΔX
CG<0时，飞机重心靠前，消耗前部水箱02中的水到用户(也可称为“用户区”)05中，并将用户05中的废水排放到后部废水箱04中；
Step 41: when ΔX CG <0, the center of gravity of the aircraft is forward, the water in the front water tank 02 is consumed into the user (also called "user area") 05, and the waste water in the user 05 is discharged into the rear waste water tank 04;
步骤四二，当ΔX
CG>0时，飞机重心靠后，消耗后部水箱01中的水到用户05中，并将用户05中的废水排放到前部废水箱03中。
Step 42: when ΔX CG >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 .
根据上述技术方案，本发明的主动控制飞机重心的方法能起到以下有益技术效果：方法和***简单可靠，易于将飞机重心保持在预期理想的范围内，保证飞行安全的同时提升飞机飞行性能。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.
具体地说，在飞行过程中，当飞机重心发生改变时，可通过调节消耗水箱中水的顺序、最终流向及水量和排放废水到废水箱中的顺序、最终流向及废水量，主动调节和控制飞机重心，使得飞机重心稳定在某一范围内，测量与计算自动进行；可将飞机的当前航向重心X
CG1与目标航向重心X
CG做比较，若当前重心较目标重心靠前，可通过消耗飞机前部水箱02中的水到用户05中，并将用户05中的废水排放到飞机后部废水箱04中，以此来控制飞机的重心稳定在目标重心X
CG附近，若当前重心较目标重心靠后， 可通过消耗飞机后部水箱01中的水到用户05中，并将用户05中的废水排放到飞机前部废水箱03中，以此来控制飞机的重心稳定在目标重心X
CG附近；通过主动调节飞机重心，使得飞机重心稳定在某一范围内，不仅可以保证飞行安全，同时可以降低配平阻力，降低燃油消耗，提升燃油经济性。
Specifically, during the flight, when the center of gravity of the aircraft changes, the center of gravity of the aircraft can be actively adjusted and controlled by adjusting the order of consuming water in the water tank, the final flow direction and the amount of water, and the order of discharging waste water into the waste water tank, the final flow direction and the amount of waste water, so that the center of gravity of the aircraft is stabilized within a certain range, and the measurement and calculation are automatically performed; the current heading center of gravity XCG1 of the aircraft can be compared with the target heading center of gravity XCG . If the current center of gravity is closer to the front of the target center of gravity, the water in the water tank 02 at the front of the aircraft can be consumed into the user 05, and the waste water in the user 05 can be discharged into the waste water tank 04 at the rear of the aircraft, so as to control the center of gravity of the aircraft to be stable near the target center of gravity XCG . If the current center of gravity is farther back than the target center of gravity, the water in the water tank 01 at the rear of the aircraft can be consumed into the user 05, and the waste water in the user 05 can be discharged into the waste water tank 03 at the front of the aircraft, so as to control the center of gravity of the aircraft to be stable at the target center of gravity XCG. Near CG ; by actively adjusting the center of gravity of the aircraft, the center of gravity of the aircraft is stabilized within a certain range, which can not only ensure flight safety, but also reduce balancing resistance, reduce fuel consumption and improve fuel economy.
在一些实施例中，在步骤四一中，前部水箱02中消耗的水量W
02等于排放到后部废水箱04中的废水量W
04，W
02和W
04通过以下力矩平衡公式来计算
In some embodiments, in step 41, the amount of water consumed in the front water tank 02, W 02, is equal to the amount of waste water discharged into the rear waste water tank 04 , W 02 and W 04 are calculated by the following moment balance formula:
ΔX
CG*W＝W
02*(X
CG05-X
CG02)+W
04*(X
CG04-X
CG05)
ΔX CG *W＝W 02 *(X CG05 −X CG02 )+W 04 *(X CG04 −X CG05 )
其中，X
CG05为飞机上用户05的航向重心；
Among them, X CG05 is the heading center of gravity of user 05 on the aircraft;
在步骤四二中，后部水箱01中消耗的水量W
01等于排放到前部废水箱03中的废水量W
03，W
01和W
03通过以下力矩平衡公式来计算
In step 42, the amount of water consumed in the rear water tank 01, W 01, is equal to the amount of waste water discharged into the front waste water tank 03 , W 01 and W 03 are calculated by the following moment balance formula:
ΔX
CG*W＝W
01*(X
CG05-X
CG01)+W
03*(X
CG03-X
CG05)。
ΔX CG *W = W 01 *(X CG05 −X CG01 )+W 03 *(X CG03 −X CG05 ).
根据上述技术方案，本发明的主动控制飞机重心的方法能起到以下有益技术效果：能更容易地主动调节飞机重心，更易于将飞机重心保持在预期理想的范围内。According to the above technical solution, the method 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.
在一些实施例中，如图1A和图1B所示，后部水箱01、前部水箱02、前部废水箱03和后部废水箱04设置在飞机上对飞机重心有较大影响的区域。根据上述技术方案，本发明的主动控制飞机重心的方法能起到以下有益技术效果：能更容易地主动调节飞机重心，更易于将飞机重心保持在预期理想的范围内。In some embodiments, as shown in FIG1A and FIG1B , 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 is easier to actively adjust the center of gravity of the aircraft and easier to keep the center of gravity of the aircraft within the expected ideal range.
在一些实施例中，例如，前部水箱02、前部废水箱03设置在飞机前货舱前部，后部水箱01、后部废水箱04设置在飞机后货舱后部；又例如，前部水箱02、前部废水箱03设置在飞机客舱的前服务区，后部水箱01、后部废水箱04设置在飞机客舱的后服务区；又例如，前部水箱02、前部废水箱03设置在飞机起落架舱，后部水箱01、后部废水箱04设置在飞机散货舱或水废水舱。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.
在一些实施例中，后部水箱01、前部水箱02与前部废水箱03、后部废水箱04中都布置有测量传感器，用于测量各水箱、废水箱内水的体积，测 量结果分别为V
01、V
02、V
03、V
04；水的体积乘以水的密度得到各水箱、废水箱中水的重量。
In some embodiments, measuring sensors are arranged in the rear water tank 01, the front water tank 02, the front waste water tank 03, and the rear waste water tank 04 for measuring the volume of water in each water tank and waste water tank, and the measurement results are V 01 , V 02 , V 03 , and V 04 respectively; the weight of water in each water tank and waste water tank is obtained by multiplying the volume of water by the density of water.
在一些实施例中，当重心差值ΔX
CG的绝对值大于设定的重心偏差阈值时，才执行步骤四一或步骤四二。根据上述技术方案，本发明的主动控制飞机重心的方法能起到以下有益技术效果：在飞机飞行过程中，控制飞机重心处于重心包线中预期理想的区域，有利于降低平尾配平阻力，降低燃油消耗，提升燃油经济性；同时设置重心偏差阈值以实现不过于频繁地主动调节飞机重心，既确保将飞机重心保持在预期理想的范围内，又节约飞机上水的消耗。
In some embodiments, when the absolute value of the center of gravity difference ΔX CG is greater than the set center of gravity deviation threshold, step 41 or step 42 is performed. 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 trim resistance, reducing fuel consumption, and improving fuel economy; at the same time, the center of gravity deviation threshold is set to achieve the 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.
在一些实施例中，如图2所示，后部水箱01通过后部供水管路06连接到用户05，前部水箱02通过前部供水管路16连接到用户05，前部废水箱03通过前部排水管路17连接到用户05，后部废水箱04通过后部排水管路07连接到用户05。根据上述技术方案，本发明的主动控制飞机重心的方法能起到以下有益技术效果：通过适宜的供水管路和排水管路，能更好地主动调节飞机重心，更易于将飞机重心保持在预期理想的范围内。In some embodiments, as shown in FIG2 , 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 solution, 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.
在一些实施例中，如图2所示，前部水箱02中消耗的水量W
02通过设置在前部供水管路16中的前部供水流量计08和前部供水控制阀12来控制，排放到后部废水箱04中的废水量W
04通过设置在后部排水管路07中的后部排水流量计11和后部排水控制阀15来控制；后部水箱01中消耗的水量W
01通过设置在后部供水管路06中的后部供水流量计09和后部供水控制阀13来控制，排放到前部废水箱03中的废水量W
03通过设置在前部排水管路17中的前部排水流量计10和前部排水控制阀14来控制。根据上述技术方案，本发明的主动控制飞机重心的方法能起到以下有益技术效果：通过适宜的流量计和控制阀，能更精确地主动调节飞机重心，更易于将飞机重心保持在预期理想的范围内。
In some embodiments, as shown in FIG2 , the amount of water W 02 consumed in the front water tank 02 is controlled by the front water supply flow meter 08 and the front water supply control valve 12 disposed in the front water supply pipeline 16, and the amount of waste water W 04 discharged into the rear waste water tank 04 is controlled by the rear water drainage flow meter 11 and the rear water drainage control valve 15 disposed in the rear drainage pipeline 07; the amount of water W 01 consumed in the rear water tank 01 is controlled by the rear water supply flow meter 09 and the rear water supply control valve 13 disposed in the rear water supply pipeline 06, and the amount of waste water W 03 discharged into the front waste water tank 03 is controlled by the front drainage flow meter 10 and the front drainage control valve 14 disposed in the front drainage pipeline 17. According to the above technical scheme, the method 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.
在一些实施例中，如图3所示，该主动控制飞机重心的方法还包括：步骤五，通过计算各水箱、废水箱的力矩变化来检验水、废水移动的重心变化结果。根据上述技术方案，本发明的主动控制飞机重心的方法能起到以下 有益技术效果：通过重心变化检验，进一步确保将飞机重心保持在预期理想的范围内。In some embodiments, as shown in FIG3 , the method for actively controlling the center of gravity of an aircraft further includes: Step 5, verifying 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 method for actively controlling the center of gravity of an 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.
在一些实施例中，水的测量和流向实现自动计算；在另一些实施例中，也可提供飞行员手动控制的功能。In some embodiments, water measurement and flow direction are automatically calculated; in other embodiments, manual control by the pilot may also be provided.
如图1A至图4所示，根据本发明的一实施例，一种主动控制飞机重心的***包括：As shown in FIG. 1A to FIG. 4 , according to an embodiment of the present invention, a system for actively controlling the center of gravity of an aircraft includes:
水箱废水箱重心获取模块，水箱废水箱重心获取模块配置成在飞机起飞前，获取后部水箱01、前部水箱02在飞机上的航向重心X
CG01和X
CG02，以及前部废水箱03、后部废水箱04在飞机上的航向重心X
CG03和X
CG04，其中，后部水箱01设置在飞机的后部，前部水箱02设置在飞机的前部，前部废水箱03设置在飞机的前部，后部废水箱04设置在飞机的后部；
A water tank and waste water tank center of gravity acquisition module, the water tank and waste water tank center of gravity acquisition module is configured to acquire the heading centers of gravity X CG01 and X CG02 of the rear water tank 01 and the front water tank 02 on the aircraft, and the heading centers of gravity X CG03 and X CG04 of the front waste water tank 03 and the rear waste water tank 04 on the aircraft before the aircraft takes off, 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;
目标航向重心设置模块，目标航向重心设置模块配置成根据飞机的飞行特性，设置飞机的目标航向重心X
CG；
A target heading center of gravity setting module, the target heading center of gravity setting module is configured to set the target heading center of gravity X CG of the aircraft according to the flight characteristics of the aircraft;
重心差值计算模块，重心差值计算模块配置成在飞行过程中，当飞机重心发生改变时，获取飞机的当前航向重心X
CG1和飞机总重量W，并计算飞机的当前航向重心X
CG1与目标航向重心X
CG之间的重心差值ΔX
CG，其中，ΔX
CG＝X
CG1-X
CG；
The center of gravity difference calculation module is configured to obtain the current heading center of gravity X CG1 of the aircraft and the total weight W of the aircraft when the center of gravity of the aircraft changes during flight, and calculate the center of gravity difference ΔX CG between the current heading center of gravity X CG1 of the aircraft and the target heading center of gravity X CG , wherein ΔX CG =X CG1 -X CG ;
水量废水量控制模块，水量废水量控制模块配置成，当ΔX
CG<0时，飞机重心靠前，消耗前部水箱02中的水到用户05中，并将用户05中的废水排放到后部废水箱04中；
The water and wastewater control module is configured such that, when ΔX CG <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 wastewater in the user 05 is discharged into the rear wastewater tank 04;
当ΔX
CG>0时，飞机重心靠后，消耗后部水箱01中的水到用户05中，并将用户05中的废水排放到前部废水箱03中。
When ΔX CG >0, the center of gravity of the aircraft is backward, the water in the rear water tank 01 is consumed to the user 05 , and the waste water in the user 05 is discharged to the front waste water tank 03 .
根据上述技术方案，本发明的主动控制飞机重心的***能起到以下有益技术效果：方法和***简单可靠，易于将飞机重心保持在预期理想的范围内，保证飞行安全的同时提升飞机飞行性能。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.
在一些实施例中，当ΔX
CG<0时，前部水箱02中消耗的水量W
02等于排放到后部废水箱04中的废水量W
04，W
02和W
04通过以下力矩平衡公式 来计算
In some embodiments, when ΔX CG <0, the amount of water consumed in the front water tank 02 W 02 is equal to the amount of waste water discharged into the rear waste water tank 04 W 04 , and W 02 and W 04 are calculated by the following moment balance formula:
ΔX
CG*W＝W
02*(X
CG05-X
CG02)+W
04*(X
CG04-X
CG05)
ΔX CG *W＝W 02 *(X CG05 −X CG02 )+W 04 *(X CG04 −X CG05 )
其中，X
CG05为飞机上用户05的航向重心；
Among them, X CG05 is the heading center of gravity of user 05 on the aircraft;
当ΔX
CG>0时，后部水箱01中消耗的水量W
01等于排放到前部废水箱03中的废水量W
03，W
01和W
03通过以下力矩平衡公式来计算
When ΔX CG > 0, the amount of water consumed in the rear water tank 01, W 01 , is equal to the amount of waste water discharged into the front waste water tank 03 , W 01 and W 03 are calculated by the following moment balance formula:
ΔX
CG*W＝W
01*(X
CG05-X
CG01)+W
03*(X
CG03-X
CG05)。
ΔX CG *W = W 01 *(X CG05 −X CG01 )+W 03 *(X CG03 −X CG05 ).
根据上述技术方案，本发明的主动控制飞机重心的***能起到以下有益技术效果：能更容易地主动调节飞机重心，更易于将飞机重心保持在预期理想的范围内。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.
在一些实施例中，当重心差值ΔX
CG的绝对值大于设定的重心偏差阈值时，才启动水量废水量控制模块，从而调节消耗水箱中水的顺序、最终流向及水量和排放废水到废水箱中的顺序、最终流向及废水量。根据上述技术方案，本发明的主动控制飞机重心的***能起到以下有益技术效果：在飞机飞行过程中，控制飞机重心处于重心包线中预期理想的区域，有利于降低平尾配平阻力，降低燃油消耗，提升燃油经济性；同时设置重心偏差阈值以实现不过于频繁地主动调节飞机重心，既确保将飞机重心保持在预期理想的范围内，又节约飞机上水的消耗。
In some embodiments, when the absolute value of the center of gravity difference ΔX CG is greater than the set center of gravity deviation threshold, the water and wastewater control module is activated 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 for 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 not too frequent active adjustment of the center of gravity of the aircraft, 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.
在一些实施例中，如图4所示，该主动控制飞机重心的***还包括：重心变化检验模块，重心变化检验模块配置成通过计算各水箱、废水箱的力矩变化来检验水、废水移动的重心变化结果。根据上述技术方案，本发明的主动控制飞机重心的***能起到以下有益技术效果：通过重心变化检验，进一步确保将飞机重心保持在预期理想的范围内。In some embodiments, as shown in FIG4 , the system for actively controlling the center of gravity of the aircraft further 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.
以上对本发明的具体实施方式进行了描述，但本领域技术人员将会理解，上述具体实施方式并不构成对本发明的限制，本领域技术人员可以在以上公开内容的基础上进行多种修改，而不超出本发明的范围。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 (12)
- 一种主动控制飞机重心的方法，包括：A method for actively controlling the center of gravity of an aircraft, comprising:步骤一，在飞机起飞前，获取后部水箱、前部水箱在飞机上的航向重心X CG01和X CG02，以及前部废水箱、后部废水箱在飞机上的航向重心X CG03和X CG04，其中，所述后部水箱设置在飞机的后部，所述前部水箱设置在飞机的前部，所述前部废水箱设置在飞机的前部，所述后部废水箱设置在飞机的后部； Step 1: Before the aircraft takes off, obtain the heading center of gravity X CG01 and X CG02 of the rear water tank and the front water tank on the aircraft, as well as the heading center of gravity X CG03 and X CG04 of the front waste water tank and the rear waste water tank on the aircraft, 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;步骤二，根据飞机的飞行特性，设置飞机的目标航向重心X CG； Step 2: Set the target heading center of gravity X CG of the aircraft according to the flight characteristics of the aircraft;步骤三，在飞行过程中，当飞机重心发生改变时，获取飞机的当前航向重心X CG1和飞机总重量W，并计算飞机的当前航向重心X CG1与目标航向重心X CG之间的重心差值ΔX CG，其中，ΔX CG＝X CG1-X CG； Step 3: During the flight, when the center of gravity of the aircraft changes, obtain the current heading center of gravity X CG1 of the aircraft and the total weight W of the aircraft, and calculate the center of gravity difference ΔX CG between the current heading center of gravity X CG1 of the aircraft and the target heading center of gravity X CG , where ΔX CG =X CG1 -X CG ;步骤四一，当ΔX CG<0时，飞机重心靠前，消耗所述前部水箱中的水到用户中，并将用户中的废水排放到所述后部废水箱中； Step 41: when ΔX CG <0, the center of gravity of the aircraft 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;步骤四二，当ΔX CG>0时，飞机重心靠后，消耗所述后部水箱中的水到用户中，并将用户中的废水排放到所述前部废水箱中。 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.
- 如权利要求1所述的主动控制飞机重心的方法，其特征在于，在步骤四一中，所述前部水箱中消耗的水量W 02等于排放到所述后部废水箱中的废水量W 04，W 02和W 04通过以下力矩平衡公式来计算 The method for actively controlling the center of gravity of an aircraft as claimed in claim 1, characterized in that in step 41, the amount of water W02 consumed in the front water tank is equal to the amount of waste water W04 discharged into the rear waste water tank, and W02 and W04 are calculated by the following moment balance formula:ΔX CG*W＝W 02*(X CG05-X CG02)+W 04*(X CG04-X CG05) ΔX CG *W＝W 02 *(X CG05 −X CG02 )+W 04 *(X CG04 −X CG05 )其中，X CG05为飞机上用户的航向重心； Among them, X CG05 is the heading center of gravity of the user on the aircraft;在步骤四二中，所述后部水箱中消耗的水量W 01等于排放到所述前部废水箱中的废水量W 03，W 01和W 03通过以下力矩平衡公式来计算 In step 42, the amount of water consumed in the rear water tank W 01 is equal to the amount of waste water discharged into the front waste water tank W 03 , and W 01 and W 03 are calculated by the following moment balance formula:ΔX CG*W＝W 01*(X CG05-X CG01)+W 03*(X CG03-X CG05)。 ΔX CG *W = W 01 *(X CG05 −X CG01 )+W 03 *(X CG03 −X CG05 ).
- 如权利要求1所述的主动控制飞机重心的方法，其特征在于，当重心差值ΔX CG的绝对值大于设定的重心偏差阈值时，才执行所述步骤四一或 所述步骤四二。 The method for actively controlling the center of gravity of an aircraft as claimed in claim 1, characterized in that step 41 or step 42 is performed only when the absolute value of the center of gravity difference ΔX CG is greater than a set center of gravity deviation threshold.
- 如权利要求1所述的主动控制飞机重心的方法，其特征在于，所述后部水箱通过后部供水管路连接到所述用户，所述前部水箱通过前部供水管路连接到所述用户，所述前部废水箱通过前部排水管路连接到所述用户，所述后部废水箱通过后部排水管路连接到所述用户。The method for actively controlling the center of gravity of an aircraft as described in claim 1 is characterized in that the rear water tank is connected to the user through a rear water supply pipeline, the front water tank is connected to the user through a front water supply pipeline, the front wastewater tank is connected to the user through a front drainage pipeline, and the rear wastewater tank is connected to the user through a rear drainage pipeline.
- 如权利要求4所述的主动控制飞机重心的方法，其特征在于，所述前部水箱中消耗的水量W 02通过设置在所述前部供水管路中的前部供水流量计和前部供水控制阀来控制，排放到所述后部废水箱中的废水量W 04通过设置在所述后部排水管路中的后部排水流量计和后部排水控制阀来控制； The method for actively controlling the center of gravity of an aircraft as claimed in claim 4 is characterized in that the amount of water consumed in the front water tank W 02 is controlled by a front water supply flow meter and a front water supply control valve provided in the front water supply pipeline, and the amount of waste water discharged into the rear waste water tank W 04 is controlled by a rear drainage flow meter and a rear drainage control valve provided in the rear drainage pipeline;所述后部水箱中消耗的水量W 01通过设置在所述后部供水管路中的后部供水流量计和后部供水控制阀来控制，排放到所述前部废水箱中的废水量W 03通过设置在所述前部排水管路中的前部排水流量计和前部排水控制阀来控制。 The amount of water W 01 consumed in the rear water tank is controlled by the rear water supply flowmeter and the rear water supply control valve arranged in the rear water supply pipeline, and the amount of waste water W 03 discharged into the front waste water tank is controlled by the front drainage flowmeter and the front drainage control valve arranged in the front drainage pipeline.
- 如权利要求1所述的主动控制飞机重心的方法，其特征在于，还包括：步骤五，通过计算各水箱、废水箱的力矩变化来检验水、废水移动的重心变化结果。The method for actively controlling the center of gravity of an aircraft as described in claim 1 is characterized in that it also includes: step 5, verifying 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.
- 一种主动控制飞机重心的***，包括：A system for actively controlling the center of gravity of an aircraft, comprising:水箱废水箱重心获取模块，所述水箱废水箱重心获取模块配置成在飞机起飞前，获取后部水箱、前部水箱在飞机上的航向重心X CG01和X CG02，以及前部废水箱、后部废水箱在飞机上的航向重心X CG03和X CG04，其中，所述后部水箱设置在飞机的后部，所述前部水箱设置在飞机的前部，所述前部废水箱设置在飞机的前部，所述后部废水箱设置在飞机的后部； a water tank and waste water tank center of gravity acquisition module, wherein the water tank and waste water tank center of gravity acquisition module is configured to acquire the heading centers of gravity X CG01 and X CG02 of the rear water tank and the front water tank on the aircraft, and the heading centers of gravity X CG03 and X CG04 of the front waste water tank and the rear waste water tank on the aircraft before the aircraft takes off, 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;目标航向重心设置模块，所述目标航向重心设置模块配置成根据飞机 的飞行特性，设置飞机的目标航向重心X CG； 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 CG of the aircraft according to the flight characteristics of the aircraft;重心差值计算模块，所述重心差值计算模块配置成在飞行过程中，当飞机重心发生改变时，获取飞机的当前航向重心X CG1和飞机总重量W，并计算飞机的当前航向重心X CG1与目标航向重心X CG之间的重心差值ΔX CG，其中，ΔX CG＝X CG1-X CG； A center of gravity difference calculation module, wherein the center of gravity difference calculation module is configured to obtain the current heading center of gravity X CG1 of the aircraft and the total weight W of the aircraft when the center of gravity of the aircraft changes during flight, and calculate the center of gravity difference ΔX CG between the current heading center of gravity X CG1 of the aircraft and the target heading center of gravity X CG , wherein ΔX CG =X CG1 -X CG ;水量废水量控制模块，所述水量废水量控制模块配置成，当ΔX CG<0时，飞机重心靠前，消耗所述前部水箱中的水到用户中，并将用户中的废水排放到所述后部废水箱中； a water and wastewater control module, wherein the water and wastewater control module is configured to, when ΔX CG <0, the center of gravity of the aircraft is forward, consume water in the front water tank into the user, and discharge wastewater in the user into the rear wastewater tank;当ΔX CG>0时，飞机重心靠后，消耗所述后部水箱中的水到用户中，并将用户中的废水排放到所述前部废水箱中。 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.
- 如权利要求7所述的主动控制飞机重心的***，其特征在于，当ΔX CG<0时，所述前部水箱中消耗的水量W 02等于排放到所述后部废水箱中的废水量W 04，W 02和W 04通过以下力矩平衡公式来计算 The system for actively controlling the center of gravity of an aircraft as claimed in claim 7, characterized in that when ΔX CG <0, the amount of water consumed in the front water tank W 02 is equal to the amount of waste water discharged into the rear waste water tank W 04 , and W 02 and W 04 are calculated by the following moment balance formula:ΔX CG*W＝W 02*(X CG05-X CG02)+W 04*(X CG04-X CG05) ΔX CG *W＝W 02 *(X CG05 −X CG02 )+W 04 *(X CG04 −X CG05 )其中，X CG05为飞机上用户的航向重心； Among them, X CG05 is the heading center of gravity of the user on the aircraft;当ΔX CG>0时，所述后部水箱中消耗的水量W 01等于排放到所述前部废水箱中的废水量W 03，W 01和W 03通过以下力矩平衡公式来计算 When ΔX CG > 0, the amount of water consumed in the rear water tank W 01 is equal to the amount of waste water discharged into the front waste water tank W 03 , and W 01 and W 03 are calculated by the following moment balance formula:ΔX CG*W＝W 01*(X CG05-X CG01)+W 03*(X CG03-X CG05)。 ΔX CG *W = W 01 *(X CG05 −X CG01 )+W 03 *(X CG03 −X CG05 ).
- 如权利要求7所述的主动控制飞机重心的***，其特征在于，当重心差值ΔX CG的绝对值大于设定的重心偏差阈值时，才启动所述水量废水量控制模块。 The system for actively controlling the center of gravity of an aircraft as claimed in claim 7, characterized in that the water and wastewater control module is activated only when the absolute value of the center of gravity difference ΔX CG is greater than a set center of gravity deviation threshold.
- 如权利要求7所述的主动控制飞机重心的***，其特征在于，所述后部水箱通过后部供水管路连接到所述用户，所述前部水箱通过前部供水管路连接到所述用户，所述前部废水箱通过前部排水管路连接到所述用户，所述后部废水箱通过后部排水管路连接到所述用户。The system for actively controlling the center of gravity of an aircraft as described in claim 7 is characterized in that the rear water tank is connected to the user through a rear water supply pipeline, the front water tank is connected to the user through a front water supply pipeline, the front wastewater tank is connected to the user through a front drainage pipeline, and the rear wastewater tank is connected to the user through a rear drainage pipeline.
- 如权利要求10所述的主动控制飞机重心的***，其特征在于，所述前部水箱中消耗的水量W 02通过设置在所述前部供水管路中的前部供水流量计和前部供水控制阀来控制，排放到所述后部废水箱中的废水量W 04通过设置在所述后部排水管路中的后部排水流量计和后部排水控制阀来控制； The system for actively controlling the center of gravity of an aircraft as claimed in claim 10, characterized in that the amount of water consumed in the front water tank W 02 is controlled by a front water supply flow meter and a front water supply control valve provided in the front water supply pipeline, and the amount of waste water discharged into the rear waste water tank W 04 is controlled by a rear drainage flow meter and a rear drainage control valve provided in the rear drainage pipeline;所述后部水箱中消耗的水量W 01通过设置在所述后部供水管路中的后部供水流量计和后部供水控制阀来控制，排放到所述前部废水箱中的废水量W 03通过设置在所述前部排水管路中的前部排水流量计和前部排水控制阀来控制。 The amount of water W 01 consumed in the rear water tank is controlled by the rear water supply flowmeter and the rear water supply control valve arranged in the rear water supply pipeline, and the amount of waste water W 03 discharged into the front waste water tank is controlled by the front drainage flowmeter and the front drainage control valve arranged in the front drainage pipeline.
- 如权利要求7所述的主动控制飞机重心的***，其特征在于，还包括：重心变化检验模块，所述重心变化检验模块配置成通过计算各水箱、废水箱的力矩变化来检验水、废水移动的重心变化结果。The system for actively controlling the center of gravity of an aircraft as described in claim 7 is characterized in that it also includes: a center of gravity change verification module, wherein the center of gravity change verification module is configured to verify 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.
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| CN202211285595.0A CN115465444A (en) | 2022-10-20 | 2022-10-20 | Method and system for actively controlling center of gravity of aircraft |
| CN202211285595.0 | 2022-10-20 |
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| WO2024082392A1 true WO2024082392A1 (en) | 2024-04-25 |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR20140052607A (en) * | 2012-10-25 | 2014-05-07 | 한국항공우주산업 주식회사 | System and method for adjusting control law gain according to the change of center of gravity of aircraft |
| CN109278988A (en) * | 2017-07-21 | 2019-01-29 | 中国航空工业集团公司西安飞机设计研究所 | A kind of center of gravity of airplane regulating device |
| WO2020059661A1 (en) * | 2018-09-18 | 2020-03-26 | 横浜ゴム株式会社 | Hot and cold water supply system for aircraft |
| CN112882379A (en) * | 2021-01-13 | 2021-06-01 | 哈尔滨工业大学 | Airplane longitudinal gravity center allocation control method |
| CN113335537A (en) * | 2021-05-28 | 2021-09-03 | 中国航空工业集团公司沈阳飞机设计研究所 | Fuel oil gravity center control method based on airplane active gravity center control strategy |
-
2022
- 2022-10-20 CN CN202211285595.0A patent/CN115465444A/en active Pending
- 2022-12-07 WO PCT/CN2022/137115 patent/WO2024082392A1/en unknown
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR20140052607A (en) * | 2012-10-25 | 2014-05-07 | 한국항공우주산업 주식회사 | System and method for adjusting control law gain according to the change of center of gravity of aircraft |
| CN109278988A (en) * | 2017-07-21 | 2019-01-29 | 中国航空工业集团公司西安飞机设计研究所 | A kind of center of gravity of airplane regulating device |
| WO2020059661A1 (en) * | 2018-09-18 | 2020-03-26 | 横浜ゴム株式会社 | Hot and cold water supply system for aircraft |
| CN112882379A (en) * | 2021-01-13 | 2021-06-01 | 哈尔滨工业大学 | Airplane longitudinal gravity center allocation control method |
| CN113335537A (en) * | 2021-05-28 | 2021-09-03 | 中国航空工业集团公司沈阳飞机设计研究所 | Fuel oil gravity center control method based on airplane active gravity center control strategy |
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