Cargo loading and unloading control method and device based on aircraft gravity center position

Abstract

The invention belongs to the technical field of cargo loading and unloading management, and particularly relates to a cargo loading and unloading control method and device based on the center-of-gravity position of an aircraft. The method comprises the following steps: S1, when an airplane is loaded and unloaded, acquiring data of stress sensors mounted on a plurality of undercarriage axles; s2, calculating the center of gravity of the aircraft in real time based on the data of the stress sensors; s3, marking the position of the center of gravity of the airplane in a preset plane schematic diagram of the airplane with a plurality of indication ranges; and S4, giving alarm information corresponding to the indication range. The method can be flexibly applied to airplanes of different models, the weight center of gravity can be rapidly measured, the airplanes can measure the weight center of gravity equipment at any time by means of the airplanes, special weighing equipment is not needed, the environmental adaptability is good, and the economic cost is low.

Description

Technical Field

[0001] The present application belongs to the technical field of cargo loading and unloading management, and in particular, relates to a cargo loading and unloading control method and device based on the center of gravity position of an aircraft. Background Art

[0002] During the process of loading and unloading cargo or after loading cargo, the center of gravity of the aircraft needs to be kept within a controllable range, so the aircraft weight and center of gravity need to be measured.

[0003] Taking the existing aircraft weight measurement as an example, there are usually two methods. One is the jacking method, which is to lift the aircraft from three jacking positions by jacking. At the same time, there is a load sensor under each jack, which can measure the load of the aircraft at each jack position. All loads are accumulated together to calculate the weight center of gravity of the aircraft. The other is the platform weighing method, which is to tow the aircraft to the weighing platform to obtain the weight center of gravity of the aircraft.

[0004] Although the above method can obtain the weight and center of gravity data of the aircraft, it requires the help of external support equipment. When the aircraft is on duty in a place without such support equipment, the required data cannot be obtained. In addition, the above method is time-consuming and labor-intensive. Each measurement is accompanied by a lot of work by the maintenance personnel, and the timeliness is poor. It is also impossible to observe the changes in the weight and center of gravity in real time, and cannot be used during the loading and unloading process. Summary of the invention

[0005] In order to solve the above problems, the present application provides a method and device for controlling loading and unloading cargo based on the center of gravity position of an aircraft, so as to realize real-time monitoring of the weight center of gravity.

[0006] The first aspect of the present application provides a method for controlling loading and unloading cargo based on the center of gravity position of an aircraft, which mainly includes:

[0007] Step S1, when the aircraft is loading or unloading, obtaining data of stress sensors installed on multiple landing gear axles;

[0008] Step S2, calculating the center of gravity of the aircraft in real time based on data from multiple stress sensors;

[0009] Step S3, marking the position of the center of gravity of the aircraft in a preset aircraft plane diagram having multiple indication ranges;

[0010] Step S4: providing warning information corresponding to the indicated range.

[0011] Preferably, the stress sensors include at least three, which are respectively installed at a front landing gear axle and two main landing gear axles.

[0012] Preferably, the stress sensors include six groups, two groups of sensor assemblies are arranged on the front landing gear axle near the two front wheels, two groups of sensor assemblies are arranged on the first main landing gear axle on the left side of the aircraft near the two left main wheels, and two groups of sensor assemblies are arranged on the second main landing gear axle on the right side of the aircraft near the two right main wheels, and each group of sensor assemblies is connected to the data processing unit through the wiring harness through the threading hole of the axle.

[0013] Preferably, the sensor assembly comprises a plurality of stress sensors arranged circumferentially on an annular surface of a support frame of the wheel axle.

[0014] Preferably, in step S3, the indication range includes a circle for indicating the center of the aircraft and a plurality of annular bands concentric with the circle; when the position of the center of gravity of the aircraft is within the circle, it is used to indicate that the aircraft loading and unloading process is in a safe state; and when the position of the center of gravity of the aircraft is within the annular bands, it is used to indicate that the aircraft loading and unloading process is in a dangerous state.

[0015] Preferably, the annular belts include at least two, and the danger level of the inner annular belt is lower than that of the outer annular belt.

[0016] Preferably, step S4 further comprises:

[0017] When the center of gravity of the aircraft is located within the inner annular zone, the aircraft sends a first warning signal, wherein the first warning signal is used to indicate that the center of gravity of the aircraft is at the boundary of the center of gravity range, prompting that subsequent loading and unloading should be replanned;

[0018] When the center of gravity of the aircraft is located within the outer annular zone, the aircraft sends a second warning signal, wherein the second warning signal is used to indicate that the center of gravity of the aircraft is outside the center of gravity range, prompting that the cargo remaining in the aircraft after loading or unloading must be re-planned.

[0019] The second aspect of the present application provides a cargo loading and unloading control device based on the center of gravity position of an aircraft, mainly comprising:

[0020] a data processing unit for acquiring data from stress sensors installed on a plurality of landing gear axles when the aircraft is being loaded or unloaded;

[0021] A center of gravity calculation unit, used to calculate the center of gravity of the aircraft in real time based on data from multiple stress sensors;

[0022] A display control unit, used for marking the position of the center of gravity of the aircraft in a preset aircraft plane schematic diagram having multiple indication ranges;

[0023] The alarm unit is used to give alarm information corresponding to the indicated range.

[0024] Preferably, the stress sensors include at least three, which are respectively installed at a front landing gear axle and two main landing gear axles.

[0025] Preferably, the stress sensors include six groups, two groups of sensor assemblies are arranged on the front landing gear axle near the two front wheels, two groups of sensor assemblies are arranged on the first main landing gear axle on the left side of the aircraft near the two left main wheels, and two groups of sensor assemblies are arranged on the second main landing gear axle on the right side of the aircraft near the two right main wheels, and each group of sensor assemblies is connected to the data processing unit through the wiring harness through the threading hole of the axle.

[0026] Preferably, the sensor assembly comprises a plurality of stress sensors arranged circumferentially on an annular surface of a support frame of the wheel axle.

[0027] Preferably, in the display control unit, the indication range includes a circle for indicating the center of the aircraft and a plurality of annular bands concentric with the circle; when the position of the center of gravity of the aircraft is within the circle, it is used to indicate that the aircraft loading and unloading process is in a safe state; and when the position of the center of gravity of the aircraft is within the annular bands, it is used to indicate that the aircraft loading and unloading process is in a dangerous state.

[0028] Preferably, the annular belts include at least two, and the danger level of the inner annular belt is lower than that of the outer annular belt.

[0029] Preferably, the alarm unit comprises:

[0030] A first warning signal generating module, configured to cause the aircraft to send a first warning signal when the center of gravity of the aircraft is located within the inner annular zone, wherein the first warning signal is used to indicate that the center of gravity of the aircraft is at the boundary of the center of gravity range, prompting that subsequent loading and unloading should be replanned;

[0031] The second warning signal generating module is used for the aircraft to send out a second warning signal when the center of gravity of the aircraft is located within the outer annular zone. The second warning signal is used to indicate that the center of gravity of the aircraft is outside the center of gravity range, prompting that the cargo remaining in the aircraft after loading or unloading must be re-planned.

[0032] A third aspect of the present application provides a computer device, comprising a processor, a memory, and a computer program stored in the memory and executable on the processor, wherein the processor executes the computer program to implement the cargo loading and unloading control method based on the aircraft center of gravity position as described above.

[0033] A fourth aspect of the present application provides a readable storage medium, which stores a computer program. When the computer program is executed by a processor, it is used to implement the above-mentioned method for controlling loading and unloading cargo based on the center of gravity position of the aircraft.

[0034] The present application can be flexibly applied to aircrafts of different models, and can quickly realize the measurement of weight and center of gravity. The aircraft can measure the weight and center of gravity by itself at any time, and does not require special weighing equipment. It has good environmental adaptability and low economic cost. BRIEF DESCRIPTION OF THE DRAWINGS

[0035] Figure 1 It is a flow chart of a preferred embodiment of the cargo loading and unloading control method based on the center of gravity position of the aircraft of the present application.

[0036] Figure 2 This is a schematic diagram of the sensor assembly installation.

[0037] Figure 3 It is a schematic diagram of sensor arrangement.

[0038] Figure 4 This is a schematic diagram showing the aircraft's center of gravity.

[0039] Figure 5 It is a schematic diagram of the system architecture of the cargo loading and unloading control device based on the center of gravity position of the aircraft in this application.

[0040] Figure 6 It is a schematic diagram of the structure of a computer device suitable for implementing the embodiments of the present application.

[0041] Among them, 1-landing gear, 2-threading hole, 3-sensor assembly, 4-wiring harness, 5-stress sensor, 6-support frame. DETAILED DESCRIPTION

[0042] In order to make the purpose, technical scheme and advantages of the implementation of this application clearer, the technical scheme in the implementation of this application will be described in more detail in combination with the drawings in the implementation of this application. In the drawings, the same or similar reference numerals throughout represent the same or similar elements or elements with the same or similar functions. The described implementation is a part of the implementation of this application, not all of the implementations. The implementation described below with reference to the drawings is exemplary and is intended to be used to explain this application, and cannot be understood as a limitation on this application. Based on the implementation in this application, all other implementations obtained by ordinary technicians in this field without making creative work are within the scope of protection of this application. The implementation of this application is described in detail below in combination with the drawings.

[0043] The present application provides a method for controlling cargo loading and unloading based on the center of gravity position of an aircraft, such as Figure 1 As shown, it mainly includes:

[0044] Step S1, when the aircraft is loading or unloading, obtaining data of stress sensors installed on multiple landing gear axles;

[0045] Step S2, calculating the center of gravity of the aircraft in real time based on data from multiple stress sensors;

[0046] Step S3, marking the position of the center of gravity of the aircraft in a preset aircraft plane diagram having multiple indication ranges;

[0047] Step S4: providing warning information corresponding to the indicated range.

[0048] The present application sets a stress sensor for each landing gear wheel axle. Each sensor transmits the collected stress and strain data to the data processing unit located in the aircraft equipment compartment through a signal line. By processing the aggregated data, the aircraft's center of gravity position data can be calculated in real time. The data is sent to the aircraft data management computer via the CAN bus data, and then sent to the aircraft cockpit display instrument, so that the pilot can easily observe whether the aircraft's center of gravity is within a safe range.

[0049] In some optional embodiments, the stress sensors include at least three, which are respectively installed at a front landing gear axle and two main landing gear axles.

[0050] In this embodiment, the landing gear of the aircraft generally includes a front landing gear and two or more main landing gears. Stress values ​​are obtained through stress sensors at the front landing gear and at least two main landing gear axles, and the weight and center of gravity of the entire aircraft can be calculated.

[0051] In some optional embodiments, the stress sensor includes six groups, two groups of sensor components 3 are arranged on the front landing gear axle near the two front wheels, two groups of sensor components 3 are arranged on the first main landing gear axle on the left side of the aircraft near the two left main wheels, and two groups of sensor components 3 are arranged on the second main landing gear axle on the right side of the aircraft near the two right main wheels, and each group of sensor components 3 is connected to the data processing unit through the wiring harness 4 via the threading hole 2 of the axle.

[0052] refer to Figure 2 The landing gear 1 here can be the front landing gear or the main landing gear. A sensor assembly 3 is arranged at the axle connecting the wheels on both sides inside the landing gear 1. When the aircraft is parked on the ground, each wheel bears a certain load, causing the axle of the landing gear 1 to be deformed by force, and this deformation and the stress received here are collected by the sensor assembly 3. The stress and strain data at the axle collected by the sensor assembly 3 are transmitted to the aircraft data processing unit through the threading hole 2 on the landing gear 1 by the wire harness 4. The data processing unit processes the collected data and converts it into load data on each wheel through an algorithm, and further calculates the aircraft weight and center of gravity data, and then transmits the obtained data to the aircraft data management computer through the bus, and finally displays it on the cockpit display.

[0053] In some optional embodiments, the sensor assembly 3 includes a plurality of stress sensors 5 arranged circumferentially on the annular surface of the support frame 6 of the wheel axle.

[0054] In this embodiment, the sensor assembly 3 can be designed to match the wheel axle size of the aircraft. In order to measure the accuracy of the data, the sensor assembly 3 can evenly distribute multiple sensors 5 on the support frame 6. Figure 3 As shown, the data of each sensor 5 is used as the measurement data of the sensor assembly 3 after weighted calculation.

[0055] In some optional embodiments, in step S3, the indication range includes a circle for representing the center of the aircraft and a plurality of annular bands concentric with the circle; when the position of the center of gravity of the aircraft is within the circle, it is used to indicate that the aircraft loading and unloading process is in a safe state; when the position of the center of gravity of the aircraft is within the annular bands, it is used to indicate that the aircraft loading and unloading process is in a dangerous state.

[0056] The data processing unit sends the collected data to the aircraft data management computer, and the center of gravity calculation unit of the aircraft data management computer calculates the weight and center of gravity, and finally displays it on the cockpit display, such as Figure 4 As shown, the displayed content usually includes the gravity at each sensor component, the total weight G of the entire aircraft and the center of gravity coordinates (H, Z). In addition, it also includes a graphical display of the center of gravity of the aircraft, which includes a circle located at the center of the aircraft, representing the safe area, and multiple annular areas outside the circle to represent different levels of danger.

[0057] In some optional embodiments, the annular belts include at least two, and the danger level of the inner annular belt is lower than the danger level of the outer annular belt.

[0058] refer to Figure 4 The asterisk in the figure indicates the center of gravity of the aircraft, area a is the safe area, area b is the inner annular area, and area c is the outer annular area. When the aircraft is loading or unloading cargo on the ground, the weight center of gravity of the aircraft can be monitored in real time.

[0059] In some optional implementations, step S4 further includes:

[0060] When the center of gravity of the aircraft is located within the inner annular zone, the aircraft sends a first warning signal, wherein the first warning signal is used to indicate that the center of gravity of the aircraft is at the boundary of the center of gravity range, prompting that subsequent loading and unloading should be replanned;

[0061] When the center of gravity of the aircraft is located within the outer annular zone, the aircraft sends a second warning signal, wherein the second warning signal is used to indicate that the center of gravity of the aircraft is outside the center of gravity range, prompting that the cargo remaining in the aircraft after loading or unloading must be re-planned.

[0062] In this embodiment, when the center of gravity mark is in area a, it indicates that the loaded cargo is reasonably distributed and the center of gravity of the aircraft is within the designed center of gravity range. When the center of gravity mark is in area b, it indicates that the center of gravity of the aircraft is already at the boundary of the designed center of gravity range, and the aircraft issues an alarm, prompting that the subsequent loading of cargo should be re-planned; when the center of gravity mark is in area c, it indicates that the center of gravity of the aircraft has exceeded the designed center of gravity range of the aircraft, and there is a danger. The aircraft issues a danger warning, prompting that the loaded cargo must be re-planned.

[0063] The present application can be flexibly applied to aircrafts of different models, and can quickly realize the measurement of weight and center of gravity. The aircraft can measure the weight and center of gravity by itself at any time, and does not require special weighing equipment. It has good environmental adaptability and low economic cost.

[0064] The second aspect of the present application provides a cargo loading and unloading control device based on the center of gravity position of an aircraft corresponding to the above method, such as Figure 5 As shown, it mainly includes:

[0065] a data processing unit for acquiring data from stress sensors installed on a plurality of landing gear axles when the aircraft is being loaded or unloaded;

[0066] A center of gravity calculation unit, used to calculate the center of gravity of the aircraft in real time based on data from multiple stress sensors;

[0067] A display control unit, used for marking the position of the center of gravity of the aircraft in a preset aircraft plane schematic diagram having multiple indication ranges;

[0068] The alarm unit is used to give alarm information corresponding to the indicated range.

[0069] In some optional embodiments, the stress sensors include at least three, which are respectively installed at a front landing gear axle and two main landing gear axles.

[0070] In some optional embodiments, the stress sensor includes six groups, two groups of sensor components 3 are arranged on the front landing gear axle near the two front wheels, two groups of sensor components 3 are arranged on the first main landing gear axle on the left side of the aircraft near the two left main wheels, and two groups of sensor components 3 are arranged on the second main landing gear axle on the right side of the aircraft near the two right main wheels, and each group of sensor components 3 is connected to the data processing unit through the wiring harness 4 via the threading hole 2 of the axle.

[0071] In some optional embodiments, the sensor assembly 3 includes a plurality of stress sensors 5 arranged circumferentially on the annular surface of the support frame 6 of the wheel axle.

[0072] In some optional embodiments, in the display control unit, the indication range includes a circle for representing the center of the aircraft and a plurality of annular bands concentric with the circle; when the position of the center of gravity of the aircraft is within the circle, it is used to indicate that the aircraft loading and unloading process is in a safe state; when the position of the center of gravity of the aircraft is within the annular bands, it is used to indicate that the aircraft loading and unloading process is in a dangerous state.

[0073] In some optional embodiments, the annular belts include at least two, and the danger level of the inner annular belt is lower than the danger level of the outer annular belt.

[0074] In some optional implementations, the alarm unit includes:

[0075] A first warning signal generating module, configured to cause the aircraft to send a first warning signal when the center of gravity of the aircraft is located within the inner annular zone, wherein the first warning signal is used to indicate that the center of gravity of the aircraft is at the boundary of the center of gravity range, prompting that subsequent loading and unloading should be replanned;

[0076] The second warning signal generating module is used for the aircraft to send out a second warning signal when the center of gravity of the aircraft is located within the outer annular zone. The second warning signal is used to indicate that the center of gravity of the aircraft is outside the center of gravity range, prompting that the cargo remaining in the aircraft after loading or unloading must be re-planned.

[0077] In a third aspect of the present application, a computer device includes a processor, a memory, and a computer program stored in the memory and executable on the processor, wherein the processor executes the computer program to implement a method for controlling loading and unloading cargo based on the center of gravity position of an aircraft.

[0078] In a fourth aspect of the present application, a readable storage medium stores a computer program, and when the computer program is executed by a processor, it is used to implement the above-mentioned method for controlling loading and unloading cargo based on the center of gravity position of the aircraft. The computer-readable storage medium may be included in the device described in the above-mentioned embodiment; or it may exist independently without being assembled into the device. The above-mentioned computer-readable storage medium carries one or more programs, and when the above-mentioned one or more programs are executed by the device, the data is processed according to the above-mentioned method.

[0079] Reference below Figure 6 , which shows a schematic structural diagram of a computer device 400 suitable for implementing the embodiments of the present application. Figure 6 The computer device shown is only an example and should not bring any limitation to the functions and scope of use of the embodiments of the present application.

[0080] like Figure 6 As shown, the computer device 400 includes a central processing unit (CPU) 401, which can perform various appropriate actions and processes according to a program stored in a read-only memory (ROM) 402 or a program loaded from a storage part 408 into a random access memory (RAM) 403. In the RAM 403, various programs and data required for the operation of the device 400 are also stored. The CPU 401, the ROM 402, and the RAM 403 are connected to each other via a bus 404. An input / output (I / O) interface 405 is also connected to the bus 404.

[0081] The following components are connected to the I / O interface 405: an input section 406 including a keyboard, a mouse, etc.; an output section 407 including a cathode ray tube (CRT), a liquid crystal display (LCD), etc., and a speaker, etc.; a storage section 408 including a hard disk, etc.; and a communication section 409 including a network interface card such as a LAN card, a modem, etc. The communication section 409 performs communication processing via a network such as the Internet. A drive 410 is also connected to the I / O interface 405 as needed. A removable medium 411, such as a magnetic disk, an optical disk, a magneto-optical disk, a semiconductor memory, etc., is installed on the drive 410 as needed, so that a computer program read therefrom is installed into the storage section 408 as needed.

[0082] In particular, according to the embodiment of the present application, the process described above with reference to the flowchart can be implemented as a computer software program. For example, the embodiment of the present application includes a computer program product, which includes a computer program carried on a computer-readable medium, and the computer program includes a program code for executing the method shown in the flowchart. In such an embodiment, the computer program can be downloaded and installed from the network through the communication part 409, and / or installed from the removable medium 411. When the computer program is executed by the central processing unit (CPU) 401, the above functions defined in the method of the present application are executed. It should be noted that the computer storage medium of the present application can be a computer-readable signal medium or a computer-readable storage medium or any combination of the above two. The computer-readable storage medium can be, for example, - but not limited to - a system, device or device of electricity, magnetism, light, electromagnetic, infrared, or semiconductor, or any combination of the above. More specific examples of computer-readable storage media may include, but are not limited to, an electrical connection with one or more conductors, a portable computer disk, a hard disk, a random access memory (RAM), a read-only memory (ROM), an erasable programmable read-only memory (EPROM or flash memory), an optical fiber, a portable compact disk read-only memory (CD-ROM), an optical storage device, a magnetic storage device, or any suitable combination of the above. In the present application, a computer-readable storage medium may be any tangible medium containing or storing a program that can be used by or in combination with an instruction execution system, an apparatus or a device. In the present application, a computer-readable signal medium may include a data signal propagated in a baseband or as part of a carrier wave, which carries a computer-readable program code. Such propagated data signals may take a variety of forms, including but not limited to electromagnetic signals, optical signals, or any suitable combination of the above. A computer-readable signal medium may also be any computer-readable medium other than a computer-readable storage medium, which may send, propagate, or transmit a program for use by or in combination with an instruction execution system, an apparatus or a device. The program code contained on the computer-readable medium may be transmitted using any appropriate medium, including but not limited to: wireless, wire, optical cable, RF, etc., or any suitable combination of the above.

[0083] The flow chart and block diagram in the accompanying drawings illustrate the possible architecture, function and operation of the system, method and computer program product according to various embodiments of the present application. In this regard, each square box in the flow chart or block diagram can represent a module, a program segment or a part of a code, and the module, the program segment or a part of the code contains one or more executable instructions for realizing the specified logical function. It should also be noted that in some implementations as replacements, the functions marked in the square box can also occur in a sequence different from that marked in the accompanying drawings. For example, two square boxes represented in succession can actually be executed substantially in parallel, and they can sometimes be executed in the opposite order, depending on the functions involved. It should also be noted that each square box in the block diagram and / or flow chart, and the combination of the square boxes in the block diagram and / or flow chart can be implemented with a dedicated hardware-based system that performs a specified function or operation, or can be implemented with a combination of dedicated hardware and computer instructions.

[0084] The modules or units involved in the embodiments described in this application may be implemented by software or hardware. The modules or units described may also be set in a processor, and the names of these modules or units do not constitute limitations on the modules or units themselves in some cases.

[0085] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. A method for controlling cargo loading and unloading based on the center of gravity position of an aircraft, characterized in that: include: Step S1, when the aircraft is loading or unloading, obtaining data of stress sensors installed on multiple landing gear axles; Step S2, calculating the center of gravity of the aircraft in real time based on data from multiple stress sensors; Step S3, marking the position of the center of gravity of the aircraft in a preset aircraft plane diagram having multiple indication ranges; Step S4: providing warning information corresponding to the indicated range.

2. The cargo loading and unloading control method based on the aircraft center of gravity position according to claim 1, characterized in that: The stress sensors include at least three, which are respectively installed at a front landing gear axle and two main landing gear axles.

3. The method for controlling cargo loading and unloading based on the center of gravity position of an aircraft according to claim 2, characterized in that: The stress sensors include six groups, two groups of sensor assemblies (3) are arranged on the front landing gear axle near the two front wheels, two groups of sensor assemblies (3) are arranged on the first main landing gear axle on the left side of the aircraft near the two left main wheels, and two groups of sensor assemblies (3) are arranged on the second main landing gear axle on the right side of the aircraft near the two right main wheels. Each group of sensor assemblies (3) is connected to a data processing unit via a wire harness (4) through a threading hole (2) of the axle.

4. The method for controlling cargo loading and unloading based on the center of gravity position of an aircraft according to claim 3, characterized in that: The sensor assembly (3) comprises a plurality of stress sensors (5) arranged along the circumferential direction on the annular surface of a support frame (6) of the wheel axle.

5. The method for controlling cargo loading and unloading based on the center of gravity position of an aircraft according to claim 1, characterized in that: In step S3, the indication range includes a circle for indicating the center of the aircraft and a plurality of annular bands concentric with the circle. When the position of the center of gravity of the aircraft is within the circle, it is used to indicate that the aircraft loading and unloading process is in a safe state. When the position of the center of gravity of the aircraft is within the annular bands, it is used to indicate that the aircraft loading and unloading process is in a dangerous state.

6. The method for controlling cargo loading and unloading based on the center of gravity position of an aircraft according to claim 5, characterized in that: The annular belts include at least two, and the danger level of the inner annular belt is lower than the danger level of the outer annular belt.

7. The method for controlling cargo loading and unloading based on the center of gravity position of an aircraft according to claim 6, characterized in that: Step S4 further comprises: When the center of gravity of the aircraft is located within the inner annular zone, the aircraft sends a first warning signal, wherein the first warning signal is used to indicate that the center of gravity of the aircraft is at the boundary of the center of gravity range, prompting that subsequent loading and unloading should be replanned; When the center of gravity of the aircraft is located within the outer annular zone, the aircraft sends a second warning signal, wherein the second warning signal is used to indicate that the center of gravity of the aircraft is outside the center of gravity range, prompting that the cargo remaining in the aircraft after loading or unloading must be re-planned.

8. A cargo loading and unloading control device based on the center of gravity position of an aircraft, characterized in that: include: a data processing unit for acquiring data from stress sensors installed on a plurality of landing gear axles when the aircraft is being loaded or unloaded; A center of gravity calculation unit, used to calculate the center of gravity of the aircraft in real time based on data from multiple stress sensors; A display control unit, used for marking the position of the center of gravity of the aircraft in a preset aircraft plane schematic diagram having multiple indication ranges; The alarm unit is used to give alarm information corresponding to the indicated range.

9. The cargo loading and unloading control device based on the aircraft center of gravity position according to claim 8, characterized in that: The stress sensors include at least three, which are respectively installed at a front landing gear axle and two main landing gear axles.

10. The cargo loading and unloading control device based on the aircraft center of gravity position according to claim 9, characterized in that: The stress sensors include six groups, two groups of sensor assemblies (3) are arranged on the front landing gear axle near the two front wheels, two groups of sensor assemblies (3) are arranged on the first main landing gear axle on the left side of the aircraft near the two left main wheels, and two groups of sensor assemblies (3) are arranged on the second main landing gear axle on the right side of the aircraft near the two right main wheels. Each group of sensor assemblies (3) is connected to a data processing unit via a wire harness (4) through a threading hole (2) of the axle.

11. The cargo loading and unloading control device based on the aircraft center of gravity position according to claim 10, characterized in that: The sensor assembly (3) comprises a plurality of stress sensors (5) arranged along the circumferential direction on the annular surface of a support frame (6) of the wheel axle.

12. The cargo loading and unloading control device based on the aircraft center of gravity position according to claim 8, characterized in that: In the display control unit, the indication range includes a circle for indicating the center of the aircraft and a plurality of annular bands concentric with the circle. When the position of the center of gravity of the aircraft is within the circle, it is used to indicate that the aircraft loading and unloading process is in a safe state. When the position of the center of gravity of the aircraft is within the annular bands, it is used to indicate that the aircraft loading and unloading process is in a dangerous state.

13. The cargo loading and unloading control device based on the aircraft center of gravity position according to claim 12, characterized in that: The annular belts include at least two, and the danger level of the inner annular belt is lower than the danger level of the outer annular belt.

14. The cargo loading and unloading control device based on the aircraft center of gravity position according to claim 13, characterized in that: The alarm unit comprises: A first warning signal generating module, configured to cause the aircraft to send a first warning signal when the center of gravity of the aircraft is located within the inner annular zone, wherein the first warning signal is used to indicate that the center of gravity of the aircraft is at the boundary of the center of gravity range, prompting that subsequent loading and unloading should be replanned; The second warning signal generating module is used for the aircraft to send out a second warning signal when the center of gravity of the aircraft is located within the outer annular zone. The second warning signal is used to indicate that the center of gravity of the aircraft is outside the center of gravity range, prompting that the cargo remaining in the aircraft after loading or unloading must be re-planned.

15. A computer device, characterized in that: The method comprises a processor, a memory, and a computer program stored in the memory and executable on the processor, wherein the processor executes the computer program to implement the cargo loading and unloading control method based on the center of gravity position of the aircraft as described in any one of claims 1 to 7.

16. A readable storage medium storing a computer program, characterized in that: When the computer program is executed by a processor, it is used to implement the cargo loading and unloading control method based on the center of gravity position of the aircraft as described in any one of claims 1 to 7.

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