A method for monitoring maintenance of an aircraft weapon external store rack

Abstract

The application relates to a kind of aircraft weapon external hanger maintenance monitoring methods, through the setting multiple displacement sensors, temperature sensors and wind speed sensors in external hanger, the aircraft weapon external hanger condition is monitored, and whether the maintenance is needed is prompted through aircraft central control platform, the above-mentioned method can be monitored in different states of aircraft weapon external hanger, and through the setting of wind speed sensor, whether the sensor can be damaged can also be evaluated, further improve the aircraft weapon external hanger monitoring accuracy.

Description

Technical Field

[0001] This invention belongs to the field of equipment testing technology, specifically a method for maintenance and monitoring of aircraft weapon pylons. Background Technology

[0002] Current aircraft weapon pylon maintenance and monitoring typically involves periodic inspections, which suffers from latency. Real-time monitoring solutions usually involve using cameras or periodically taking pictures, modeling the image data, and then comparing the morphology. However, these methods are computationally intensive, placing a heavy burden on the aircraft's computing resources. Sensor-based solutions for aircraft weapon pylons typically use coordinate axes set on the aircraft body, with a reference point at the midpoint of the aircraft body to measure the distance to the pylons. However, this method may introduce errors during flight due to the high speeds involved.

[0003] Therefore, there is an urgent need for a maintenance and monitoring method for aircraft weapon pylons that can solve the above problems. Summary of the Invention

[0004] To address the aforementioned issues, this invention proposes a maintenance and monitoring method for aircraft weapon pylons. This method involves monitoring the condition of the pylons by installing multiple displacement sensors, temperature sensors, and wind speed sensors. The aircraft's central control platform then provides alerts regarding the need for maintenance. This method enables monitoring of the aircraft weapon pylons under various conditions. Furthermore, the wind speed sensors allow for assessment of potential sensor damage, further improving the accuracy of the aircraft weapon pylon monitoring.

[0005] A method for maintenance and monitoring of aircraft weapon pylons, the method employing multiple displacement sensors, multiple wind speed sensors, multiple temperature sensors, and an aircraft central control platform; the method performs the following steps:

[0006] S1. The weapon hardpoints are symmetrically arranged on both sides of the fuselage, and when the aircraft is stationary on a flat ground, the height of each part of the weapon hardpoints on both sides is the same.

[0007] S2. The weapon external hardpoints on both sides have the same structure, each including a fuselage connecting shaft, a left mounting component, and a right mounting component;

[0008] S3. The plurality of displacement sensors are respectively placed at the connection points between the fuselage connecting shaft and the fuselage on both sides, and are respectively the left reference displacement sensor and the right reference displacement sensor;

[0009] S4. The plurality of displacement sensors are also respectively placed inside the four hanging components to form a displacement sensor matrix;

[0010] S5. All four mounting components are freely extendable and retractable. When the control signal of the control system is a closed signal, the four mounting components are hidden inside the fuselage; when the control signal of the control system is an open signal, all four mounting components can extend out of the fuselage carrying aircraft weapons.

[0011] S6. The aircraft's mid-altitude platform collects position change data from each displacement sensor. When the displacement sensor data is abnormal, it indicates that maintenance is required.

[0012] Furthermore, the plurality of displacement sensors are respectively placed inside the four mounting components to form a displacement sensor matrix, including:

[0013] S41. The plurality of displacement sensors are symmetrically distributed in pairs on both sides of the fuselage;

[0014] S42. The left and right mounting components of the weapon external hardpoints on the same side of the fuselage are both arc-shaped, and the two mounting components on the same side of the fuselage have their center sides facing each other, and their arc and length are the same.

[0015] S43. The plurality of displacement sensors are respectively installed in the left and right attachment components on the same side of the fuselage, and the plurality of displacement sensors are symmetrically distributed in pairs between the two attachment components on the same side of the aircraft.

[0016] Furthermore, S51. After the aircraft starts, each displacement sensor periodically records its distance from the reference displacement sensor on the same side, and the aircraft central control platform records the displacement sensor data matrix with time as an identifier and saves the displacement sensor data matrix.

[0017] Furthermore, S61. When the control signal of the control system is not an activation signal, the aircraft central control platform determines whether the positions of the four attachment components are abnormal based on the real-time data of the displacement sensor data matrix.

[0018] Furthermore, S611. When the external rack of the aircraft is normal, the distance data between each displacement sensor and the reference displacement sensor on the same side is recorded;

[0019] S612. The aircraft central control platform compares the real-time data of the displacement sensor data matrix with the distance data in step S611. If the comparison data is abnormal, it prompts that maintenance is required.

[0020] Further, in step S6121, the aircraft central control platform compares the real-time data from the displacement sensor data matrix with the distance data from step S611, specifically as follows:

[0021] Different data from the same displacement sensor are subtracted and their absolute values ​​are taken. If the absolute value is greater than a first threshold, the comparison data is considered abnormal.

[0022] Furthermore, S62. When the control signal of the control system is an activation signal, the aircraft central control platform determines whether the positions of the four attachment components are abnormal based on the data from the displacement sensor data matrix.

[0023] Further, S621. The control signal of the control system is the time from the start time to the time when the aircraft weapon hardpoints are completely placed outside the fuselage and the shape of the aircraft weapon hardpoints no longer changes within a first time threshold, which is taken as the first preset time period;

[0024] S622. Based on the position data of each displacement sensor relative to the same-side reference displacement sensor collected within the first preset time period, a pseudo motion trajectory of each displacement sensor is formed. Based on the pseudo motion trajectory, the aircraft central control platform can determine whether the aircraft weapon hardpoint is abnormal.

[0025] Furthermore, S6221. Set the pseudo motion trajectory reference data for the aircraft weapon hardpoint on either side;

[0026] S6222. Determine whether the aircraft weapon hardpoint on that side is abnormal based on the pseudo motion trajectory reference data;

[0027] When abnormal data is present, the pseudo motion trajectory reference data of the aircraft weapon hardpoint on the other side is obtained by real-time mirroring, and the abnormality of the aircraft weapon hardpoint on the other side is determined based on the pseudo motion trajectory reference data obtained by real-time mirroring.

[0028] S6223. When there is no abnormal data, determine whether the aircraft weapon hardpoint on the other side is abnormal based on the pseudo motion trajectory data.

[0029] Furthermore, the method for determining whether the aircraft weapon pylon is abnormal is as follows: the distance data between each displacement sensor and the reference displacement sensor on the same side can form a relative position data matrix. Within the first preset time period, multiple relative position data matrices can be acquired, with the nth time as the identifier; n>0, where n is a natural number.

[0030] The pseudo-motion trajectory reference data is a data matrix of the same number as the plurality of relative position data matrices, with the m-th time corresponding to the n-th time as the identifier m>0, where m is a natural number;

[0031] When m=n, if there are no abnormalities in the aircraft weapon pylons, the difference data of the same displacement sensor is less than the second threshold after taking the absolute value of the difference between the relative position data matrix and the pseudo motion trajectory reference data matrix.

[0032] The advantages of this invention are:

[0033] 1. By setting up displacement sensors and reference displacement sensors to determine the relative position of the equipment, the error in displacement detection can be minimized during aircraft flight.

[0034] 2. By determining whether the aircraft's weapon pylons are abnormal in different ways based on whether the aircraft extends them via a control device, when the control signal is not an activation signal, the distance data from the same-side reference displacement sensor is used to determine whether the pylons are abnormal; when the control signal is an activation signal, the two mounting components on one side are compared with the reference data, and based on the comparison results, different data are used to determine the abnormality of the two mounting components on the other side. This method can reduce the aircraft's computing resources when no other monitoring equipment is present.

[0035] 3. By setting temperature sensors, the temperature information of the aircraft weapon pylons can be measured. Since temperature parameters are not sensitive, after multiple displacement sensors determine that there is no abnormality in the aircraft, confirmation is made based on the temperature sensors. By setting multiple wind speed sensors on each mounting component, it is possible to monitor whether there are potential faults in the sensors. Attached Figure Description

[0036] Various other advantages and benefits will become apparent to those skilled in the art upon reading the following detailed description of preferred embodiments. The accompanying drawings are for illustrative purposes only and are not intended to limit the invention. Furthermore, the same reference numerals denote the same parts throughout the drawings. In the drawings:

[0037] Figure 1 Flowchart for aircraft weapon external hardpoint maintenance and monitoring methods Detailed Implementation

[0038] To make the objectives, technical solutions, and advantages of this application clearer, the application is described and illustrated below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative and not intended to limit the scope of this application. All other embodiments obtained by those skilled in the art based on the embodiments provided in this application without inventive effort are within the scope of protection of this application.

[0039] Obviously, the accompanying drawings described below are merely some examples or embodiments of this application. Those skilled in the art can apply this application to other similar scenarios based on these drawings without any inventive effort. Furthermore, it is understood that although the efforts made in this development process may be complex and lengthy, for those skilled in the art related to the content disclosed in this application, any changes to design, manufacturing, or production based on the technical content disclosed in this application are merely conventional technical means and should not be construed as insufficient disclosure of the content of this application.

[0040] In this application, the reference to "embodiment" means that a specific feature, structure, or characteristic described in connection with an embodiment may be included in at least one embodiment of this application. The appearance of this phrase in various places in the specification does not necessarily refer to the same embodiment, nor is it a separate or alternative embodiment that is mutually exclusive with other embodiments. It will be explicitly and implicitly understood by those skilled in the art that the embodiments described in this application may be combined with other embodiments without conflict.

[0041] Unless otherwise defined, the technical or scientific terms used in this application shall have the ordinary meaning understood by one of ordinary skill in the art to which this application pertains. The terms “a,” “an,” “an,” “the,” and similar words used in this application do not indicate quantity limitation and may represent singular or plural. The terms “comprising,” “including,” “having,” and any variations thereof used in this application are intended to cover non-exclusive inclusion; for example, a process, method, system, product, or apparatus that includes a series of steps or modules (units) is not limited to the listed steps or units, but may also include steps or units not listed, or may include other steps or units inherent to these processes, methods, products, or apparatuses.

[0042] The flowchart of the database storage encryption method proposed in this invention is as follows: Figure 1 As shown.

[0043] A method for maintenance and monitoring of aircraft weapon pylons, the method employing multiple displacement sensors, multiple wind speed sensors, multiple temperature sensors, and an aircraft central control platform; the method performs the following steps:

[0044] S1. The weapon hardpoints are symmetrically arranged on both sides of the fuselage, and when the aircraft is stationary on a flat ground, the height of each part of the weapon hardpoints on both sides is the same.

[0045] S2. The weapon external hardpoints on both sides have the same structure, each including a fuselage connecting shaft, a left mounting component, and a right mounting component;

[0046] S3. The plurality of displacement sensors are respectively placed at the connection points between the fuselage connecting shaft and the fuselage on both sides, and are respectively the left reference displacement sensor and the right reference displacement sensor;

[0047] S4. The plurality of displacement sensors are also respectively placed inside the four hanging components to form a displacement sensor matrix;

[0048] S5. All four mounting components are freely extendable and retractable. When the control signal of the control system is a closed signal, the four mounting components are hidden inside the fuselage; when the control signal of the control system is an open signal, all four mounting components can extend out of the fuselage carrying aircraft weapons.

[0049] S6. The aircraft's mid-altitude platform collects position change data from each displacement sensor. When the displacement sensor data is abnormal, it indicates that maintenance is required.

[0050] Furthermore, the plurality of displacement sensors are respectively placed inside the four mounting components to form a displacement sensor matrix, including:

[0051] S41. The plurality of displacement sensors are symmetrically distributed in pairs on both sides of the fuselage;

[0052] S42. The left and right mounting components of the weapon external hardpoints on the same side of the fuselage are both arc-shaped, and the two mounting components on the same side of the fuselage have their center sides facing each other, and their arc and length are the same.

[0053] S43. The plurality of displacement sensors are respectively installed in the left and right attachment components on the same side of the fuselage, and the plurality of displacement sensors are symmetrically distributed in pairs between the two attachment components on the same side of the aircraft.

[0054] Furthermore, S51. After the aircraft starts, each displacement sensor periodically records its distance from the reference displacement sensor on the same side, and the aircraft central control platform records the displacement sensor data matrix with time as an identifier and saves the displacement sensor data matrix.

[0055] Furthermore, S61. When the control signal of the control system is not an activation signal, the aircraft central control platform determines whether the positions of the four attachment components are abnormal based on the real-time data of the displacement sensor data matrix.

[0056] Furthermore, S611. When the external rack of the aircraft is normal, the distance data between each displacement sensor and the reference displacement sensor on the same side is recorded;

[0057] Further, step S611 records the distance data between each displacement sensor and the reference displacement sensor on the same side, specifically including:

[0058] S6111. Each displacement sensor acquires an image from a reference displacement sensor on the same side;

[0059] S6112. Based on the length L1 and width K1 of the same-side reference displacement sensor in the image acquired by each displacement sensor, the length L2 and width K2 of the same-side reference displacement sensor in the image acquired by each displacement sensor at the previous moment, and the distance Ds between each displacement sensor and the same-side reference displacement sensor at the previous moment, calculate the distance Dx between each displacement sensor and the same-side reference displacement sensor; where,

[0060]

[0061] S6113. The image of each displacement sensor in each displacement sensor is acquired by the same-side reference displacement sensor;

[0062] S6114. Based on the length L3 and width K3 of the displacement sensor in the image of each displacement sensor acquired by the same-side reference displacement sensor, the length L4 and width K4 of the displacement sensor in the image of each displacement sensor acquired by the same-side reference displacement sensor at the previous moment, and the distance Ds between the same-side reference displacement sensor and each displacement sensor at the previous moment, calculate the distance Dp between the same-side reference displacement sensor and each displacement sensor; where:

[0063]

[0064] S6115. According to D x and D p Obtain the distance between each displacement sensor and the reference displacement sensor on the same side.

[0065] The initial distance between each displacement sensor and the reference displacement sensor on the same side, the actual length and width of each displacement sensor, and the actual length and width of the reference displacement sensor on the same side are all pre-measured and stored.

[0066] When each displacement sensor and the same-side reference displacement sensor are arranged in the initial position, the length and width of the displacement sensor in the image of each displacement sensor acquired by the same-side reference displacement sensor, and the length and width of the same-side reference displacement sensor in the image of the same-side reference displacement sensor acquired by each displacement sensor are all pre-measured and stored.

[0067] The lengths and widths of the sensors in the image in steps S6111 - S6115 refer to the lengths and widths of the sensors in the image identified by the image recognition algorithm and obtained through calculation; the actual lengths and widths of the sensors are the actual lengths and widths of the sensor devices in the natural environment.

[0068] In step S6115, D x and D p Obtain the distances between each displacement sensor and the reference displacement sensor on the same side, specifically including:

[0069] S61151. When |D x - D p | > C, add 1 to the preset register value and return to execute steps S6111 - S6115; where C is the preset distance difference threshold;

[0070] S61152. When the preset register value exceeds the preset threshold T, issue a sensor maintenance alarm and reset the preset register value to 0; preferably, T is 1 - 5;

[0071] S61153. When |D x - D p | < C, obtain the distances between each displacement sensor and the reference displacement sensor on the same side

[0072] Each of the displacement sensors and the reference displacement sensor on the same side includes a sensing module and an image acquisition module; the sensing module is used to collect displacement data, and the image acquisition module is used to collect image data.

[0073] S612. The aircraft central control platform compares the real - time data of the displacement sensor data matrix with the distance data in step S611. If the comparison data is abnormal, it prompts that maintenance is required.

[0074] Further, S6121. The specific comparison of the real - time data of the displacement sensor data matrix by the aircraft central control platform with the distance data in step S611 is as follows:

[0075] Take the absolute value after taking the difference between different data of the same displacement sensor. When the absolute value is greater than the first threshold, it is determined that the comparison data is abnormal.

[0076] Further, S62. When the control signal of the control system is an opening signal, the aircraft central control platform determines whether the positions of the four hanging components are abnormal based on the data of the displacement sensor data matrix.

[0077] Further, S621. The control signal of the control system is the time from the start time to the time when the aircraft weapon hardpoints are completely placed outside the fuselage and the shape of the aircraft weapon hardpoints no longer changes within a first time threshold, which is taken as the first preset time period;

[0078] S622. Based on the position data of each displacement sensor relative to the same-side reference displacement sensor collected within the first preset time period, a pseudo motion trajectory of each displacement sensor is formed. Based on the pseudo motion trajectory, the aircraft central control platform can determine whether the aircraft weapon hardpoint is abnormal.

[0079] Furthermore, S6221. Set the pseudo motion trajectory reference data for the aircraft weapon hardpoint on either side;

[0080] S6222. Determine whether the aircraft weapon hardpoint on that side is abnormal based on the pseudo motion trajectory reference data;

[0081] When abnormal data is present, the pseudo motion trajectory reference data of the aircraft weapon pylon on the other side is obtained by real-time mirroring, and the abnormality of the aircraft weapon pylon on the other side is determined based on the pseudo motion trajectory reference data obtained by real-time mirroring.

[0082] S6223. When there is no abnormal data, determine whether the aircraft weapon hardpoint on the other side is abnormal based on the pseudo motion trajectory data.

[0083] Furthermore, the method for determining whether the aircraft weapon pylon is abnormal is as follows: the distance data between each displacement sensor and the reference displacement sensor on the same side can form a relative position data matrix. Within the first preset time period, multiple relative position data matrices can be acquired, with the nth time as the identifier; n>0, where n is a natural number.

[0084] The pseudo-motion trajectory reference data is a data matrix of the same number as the plurality of relative position data matrices, with the m-th time corresponding to the n-th time as the identifier m>0, where m is a natural number;

[0085] When m=n, if there are no abnormalities in the aircraft weapon pylons, the difference data of the same displacement sensor is less than the second threshold after taking the absolute value of the difference between the relative position data matrix and the pseudo motion trajectory reference data matrix.

[0086] Furthermore, after the aircraft starts, if there is no abnormality in the aircraft's weapon pylons, it is determined that there is no abnormality in the form, and the process of collecting the temperature of the aircraft's weapon pylons is started to form historical temperature data. When the absolute value of the difference between the temperature and the real-time outdoor temperature is greater than a third threshold, the aircraft's central control platform will prompt a temperature abnormality.

[0087] Furthermore, the multiple wind speed sensors are respectively disposed on the outside of the four attachment components, and multiple wind speed sensors are disposed on the same attachment component; during the first preset time period, wind speed is collected in real time, and based on the wind speed data of the same attachment component, it is determined whether the sensor of the attachment component may be damaged. If the wind speed data is abnormal, the aircraft central control platform will prompt that the wind speed sensor, temperature sensor and displacement sensor may be damaged, and timely maintenance will be carried out.

[0088] The advantages of this invention are:

[0089] 1. By setting up displacement sensors and reference displacement sensors to determine the relative position of the equipment, the error in displacement detection can be minimized during aircraft flight.

[0090] 2. By determining whether the aircraft's weapon pylons are abnormal in different ways based on whether the aircraft extends them via a control device, when the control signal is not an activation signal, the distance data from the same-side reference displacement sensor is used to determine whether the pylons are abnormal; when the control signal is an activation signal, the two mounting components on one side are compared with the reference data, and based on the comparison results, different data are used to determine the abnormality of the two mounting components on the other side. This method can reduce the aircraft's computing resources when no other monitoring equipment is present.

[0091] 3. By setting temperature sensors, the temperature information of the aircraft weapon pylons can be measured. Since temperature parameters are not sensitive, after multiple displacement sensors determine that there is no abnormality in the aircraft, confirmation is made based on the temperature sensors. By setting multiple wind speed sensors on each mounting component, it is possible to monitor whether there are potential faults in the sensors.

[0092] 4. Based on the sensor's length and width in the current measurement image, the sensor's length and width in the previous measurement image, and the distance between the two sensors in the previous measurement, the distance between the two sensors in the current measurement is calculated using a linear scaling method. Compared to traditional methods using acoustic waves or lasers for distance measurement, this method can improve the accuracy of distance calculation in scenarios where sensors are close together. Furthermore, by using mutual distance measurement verification during the distance measurement process between the two sensors, errors are identified. If too many errors occur, it indicates a potential sensor malfunction, prompting the sensor to be inspected and repaired, thus reducing the sensor failure rate.

[0093] The above description is merely a preferred embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in the present invention should be included within the scope of protection of the present invention. Therefore, the scope of protection of the present invention should be determined by the scope of the claims.

Claims

1. A method for maintenance and monitoring of aircraft weapon pylons, characterized in that: The method utilizes multiple displacement sensors, multiple wind speed sensors, multiple temperature sensors, and an aircraft central control platform; the method performs the following steps: S1. The weapon hardpoints are symmetrically arranged on both sides of the fuselage, and when the aircraft is stationary on a flat ground, the height of each part of the weapon hardpoints on both sides is the same. S2. The weapon external hardpoints on both sides have the same structure, each including a fuselage connecting shaft, a left mounting component, and a right mounting component; S3. The plurality of displacement sensors are respectively placed at the connection points between the fuselage connecting shaft and the fuselage on both sides, and are respectively the left reference displacement sensor and the right reference displacement sensor; S4. The plurality of displacement sensors are also respectively placed inside the four hanging components to form a displacement sensor matrix; S5. All four mounting components are freely extendable and retractable. When the control signal of the control system is a closed signal, the four mounting components are hidden inside the fuselage; when the control signal of the control system is an open signal, all four mounting components can extend out of the fuselage carrying aircraft weapons. S6. The aircraft central control platform collects position change data from each displacement sensor. When the displacement sensor data is abnormal, it prompts that maintenance is required.

2. The method for maintenance and monitoring of aircraft weapon pylons according to claim 1, characterized in that: The plurality of displacement sensors are also respectively placed inside the four mounting components, forming a displacement sensor matrix, including: S41. The plurality of displacement sensors are symmetrically distributed in pairs on both sides of the fuselage; S42. The left and right mounting components of the weapon external hardpoints on the same side of the fuselage are both arc-shaped, and the two mounting components on the same side of the fuselage have their center sides facing each other, and their arc and length are the same. S43. The plurality of displacement sensors are respectively installed in the left and right attachment components on the same side of the fuselage, and the plurality of displacement sensors are symmetrically distributed in pairs between the two attachment components on the same side of the aircraft.

3. The method for maintenance and monitoring of aircraft weapon external hardpoints according to claim 2, characterized in that: S51. After the aircraft starts, each displacement sensor periodically records its distance from the reference displacement sensor on the same side. The aircraft central control platform records the displacement sensor data matrix with time as an identifier and saves the displacement sensor data matrix.

4. The method for maintenance and monitoring of aircraft weapon external hardpoints according to claim 3, characterized in that: S61. When the control signal of the control system is not an activation signal, the aircraft central control platform determines whether the positions of the four attachment components are abnormal based on the real-time data of the displacement sensor data matrix.

5. The method for maintenance and monitoring of aircraft weapon external hardpoints according to claim 4, characterized in that: S611. When the external hardpoints of the aircraft are normal, record the distance data between each displacement sensor and the reference displacement sensor on the same side; S612. The aircraft central control platform compares the real-time data of the displacement sensor data matrix with the distance data in step S611. If the comparison data is abnormal, it prompts that maintenance is required.

6. The method for maintenance and monitoring of aircraft weapon pylons according to claim 5, characterized in that: S6121. The aircraft central control platform compares the real-time data based on the displacement sensor data matrix with the distance data in step S611, specifically as follows: Different data from the same displacement sensor are subtracted and their absolute values ​​are taken. If the absolute value is greater than a first threshold, the comparison data is considered abnormal.

7. The method for maintenance and monitoring of aircraft weapon pylons according to claim 6, characterized in that: S62. When the control signal of the control system is an activation signal, the aircraft central control platform determines whether the positions of the four attachment components are abnormal based on the data from the displacement sensor data matrix.

8. The method for maintenance and monitoring of aircraft weapon external hardpoints according to claim 7, characterized in that: S621. The control signal of the control system is the time from the start time to the time when the aircraft weapon hardpoints are completely placed outside the fuselage and the shape of the aircraft weapon hardpoints no longer changes within a first time threshold, which is taken as the first preset time period; S622. Based on the position data of each displacement sensor relative to the same-side reference displacement sensor collected within the first preset time period, a pseudo motion trajectory of each displacement sensor is formed. Based on the pseudo motion trajectory, the aircraft central control platform can determine whether the aircraft weapon hardpoint is abnormal.

9. A method for maintenance and monitoring of aircraft weapon pylons according to claim 8, characterized in that: S6221. Set the pseudo motion trajectory reference data for the aircraft weapon hardpoint on either side; S6222. Determine whether the aircraft weapon hardpoint on this side is abnormal based on the pseudo motion trajectory reference data; When abnormal data is present, the pseudo motion trajectory reference data of the aircraft weapon pylon on the other side is obtained by real-time mirroring, and the abnormality of the aircraft weapon pylon on the other side is determined based on the pseudo motion trajectory reference data obtained by real-time mirroring. S6223. When there is no abnormal data, determine whether the aircraft weapon hardpoint on the other side is abnormal based on the pseudo motion trajectory data.

10. A method for maintenance and monitoring of aircraft weapon pylons according to claim 9, characterized in that: The method for determining whether the aircraft weapon pylon is abnormal is as follows: the distance data between each displacement sensor and the reference displacement sensor on the same side can form a relative position data matrix. Within the first preset time period, multiple relative position data matrices can be acquired, with the nth time as the identifier. n>0, where n is a natural number; The pseudo-motion trajectory reference data is a data matrix of the same number as the plurality of relative position data matrices, with the m-th time corresponding to the n-th time as the identifier m>0, where m is a natural number; When m=n, if there are no abnormalities in the aircraft weapon pylons, the difference data of the same displacement sensor is less than the second threshold after taking the absolute value of the difference between the relative position data matrix and the pseudo motion trajectory reference data matrix.

Images