A method and device for measuring the dynamic load of an aircraft wheel during taxiing

Abstract

The application relates to a kind of aircraft wheel load dynamic measurement methods and devices under the condition of aircraft taxiing, applied to aircraft wheel load measurement technical field, comprising: by setting measurement strip in airport taxiway, and establishing coordinate system based on the measurement strip, and measuring the time of aircraft passing through measurement strip, wheel load and aircraft taxiing speed, longitudinal axle distance and lateral axle distance are calculated by the data obtained, and aircraft wheel load plane matrix diagram is established;According to aircraft wheel load plane matrix diagram, the spatial plane distribution and wheel load of each aircraft wheel of aircraft are obtained;The application automatically generates wheel load matrix diagram, meets the demand of bridge and pavement monitoring, the dimension of the data obtained is complete, the aircraft does not need to be stationary, is measured in real time in taxiing, and does not affect normal operation of airport.

Description

Technical Field

[0001] This invention relates to the field of aircraft wheel load measurement technology, specifically to a method and device for dynamic measurement of aircraft wheel load during taxiing. Background Technology

[0002] The operational monitoring of airport pavement and aircraft wheel-mounted bridges requires accurate acquisition of real-time aircraft wheel loads. Existing aircraft weight measurement mostly uses static weighing technology, which can only complete the weight measurement of the entire aircraft when it is stationary, and cannot achieve dynamic measurement in the taxiing state. At the same time, static measurement cannot obtain the spatial planar distribution of the wheels and the real-time wheel load of each wheel group, which is difficult to match the needs of monitoring and pavement maintenance of wide box girder bridges.

[0003] Existing automotive dynamic weighing technology is only suitable for vehicles with single axle dual wheel sets and uniform wheel track. It cannot be adapted to aircraft wheel set structures with single nose wheel sets, multiple rows and multiple wheels on main wheels, and different lateral wheel track, and cannot meet the requirements for accurate measurement of aircraft wheel load and aircraft type identification. Summary of the Invention

[0004] In view of this, the purpose of the present invention is to provide a method and device for dynamic measurement of wheel load in the taxiing state of an aircraft, which aims to solve the shortcomings of existing static weighing methods that cannot perform dynamic measurement, lack spatial distribution data, and lack real-time wheel load.

[0005] According to a first aspect of the present invention, a method for dynamic measurement of wheel loads of an aircraft during taxiing is provided, the method comprising:

[0006] Measurement strips are set up on the airport taxiway, and a coordinate system is established based on the measurement strips; As each wheel of the aircraft under test slides sequentially across the measurement strip, the X-coordinate value, wheel load, and passage time of the nose wheel of the aircraft under test are obtained; and the X-coordinate value, wheel load, and passage time of each row of main wheels of the aircraft under test are also obtained. The aircraft's speed during taxiing is obtained through pre-set speed measurement and camera devices; Based on the X-coordinate values ​​of each row of main wheels and the nose wheel, as well as the wheel load, establish an X-coordinate-wheel load array for each row of main wheels relative to the nose wheel; The longitudinal wheelbase between the nose wheel and the first row of main wheels is obtained by taking the time between the nose wheel and the first row of main wheels and the speed of the aircraft during taxiing; and the longitudinal wheelbase between the two adjacent rows of main wheels is obtained by taking the time between the two adjacent rows of main wheels and the speed of the aircraft during taxiing. The Y coordinate of each row of main wheels relative to the nose wheel is obtained based on the longitudinal axis distance between the nose wheel and the first row of main wheel shafts, and the longitudinal axis distance between two adjacent rows of main wheel shafts; Based on the X-coordinate-wheel load array of each row of main wheels relative to the nose wheel and the Y-coordinate of each row of main wheels relative to the nose wheel, establish a ternary array of X-coordinate-Y-wheel load for each row of main wheels relative to the nose wheel; Based on the ternary array of X-Y coordinates and wheel load of each row of main wheels relative to the nose wheel, an aircraft wheel load planar matrix diagram is established; The spatial planar distribution and wheel load of each aircraft wheel are obtained from the aircraft wheel load planar matrix diagram.

[0007] Preferably, The step of setting up a measurement zone on the airport taxiway and establishing a coordinate system based on the measurement zone includes: A rectangular measuring strip is set up on the airport taxiway. The length side of the measuring strip is perpendicular to the aircraft taxiing direction and is set as the X-axis; the width side of the measuring strip is parallel to the aircraft taxiing direction and is set as the Y-axis. The aircraft taxiing direction is positive, and the intersection of the X-axis and Y-axis is the origin of the coordinate system. A planar coordinate system is established with the intersection of the X-axis and Y-axis as the origin. The measurement strip is divided into multiple independent measurement modules along the X and Y axes to form a measurement array. Each independent measurement module is assigned an X-coordinate value, and a force sensor is set in each independent measurement module. A speed measuring and camera device is installed on the extension line of the measuring strip.

[0008] Preferably, it further includes: The aircraft's taxiing wheel tracks are located based on the X-coordinates of each wheel during taxiing.

[0009] Preferably, it further includes: The total weight of the aircraft is obtained by summing the wheel loads of each wheel.

[0010] Preferably, it further includes: A model database is pre-built, which stores data on wheel load distribution, wheel set arrangement, wheel track and wheelbase for each model. The aircraft model is identified by comparing and matching the aircraft wheel load plane matrix diagram with the aircraft model database.

[0011] Preferably, The longitudinal wheelbase is calculated as follows: The longitudinal wheelbase between the nose wheel and the first row of main wheels is: L1=(t1-tb)×v In the formula, t1 represents the time it takes for the first row of main wheels to pass through the measuring strip, tb represents the time it takes for the nose wheel to pass through the measuring strip, and v represents the speed of the aircraft during taxiing. The longitudinal wheelbase between the (m-1)th row of main wheels and the mth row of main wheels is: Lm=(tm-t (m-1))×v In the formula, tm represents the time it takes for the m-th row of main wheels to pass through the measuring strip, and t(m-1) represents the time it takes for the (m-1)-th row of main wheels to pass through the measuring strip.

[0012] Preferably, it further includes: Based on the X-coordinate values ​​of adjacent wheels in each row of the aircraft wheel load plane matrix diagram, the lateral wheel spacing of adjacent wheels in each row of the main wheels is obtained. Preferably, it further includes: The speed measuring and camera device detects when an aircraft is about to enter the measurement area and automatically starts the measurement; if no aircraft enters within a preset time after the measurement is started, the measurement is automatically stopped.

[0013] Preferably, The width of the measuring strip is set according to the actual ground contact area of ​​the wheel; The length of the measuring strip is set according to the width of the airport taxiway pavement.

[0014] According to a second aspect of the present invention, a wheel load dynamic measurement device for an aircraft in taxiing state is provided, the device comprising: Measurement area setting module: used to set measurement strips on the airport taxiway and establish a coordinate system based on the measurement strips; Wheel load acquisition module: used to acquire the X coordinate value, wheel load size and passage time of the nose wheel of the aircraft under test as each wheel of the aircraft under test slides through the measurement strip in sequence; and to acquire the X coordinate value, wheel load size and passage time of each row of main wheels of the aircraft under test. Speed ​​acquisition module: used to acquire the aircraft's speed during taxiing through a pre-set speed measuring and camera device; Binary array acquisition module: used to create an X-coordinate-wheel load array of each row of main wheels relative to the nose wheel based on the X-coordinate values ​​of each row of main wheels and nose wheel and the wheel load size; Longitudinal wheelbase acquisition module: used to obtain the longitudinal wheelbase between the nose wheel and the first row of main wheels by the elapsed time between the nose wheel and the first row of main wheels and the speed of the aircraft during taxiing; and to obtain the longitudinal wheelbase between two adjacent rows of main wheels based on the elapsed time between two adjacent rows of main wheels and the speed of the aircraft during taxiing. Y-coordinate acquisition module: used to acquire the Y-coordinate of each row of main wheels relative to the nose wheel based on the longitudinal axis distance between the nose wheel and the first row of main wheel shafts, and the longitudinal axis distance between two adjacent rows of main wheel shafts; Ternary array acquisition module: used to establish a ternary array of X-coordinate-Y-wheel load for each row of main wheels relative to the nose wheel based on the X-coordinate-wheel load array of each row of main wheels relative to the nose wheel and the Y-coordinate of each row of main wheels relative to the nose wheel; Planar matrix diagram construction module: used to build an aircraft wheel load planar matrix diagram based on the ternary array of X-coordinate-Y-wheel load of each row of main wheels relative to the nose wheel; Output module: used to obtain the spatial planar distribution and wheel load of each aircraft wheel based on the aircraft wheel load planar matrix diagram.

[0015] The technical solutions provided by the embodiments of the present invention may include the following beneficial effects: This application involves setting up measurement strips on airport taxiways, establishing a coordinate system based on the measurement strips, and measuring the time it takes for an aircraft to pass through the measurement strips, its wheel load, and its taxiing speed. The longitudinal and lateral wheelbases are calculated using the acquired data, and an aircraft wheel load planar matrix diagram is created. Based on the aircraft wheel load planar matrix diagram, the spatial planar distribution and wheel load of each aircraft wheel are obtained. This application automatically generates a wheel load matrix diagram, meeting the monitoring needs of bridges and pavements. The acquired data is dimensionally complete, requires no stationary aircraft, and allows for real-time measurement during taxiing, without affecting normal airport operations.

[0016] It should be understood that the above general description and the following detailed description are exemplary and explanatory only, and are not intended to limit the invention. Attached Figure Description

[0017] The accompanying drawings, which are incorporated in and form part of this specification, illustrate embodiments consistent with the invention and, together with the description, serve to explain the principles of the invention.

[0018] Figure 1 This is a flowchart illustrating a method for dynamic measurement of wheel loads during aircraft taxiing, according to an exemplary embodiment. Figure 2 This is an elevation view of an aircraft wheel axle arrangement according to another exemplary embodiment; Figure 3 This is a diagram illustrating the relationship between the measurement strips and the aircraft plane, according to another exemplary embodiment. Figure 4 This is a schematic diagram of a measurement plane coordinate system according to another exemplary embodiment; Figure 5 This is a plan view of the measuring wheel axle shown according to another exemplary embodiment; Figure 6 This is a measurement wheel load plane coordinate diagram shown according to another exemplary embodiment; Figure 7 This is a longitudinal axis spacing plan view shown according to another exemplary embodiment; Figure 8 This is a diagram of the aircraft wheel load planar matrix according to another exemplary embodiment; Figure 9This is a schematic diagram of a system for measuring the dynamic load on the wheels of an aircraft in a taxiing state, according to another exemplary embodiment. In the attached diagram: 1-Measurement area setting module, 2-Wheel load acquisition module, 3-Speed ​​acquisition module, 4-Binary array acquisition module, 5-Longitudinal wheelbase acquisition module, 6-Y coordinate acquisition module, 7-Ternary array acquisition module, 8-Planar matrix diagram construction module, 9-Output module. Detailed Implementation

[0019] Exemplary embodiments will now be described in detail, examples of which are illustrated in the accompanying drawings. When the following description relates to the drawings, unless otherwise indicated, the same numerals in different drawings denote the same or similar elements. The embodiments described in the following exemplary embodiments do not represent all embodiments consistent with the present invention. Rather, they are merely examples of apparatuses and methods consistent with some aspects of the invention as detailed in the appended claims.

[0020] Example 1 Figure 1 This is a flowchart illustrating a method for dynamically measuring the wheel load of an aircraft in a taxiing state, according to an exemplary embodiment. Figure 1 As shown, the method includes: S1, Set up a measurement strip on the airport taxiway and establish a coordinate system based on the measurement strip; S2, when each wheel of the aircraft under test slides through the measuring strip in sequence, the X-coordinate value, wheel load size, and passage time of the nose wheel of the aircraft under test are obtained; and the X-coordinate value, wheel load size, and passage time of each row of main wheels of the aircraft under test are obtained. S3 acquires the aircraft's speed during taxiing through a pre-set speed measurement and camera device; S4. Based on the X-coordinate values ​​of each row of main wheels and the nose wheel, as well as the wheel load, establish the X-coordinate-wheel load array of each row of main wheels relative to the nose wheel; S5, obtain the longitudinal wheelbase between the nose wheel and the first row of main wheels by the transit time between the nose wheel and the first row of main wheels and the speed of the aircraft during taxiing; and obtain the longitudinal wheelbase between the two adjacent rows of main wheels by the transit time between the two adjacent rows of main wheels and the speed of the aircraft during taxiing. S6. Obtain the Y coordinate of each row of main wheels relative to the nose wheel based on the longitudinal axis distance between the nose wheel and the first row of main wheel shafts, and the longitudinal axis distance between two adjacent rows of main wheel shafts. S7. Based on the X-coordinate-wheel load array of each row of main wheels relative to the nose wheel and the Y-coordinate of each row of main wheels relative to the nose wheel, establish a ternary array of X-coordinate-Y-wheel load of each row of main wheels relative to the nose wheel. S8. Based on the ternary array of X-coordinate-Y-wheel load of each row of main wheels relative to the nose wheel, establish the aircraft wheel load planar matrix diagram. S9. Obtain the spatial planar distribution and wheel load of each aircraft wheel according to the aircraft wheel load planar matrix diagram; It is understood that this application specifically includes: Measurement preparation: Measurement strip design: Dimensions: The strip width (parallel to the aircraft's taxiing direction) is set based on the actual ground contact area of ​​the wheels, and the elevation layout of the aircraft wheel axles is attached. Figure 2 As shown, the length of the strip is tentatively set at 0.6 meters; the strip length (perpendicular to the aircraft's taxiing direction) can be set according to the width of the airport taxiway, tentatively set at 23 meters. The planar relationship between the strip and the aircraft is shown in the attached figure. Figure 3 As shown.

[0021] Coordinate system: The X-axis is located on the side perpendicular to the aircraft's taxiing direction (positive to the right of the aircraft's taxiing direction), and the Y-axis is located on the side parallel to the aircraft's taxiing direction (positive to the aircraft's taxiing direction). The intersection of the X and Y axes is the origin O of the coordinate system. The measurement plane coordinate system is shown in the attached figure. Figure 4 As shown.

[0022] Measurement module division: The length and width of the measurement strip are divided into several small-sized modules to form a measurement array. Each module is independent and assigned an X-coordinate value. The module size meets the measurement accuracy requirements of the wheel contact area range. The module size in the length direction of the strip is temporarily set at 0.5 meters, and the module size in the width direction of the strip is temporarily set at 0.3 meters.

[0023] Sensor deployment: Force sensors are deployed in each independent module; Camera deployment: Install cameras along the extended length of the measuring strip to perform functions such as measuring aircraft taxiing speed and recording images; Data integration and analysis: Integrate and analyze the data collected by sensors and cameras to obtain wheel load size and wheel distribution, and generate a measurement report; Measurement system activation and deactivation: When the camera detects that an aircraft is about to pass through the measurement area, the measurement system is automatically activated. If no aircraft is detected after a certain period of time, the measurement system is automatically deactivated. Aircraft nose wheel load measurement and pressure point coordinate positioning: After the aircraft nose wheel slides over the measuring strip, the force sensor measures the load size Pb, and obtains the X coordinate value Xb of the nose wheel pressure point based on the position of the pressure module, and records the strip pressure time point tb. Aircraft taxiing speed and taxiing direction measurement: The speed v is measured by a camera to identify the taxiing direction; Wheel load measurement and pressure point coordinate positioning of different axles of the aircraft main landing gear, as shown in the attached document. Figure 5 and appendix Figure 6 As shown: Wheel load measurement and pressure point coordinate positioning of the first row of main wheels of the aircraft (assuming there are i1 wheels laterally): When the first row of main wheels of the aircraft's main landing gear slides over the measuring strip, the force sensor measures the wheel load P1.1~P1.i1 at different wheels on the same axle. Based on the location of the pressure point, the X coordinates of the pressure point are formed. The X coordinates of the pressure points from left to right are X1.1~X1.i1. The time point t1 when the strip is compressed is recorded. Wheel load measurement and pressure point coordinate positioning of the second row of main wheels of the aircraft (assuming there are i2 wheels on this axle): When the second row of main wheels of the aircraft's main landing gear slides over the measuring strip, the force sensor measures the wheel load P2.1~P2.i2 at different wheels on the same axle. Based on the location of the pressure point, the X coordinates of the pressure point are formed. The X coordinates of the pressure points from left to right are X2.1~X2.i2. The time point t2 when the strip is compressed is recorded. Wheel load measurement and pressure point coordinate positioning of the third row of main wheels of the aircraft (assuming there are i3 wheels on this axle): When the third row of main wheels of the aircraft's main landing gear slides over the measuring strip, the force sensor measures the wheel load P3.1~P3.i3 at different wheels on the same axle. Based on the location of the pressure point, the X coordinates of the pressure point are formed. The X coordinates of the pressure points from left to right are X3.1~X3.i3. The pressure time point t3 of the strip is recorded. ... Wheel load measurement and pressure point coordinate location of the m-th row of main wheels of an aircraft (assuming there are in wheels on this axle): When the m-th row of main landing gear wheels of the aircraft slides over the measuring strip, the force sensor measures the wheel load Pm.1~Pm.in at different wheels on the same axle. Based on the location of the pressure point, the X coordinate of the pressure point is formed. The X coordinates of the pressure points from left to right are Xm.1~Xm.in. The time point tm of the strip being compressed is recorded. Data Analysis: Construct an array of pressure points (X coordinate, wheel load): One array for the nasal rim: (Xb, Pb); The i1 arrays of the first row of main wheels are: (X1.1, P1.1), (X1.2, P1.2), (X1.3, P1.3), ..., (X1.i1, P1.i1). The i2 arrays of the second row of main wheels are: (X2.1, P2.1), (X2.2, P2.2), (X2.3, P2.3), ..., (X2.i2, P2.i2). The i3 arrays of the third row of main wheels are: (X3.1, P3.1), (X3.2, P3.2), (X3.3, P3.3), ..., (X3.i3, P3.i3). ... The in-th array of the m-th main wheel: (Xm.1, Pm.1), (Xm.2, Pm.2), (Xm.3, Pm.3), ..., (Xm.in, Pm.in); Construct an array of (X coordinate, wheel load) for each pressure point relative to the nose wheel pressure point: Nasal rim array: (0, Pb); The i1 arrays of the first row of main wheels are: (X1.1 -Xb, P1.1), (X1.2 -Xb, P1.2), (X1.3 -Xb, P1.3), ..., (X1.i1 -Xb, P1.i1). The i2 arrays of the second row of main wheels are: (X2.1-Xb, P2.1), (X2.2-Xb, P2.2), (X2.3-Xb, P2.3), ..., (X2.i2-Xb, P2.i2); The i3 arrays of the third row of main wheels are: (X3.1-Xb, P3.1), (X3.2-Xb, P3.2), (X3.3-Xb, P3.3), ..., (X3.i3-Xb, P3.i3). ... The in-th array of the m-th row of main wheels: (Xm.1-Xb, Pm.1), (Xm.2-Xb, Pm.2), (Xm.3-Xb, Pm.3), ..., (Xm.in-Xb, Pm.in); Longitudinal wheelbase calculation, as shown in the appendix. Figure 7 As shown: The distance L1 between the nose landing gear (nose wheel) and the first row of main wheel axles is L1 = (t1 - tb). v; The distance between the first row of main wheel axles and the second row of main wheel axles is L2 = (t2 - t1). v; The distance between the second row of main wheel axles and the third row of main wheel axles is L3 = (t3 - t2). v; ... The distance Lm between the (m-1)th row main wheel axle and the mth row main wheel axle is Lm = (tm - t(m-1)). v; Construct the Y-coordinate of each pressure point relative to the nose roller pressure point: The Y-coordinate of the nose helix is ​​Yb=0; The Y-coordinate of the first row of main wheel axles: Y1=L1; The Y-coordinate of the second row of main wheel axles: Y2 = L1 + L2; The Y-coordinate of the third row of main wheel axles: Y3 = L1 + L2 + L3; ... The Y-coordinate of the m-th row of main wheel axles is: Ym = L1 + L2 + L3 + … + Lm; Construct an array of (X coordinate, Y coordinate, wheel load) for each pressure point relative to the nose wheel pressure point: Nasal rim array: (0, 0, Pb) The i1 arrays of the first row of main wheel axles are: (X1.1 -Xb, Y1, P1.1), (X1.2 -Xb, Y1, P1.2), (X1.3 -Xb, Y1, P1.3), ..., (X1.i1 -Xb, Y1, P1.i1). The i2 arrays of the second row of main wheel axles are: (X2.1-Xb, Y2, P2.1), (X2.2-Xb, Y2, P2.2), (X2.3-Xb, Y2, P2.3), ..., (X2.i2-Xb, Y2, P2.i2). The i3 arrays of the third row of main wheel axles are: (X3.1-Xb, Y3, P3.1), (X3.2-Xb, Y3, P3.2), (X3.3-Xb, Y3, P3.3), ..., (X3.i3-Xb, Y3, P3.i3). ... The in arrays of the m-th row of main wheel axles: (Xm.1-Xb, Ym, Pm.1), (Xm.2-Xb, Ym, Pm.2), (Xm.3-Xb, Ym, Pm.3), ..., (Xm.in-Xb, Ym, Pm.in); Generate the aircraft wheel load planar matrix diagram, as shown in the attached diagram. Figure 8 As shown: The above ternary array can generate a planar matrix diagram composed of the spatial planar distribution of the aircraft landing gear wheels and the wheel load values. The origin of the matrix diagram is located at the nose wheel pressure point. Positioning the aircraft wheel load range: The taxiing wheel tracks of the entire aircraft can be located based on the X coordinate values ​​of each wheel; Determine the total weight of the aircraft: The total weight of the aircraft, G, is given by: G = Pb + P1.1 + P1.2 + ... + P1.i1 + P2.1 + P2.2 + ... + P2.i2 + P3.1 + P3.2 + ... + P3.i3 + Pm.1 + Pm.2 + ... + Pm.in; Determine the lateral wheelbase of each main wheel: Nose wheel: wheelbase is 0; First row of main wheels: From left to right, the wheel spacing between adjacent wheels is b1.1, b1.2, ..., b1.i1-1, where... b1.1 = X1.2 - X1.1 b1.2 = X1,3 - X1,2 … b1.i1-1=X1.i1 - X1.i1-1 Second row of main wheels: From left to right, the wheel spacing between adjacent wheels is b2.1, b2.2, ..., b2.i2-1, where... b2.1 = X2.2 - X2.1 b².2 = X².3 - X².2 … b2.i2-1=X2.i2 - X2.i2-1 The m-th row of main wheels: from left to right, the wheel distances between adjacent wheels are bm.1, bm.2, ..., bm.in-1, where, bm.1 = Xm.2 - Xm.1 bm.2 = Xm.3 - Xm.2 … bm.in-1 = Xm.in – Xm.in-1 Image generation: When each axis of the aircraft passes through the measurement area, the camera takes pictures of the measurement area and records the measurement area while the measurement system is active; Model identification: An aircraft model database is pre-built, which stores data on wheel load distribution, wheel set arrangement, wheel track, and wheelbase for each aircraft model. The generated aircraft wheel load planar matrix is ​​then compared with the aircraft model data in the database to identify the aircraft model passing through the measurement area.

[0024] Example 2 Figure 9 This is a schematic diagram of a system for measuring the dynamic load on the wheels of an aircraft during taxiing, according to another exemplary embodiment. The device includes: Measurement area setting module 1: used to set measurement strips on the airport taxiway and establish a coordinate system based on the measurement strips; Wheel load acquisition module 2: used to acquire the X coordinate value, wheel load size and passage time of the nose wheel of the aircraft under test when each wheel of the aircraft under test slides through the measurement strip in sequence; and to acquire the X coordinate value, wheel load size and passage time of each row of main wheels of the aircraft under test. Speed ​​acquisition module 3: used to acquire the aircraft's speed during taxiing through a pre-set speed measuring and camera device; Binary array acquisition module 4: used to establish an X-coordinate-wheel load array of each row of main wheels relative to the nose wheel based on the X-coordinate values ​​of each row of main wheels and nose wheel and the wheel load size; Longitudinal wheelbase acquisition module 5: used to obtain the longitudinal wheelbase between the nose wheel and the first row of main wheels by the elapsed time between the nose wheel and the first row of main wheels and the speed of the aircraft during taxiing; and to obtain the longitudinal wheelbase between two adjacent rows of main wheels based on the elapsed time between two adjacent rows of main wheels and the speed of the aircraft during taxiing. Y-coordinate acquisition module 6: used to acquire the Y-coordinate of each row of main wheels relative to the nose wheel based on the longitudinal axis distance between the nose wheel and the first row of main wheel shafts, and the longitudinal axis distance between two adjacent rows of main wheel shafts; Ternary array acquisition module 7: is used to establish a ternary array of X-coordinate-Y-wheel load of each row of main wheels relative to the nose wheel based on the X-coordinate-wheel load array of each row of main wheels relative to the nose wheel and the Y-coordinate of each row of main wheels relative to the nose wheel; Planar matrix diagram construction module 8: used to establish an aircraft wheel load planar matrix diagram based on the ternary array of X-coordinate-Y-wheel load of each row of main wheels relative to the nose wheel; Output module 9: used to obtain the spatial planar distribution and wheel load of each aircraft wheel based on the aircraft wheel load planar matrix diagram.

[0025] It is understood that the same or similar parts in the above embodiments can be referred to each other, and the contents not described in detail in some embodiments can be referred to the same or similar contents in other embodiments.

[0026] It should be noted that in the description of this invention, the terms "first," "second," etc., are used for descriptive purposes only and should not be construed as indicating or implying relative importance. Furthermore, in the description of this invention, unless otherwise stated, "a plurality of" means at least two.

[0027] Any process or method description in the flowchart or otherwise herein can be understood as representing a module, segment, or portion of code comprising one or more executable instructions for implementing a particular logical function or process, and the scope of the preferred embodiments of the invention includes additional implementations in which functions may be performed not in the order shown or discussed, including substantially simultaneously or in reverse order depending on the functions involved, as will be understood by those skilled in the art to which embodiments of the invention pertain.

[0028] It should be understood that various parts of the present invention can be implemented in hardware, software, firmware, or a combination thereof. In the above embodiments, multiple steps or methods can be implemented in software or firmware stored in memory and executed by a suitable instruction execution system. For example, if implemented in hardware, as in another embodiment, it can be implemented using any one or a combination of the following techniques known in the art: discrete logic circuits having logic gates for implementing logical functions on data signals, application-specific integrated circuits (ASICs) having suitable combinational logic gates, programmable gate arrays (PGAs), field-programmable gate arrays (FPGAs), etc.

[0029] Those skilled in the art will understand that all or part of the steps of the methods in the above embodiments can be implemented by a program instructing related hardware. The program can be stored in a computer-readable storage medium, and when executed, the program includes one or a combination of the steps of the method embodiments.

[0030] Furthermore, the functional units in the various embodiments of the present invention can be integrated into a processing module, or each unit can exist physically separately, or two or more units can be integrated into a module. The integrated module can be implemented in hardware or as a software functional module. If the integrated module is implemented as a software functional module and sold or used as an independent product, it can also be stored in a computer-readable storage medium.

[0031] The storage media mentioned above can be read-only memory, disk, or optical disk, etc.

[0032] In the description of this specification, references to terms such as "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of the invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples.

[0033] Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention. Those skilled in the art can make changes, modifications, substitutions and variations to the above embodiments within the scope of the present invention.

Claims

1. A method for dynamically measuring wheel loads of an aircraft during taxiing, characterized in that, The method includes: Measurement strips are set up on the airport taxiway, and a coordinate system is established based on the measurement strips; As each wheel of the aircraft under test slides sequentially across the measurement strip, the X-coordinate value, wheel load, and passage time of the nose wheel of the aircraft under test are obtained; and the X-coordinate value, wheel load, and passage time of each row of main wheels of the aircraft under test are also obtained. The aircraft's speed during taxiing is obtained through pre-set speed measurement and camera devices; Based on the X-coordinate values ​​of each row of main wheels and the nose wheel, as well as the wheel load, establish an X-coordinate-wheel load array for each row of main wheels relative to the nose wheel; The longitudinal wheelbase between the nose wheel and the first row of main wheels is obtained by the transit time between the nose wheel and the first row of main wheels, and the speed of the aircraft during taxiing; and the longitudinal wheelbase between two adjacent rows of main wheels is obtained by the transit time between two adjacent rows of main wheels and the speed of the aircraft during taxiing. The Y coordinate of each row of main wheels relative to the nose wheel is obtained based on the longitudinal axis distance between the nose wheel and the first row of main wheels, and the longitudinal axis distance between two adjacent rows of main wheels; Based on the X-coordinate-wheel load array of each row of main wheels relative to the nose wheel and the Y-coordinate of each row of main wheels relative to the nose wheel, establish a ternary array of X-coordinate-Y-wheel load for each row of main wheels relative to the nose wheel; Based on the ternary array of X-Y coordinates and wheel load of each row of main wheels relative to the nose wheel, an aircraft wheel load planar matrix diagram is established; The spatial planar distribution and wheel load of each aircraft wheel are obtained from the aircraft wheel load planar matrix diagram.

2. The method according to claim 1, characterized in that, The step of setting up measurement strips on the airport taxiway and establishing a coordinate system based on the measurement strips includes: A rectangular measuring strip is set up on the airport taxiway. The length side of the measuring strip is perpendicular to the aircraft taxiing direction and is set as the X-axis; the width side of the measuring strip is parallel to the aircraft taxiing direction and is set as the Y-axis. The aircraft taxiing direction is positive, and the intersection of the X-axis and Y-axis is the origin of the coordinate system. A planar coordinate system is established with the intersection of the X-axis and Y-axis as the origin. The measurement strip is divided into multiple independent measurement modules along the X and Y axes to form a measurement array. Each independent measurement module is assigned an X-coordinate value, and a force sensor is set in each independent measurement module. A speed measuring and camera device is installed on the extension line of the measuring strip.

3. The method according to claim 2, characterized in that, Also includes: The taxiing wheel tracks of the aircraft during taxiing are located based on the X coordinates of each of the aircraft's wheels.

4. The method according to claim 3, characterized in that, Also includes: The total weight of the aircraft is obtained by summing the wheel loads of each wheel.

5. The method according to claim 4, characterized in that, Also includes: A model database is pre-built, which stores data on wheel load distribution, wheel set arrangement, wheel track and wheelbase for each model. The aircraft model is identified by comparing and matching the aircraft wheel load plane matrix diagram with the aircraft model database.

6. The method according to claim 5, characterized in that, The longitudinal wheelbase is calculated as follows: The longitudinal wheelbase between the nose wheel and the first row of main wheels is: L1=(t1-tb)×v In the formula, t1 represents the time it takes for the first row of main wheel axles to pass through the measuring strip, tb represents the time it takes for the nose wheel axle to pass through the measuring strip, and v represents the speed of the aircraft during taxiing. The longitudinal wheelbase between the (m-1)th row of main wheels and the mth row of main wheels is: Lm=(tm-t (m-1))×v In the formula, tm represents the time it takes for the m-th row of main wheel axles to pass through the measuring strip, and t(m-1) represents the time it takes for the (m-1)-th row of main wheel axles to pass through the measuring strip.

7. The method according to claim 6, characterized in that, Also includes: Based on the X-coordinate values ​​of the adjacent wheels in each row of the aircraft wheel load plane matrix diagram, the lateral wheel spacing of the adjacent wheels in each row of the main wheels is obtained.

8. The method according to claim 7, characterized in that, Also includes: The speed measuring and camera device detects when an aircraft is about to enter the measurement area and automatically starts the measurement; if no aircraft enters within a preset time after the measurement is started, the measurement is automatically stopped.

9. The method according to claim 8, characterized in that, The width of the measuring strip is set according to the actual ground contact area of ​​the wheel; The length of the measuring strip is set according to the width of the airport taxiway pavement.

10. A dynamic measurement device for wheel load on an aircraft during taxiing, characterized in that, The device includes: Measurement area setting module: used to set measurement strips on the airport taxiway and establish a coordinate system based on the measurement strips; Wheel load acquisition module: used to acquire the X coordinate value, wheel load size and passage time of the nose wheel of the aircraft under test as each wheel of the aircraft under test slides through the measurement strip in sequence; and to acquire the X coordinate value, wheel load size and passage time of each row of main wheels of the aircraft under test. Speed ​​acquisition module: used to acquire the aircraft's speed during taxiing through a pre-set speed measuring and camera device; Binary array acquisition module: used to create an X-coordinate-wheel load array of each row of main wheels relative to the nose wheel based on the X-coordinate values ​​of each row of main wheels and nose wheel and the wheel load size; Longitudinal wheelbase acquisition module: used to obtain the longitudinal wheelbase between the nose wheel and the first row of main wheels by the elapsed time between the nose wheel and the first row of main wheels and the speed of the aircraft during taxiing; and to obtain the longitudinal wheelbase between two adjacent rows of main wheels based on the elapsed time between two adjacent rows of main wheels and the speed of the aircraft during taxiing. Y-coordinate acquisition module: used to acquire the Y-coordinate of each row of main wheels relative to the nose wheel based on the longitudinal axis distance between the nose wheel and the first row of main wheels, and the longitudinal axis distance between two adjacent rows of main wheels; Ternary array acquisition module: used to establish a ternary array of X-coordinate-Y-wheel load for each row of main wheels relative to the nose wheel based on the X-coordinate-wheel load array of each row of main wheels relative to the nose wheel and the Y-coordinate of each row of main wheels relative to the nose wheel; Planar matrix diagram construction module: used to build an aircraft wheel load planar matrix diagram based on the ternary array of X-coordinate-Y-wheel load of each row of main wheels relative to the nose wheel; Output module: used to obtain the spatial planar distribution and wheel load of each aircraft wheel based on the aircraft wheel load planar matrix diagram.

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