Wing deflection deformation measurement method and system, storage medium and electronic equipment

Abstract

The invention relates to the field of aircraft testing, in particular to a wing deflection deformation measuring method and system, a storage medium and electronic equipment. The method comprises the following steps: acquiring wing detection data of a to-be-measured wing, wherein the wing detection data comprises a target file containing a physical quantity acceleration value; obtaining an effective acceleration value based on the wing detection data; according to the effective acceleration value, calculating deformation data of the to-be-measured wing, wherein the deformation data comprises deflection deformation and torsion deformation angles generated by the to-be-measured wing relative to the geodetic coordinate system; and according to the deformation data, a deflection deformation measurement result of the to-be-measured wing is determined, and the deflection deformation measurement result comprises a deformation angle and a deflection deformation distance corresponding to a target measurement point on the to-be-measured wing. Through the method, the deformation condition of the wing can be accurately measured, so that powerful technical support is provided for improving the flight safety performance and optimizing the design and maintenance of the wing.

Description

Technical Field

[0001] The present disclosure relates to the field of aircraft testing, and particularly to a method and system for measuring wing deflection deformation, a storage medium, and an electronic device. Background Art

[0002] In recent years, various countries have competed to focus their research on aircraft technologies that operate at ultra-high altitudes, have long endurance, and are powered by renewable energy. The cruising capabilities of these aircraft in the near-space domain are particularly remarkable, and they are widely used in multiple key fields such as long-term reconnaissance and surveillance, detailed environmental monitoring, and high-efficiency communication relay. To maximize energy utilization and achieve ultra-long endurance, these aircraft are carefully designed to have characteristics such as a large aspect ratio, a flexible structure, and extreme lightweight.

[0003] However, precisely these unique design advantages also make such aircraft more prone to wing deformation and larger deformation amounts when facing factors such as gravity, severe vibrations during flight, and complex and variable aerodynamic pressures, compared to traditional rigid-structure aircraft. Summary of the Invention

[0004] The main objective of the present disclosure is to provide a method and system for measuring wing deflection deformation, a storage medium, and an electronic device, aiming to solve the technical problem of limited measurement of wing deflection deformation in flexible-structure aircraft in the prior art.

[0005] To achieve the above objective, the present disclosure proposes a method for measuring wing deflection deformation, including:

[0006] Obtain wing detection data of the wing to be measured, where the wing detection data includes a target file containing a physical quantity acceleration value;

[0007] Based on the wing detection data, obtain an effective acceleration value;

[0008] According to the effective acceleration value, calculate the deformation data of the wing to be measured, where the deformation data includes the deflection deformation and the torsional deformation angle generated by the wing to be measured relative to the earth coordinate system;

[0009] According to the deformation data, determine the measurement result of the wing deflection deformation to be measured, where the measurement result of the wing deflection deformation includes the deformation angle and the deflection deformation distance corresponding to the target measurement point on the wing to be measured.

[0010] Optionally, the step of determining the measurement result of the wing deflection deformation to be measured according to the deformation data includes:

[0011] Obtain the digital mock-up design drawing of the wing to be measured;

[0012] Determine the wing parameters of the wing to be measured according to the digital-analog design drawing;

[0013] Calculate the spanwise and chordwise deformation data corresponding to the target measurement point according to the wing parameters and the deformation data;

[0014] Input the spanwise and chordwise deformation data into the trained deformation prediction model to obtain the deformation prediction result output by the deformation prediction model;

[0015] Determine the deflection deformation measurement result according to the deformation prediction result.

[0016] Optionally, the obtaining of the wing detection data of the wing to be measured includes:

[0017] Obtain the original acceleration voltage value data of the wing to be measured at the target measurement point;

[0018] Obtain the wire calibration formula corresponding to the original acceleration voltage value data;

[0019] Based on the wire calibration formula, convert the original acceleration voltage value data into the target file containing the physical quantity acceleration value;

[0020] Determine the wing detection data according to the target file containing the physical quantity acceleration value.

[0021] Optionally, the obtaining of the effective acceleration value based on the wing detection data includes:

[0022] Perform low-pass filtering on the target file containing the physical quantity acceleration value to filter out the vibration interference data in the target file containing the physical quantity acceleration value, and obtain the target file after low-pass filtering;

[0023] Determine the effective acceleration value based on the target file after low-pass filtering.

[0024] Optionally, the calculating of the deformation data of the wing to be measured according to the effective acceleration value includes:

[0025] According to the effective acceleration value, determine the first acceleration value generated by the X-axis of the measurement coordinate system of the wing to be measured, the second acceleration value generated by the Y-axis of the measurement coordinate system, and the third acceleration value generated by the Z-axis of the measurement coordinate system;

[0026] Obtain the principle conversion formula between acceleration and tilt angle;

[0027] Calculate the tilt angle data of the wing to be measured relative to the geodetic coordinate system according to the first acceleration value, the second acceleration value, the third acceleration value, and the principle conversion formula;

[0028] Determine the deformation data according to the tilt angle data and the position of the target measurement point.

[0029] Optionally, the calculating the tilt angle data generated by the wing to be measured relative to the geodetic coordinate system according to the first acceleration value, the second acceleration value, the third acceleration value, and the principle conversion formula includes:

[0030] Based on the following first formula, calculate the first angle between the XOY plane of the measurement coordinate system after tilting along the XOZ plane of the measurement coordinate system and the XOY plane in the geodetic coordinate system:

[0031]

[0032] where θ is the first angle, A x is the first acceleration value, A y is the second acceleration value, A z is the third acceleration value;

[0033] Based on the following second formula, calculate the second angle between the XOY plane of the measurement coordinate system after tilting along the YOZ plane of the measurement coordinate system and the XOY plane in the geodetic coordinate system:

[0034]

[0035] where, is the second angle;

[0036] Based on the following third formula, calculate the third angle, where the third angle is the angle between the Z axis of the measurement coordinate system and the Z axis of the geodetic coordinate system after the XOY plane of the measurement coordinate system tilts along the XOZ plane and the YOZ plane simultaneously:

[0037]

[0038] where φ is the third angle.

[0039] Optionally, the deformation prediction model is a cubic spline interpolation model.

[0040] In addition, to achieve the above object, the present disclosure also provides a wing deflection deformation measurement system, including:

[0041] A data acquisition device, disposed on the target measurement point of the wing to be measured, for acquiring acceleration voltage data on the accelerometer sensor of the wing to be measured;

[0042] A data recording device, which is arranged in the aircraft equipment cabin corresponding to the wing to be measured, and is used for recording the hexadecimal code value corresponding to the acceleration voltage data;

[0043] A separation and extension device, one end of which is connected to the data acquisition device and the other end is connected to the data recording device, and is used for connecting the data acquisition device and the data recording device together;

[0044] A wing deflection deformation measurement device, which is used for determining the deflection deformation measurement result of the wing to be measured according to the acceleration voltage data acquired by the data acquisition device.

[0045] Optionally, the wing deflection deformation measurement device includes:

[0046] A first acquisition module, which is used for acquiring wing detection data of the wing to be measured, and the wing detection data includes a target file containing a physical quantity acceleration value;

[0047] A second acquisition module, which is used for acquiring an effective acceleration value based on the wing detection data;

[0048] A calculation module, which is used for calculating the deformation data of the wing to be measured according to the effective acceleration value, and the deformation data includes the deflection deformation and the torsion deformation angle generated by the wing to be measured relative to the earth coordinate system;

[0049] A determination module, which is used for determining the deflection deformation measurement result of the wing to be measured according to the deformation data, and the deflection deformation measurement result includes the deformation angle and the deflection deformation distance corresponding to the target measurement point on the wing to be measured.

[0050] In addition, to achieve the above object, the present disclosure also provides a computer-readable storage medium, on which a computer program is stored, and a processor executes the computer program to implement the above method.

[0051] In addition, to achieve the above object, the present disclosure also provides an electronic device, which includes a memory and a processor, a computer program is stored in the memory, and the processor executes the computer program to implement the above method.

[0052] In addition, to achieve the above object, the present disclosure also provides a computer program product, which implements the above method when being run by a processor.

[0053] The wing deflection deformation measurement method, system, storage medium and electronic device proposed in the embodiments of the present disclosure first directly obtain the physical quantity acceleration value of the wing to be measured as the wing detection data, calculate the effective acceleration value according to the wing detection data, then calculate the deformation data according to the calculated effective acceleration value, and finally determine the wing deflection deformation measurement result of the wing to be measured according to the deformation data. In this way, it can accurately reflect the dynamic changes of the wing during flight, help to timely detect and accurately measure the deformation of the wing, and thus provide strong technical support for improving flight safety performance, optimizing wing design and maintenance. BRIEF DESCRIPTION OF THE DRAWINGS

[0054] In order to more clearly illustrate the technical solutions in the embodiments of the present disclosure or the prior art, the following will briefly introduce the drawings required for use in the description of the embodiments or the prior art. Obviously, the following drawings are only some embodiments of the present disclosure. For those of ordinary skill in the art, without creative efforts, other drawings can also be obtained according to the structures shown in these drawings.

[0055] Figure 1 It is a schematic diagram of the device structure of the hardware operating environment related to the solution of the embodiments of the present disclosure;

[0056] Figure 2 It is a structural block diagram of a wing deflection deformation measurement system related to the solution of the embodiments of the present disclosure;

[0057] Figure 3 It is a schematic diagram of the distribution of target test points related to the solution of the embodiments of the present disclosure;

[0058] Figure 4 It is a schematic flowchart of a wing deflection deformation measurement method related to the solution of the embodiments of the present disclosure;

[0059] Figure 5 It is a schematic diagram of deformation related to the solution of the embodiments of the present disclosure;

[0060] Figure 6 It is a structural block diagram of a wing deflection deformation measurement device related to the solution of the embodiments of the present disclosure.

[0061] The realization, functional features and advantages of the purpose of the present disclosure will be further described with reference to the embodiments and the drawings. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0062] The following will clearly and completely describe the technical solutions in the embodiments of the present disclosure with reference to the accompanying drawings in the embodiments of the present disclosure. Obviously, the described embodiments are only a part of the embodiments of the present disclosure, rather than all the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments in the present disclosure without making creative efforts belong to the scope of protection of the present disclosure.

[0063] Referring to Figure 1 , Figure 1 is a schematic structural diagram of a device for the hardware operating environment related to the solution of the embodiment of the present disclosure.

[0064] Generally, the device includes: at least one processor 301, a memory 302, and a wing deflection deformation measurement program stored on the memory 302 and executable on the processor 301. The wing deflection deformation measurement program is configured to implement the steps of the wing deflection deformation measurement method as described above.

[0065] The processor 301 may include one or more processing cores, such as a 4-core processor, an 8-core processor, etc. The processor 301 may be implemented in at least one hardware form of DSP (Digital Signal Processing), FPGA (Field-Programmable Gate Array), or PLA (Programmable Logic Array). The processor 301 may also include a main processor and a coprocessor. The main processor is a processor for processing data in the wake state, also known as the CPU (Central Processing Unit); the coprocessor is a low-power processor for processing data in the standby state. In some embodiments, the processor 301 may be integrated with a GPU (Graphics Processing Unit), and the GPU is responsible for rendering and drawing the content to be displayed on the display screen. The processor 301 may also include an AI (Artificial Intelligence) processor, which is used to process operations related to the wing deflection deformation measurement method, so that the wing deflection deformation measurement method model can autonomously train and learn to improve efficiency and accuracy.

[0066] The memory 302 may include one or more storage media, which may be non-transitory. The memory 302 may further include high-speed random access memory, as well as non-volatile memory, such as one or more magnetic disk storage devices and flash storage devices. In some embodiments, the non-transitory storage media in the memory 302 is used to store at least one instruction for being executed by the processor 301 to implement the wing deflection deformation measurement method provided in the method embodiments of the present disclosure.

[0067] In some embodiments, the terminal may further optionally include: a communication interface 303 and at least one peripheral device. The processor 301, the memory 302, and the communication interface 303 may be connected through a bus or signal lines. Each peripheral device may be connected to the communication interface 303 through a bus, signal lines, or a circuit board. Specifically, the peripheral device includes at least one of a radio frequency circuit 304, a display screen 305, and a power supply 306.

[0068] The communication interface 303 can be used to connect at least one peripheral device related to I / O (Input / Output) to the processor 301 and the memory 302. In some embodiments, the processor 301, the memory 302, and the communication interface 303 are integrated on the same chip or circuit board; in some other embodiments, any one or two of the processor 301, the memory 302, and the communication interface 303 can be implemented on a separate chip or circuit board, and the present embodiment does not limit this.

[0069] The radio frequency circuit 304 is used to receive and transmit RF (Radio Frequency) signals, also known as electromagnetic signals. The radio frequency circuit 304 communicates with a communication network and other communication devices through electromagnetic signals. The radio frequency circuit 304 converts an electrical signal into an electromagnetic signal for transmission, or converts the received electromagnetic signal into an electrical signal. Optionally, the radio frequency circuit 304 includes: an antenna system, an RF transceiver, one or more amplifiers, a tuner, an oscillator, a digital signal processor, a codec chipset, a subscriber identity module card, and so on. The radio frequency circuit 304 can communicate with other terminals through at least one wireless communication protocol. The wireless communication protocol includes but is not limited to: a metropolitan area network, each generation of mobile communication networks (2G, 3G, 4G, and 5G), a wireless local area network, and / or a WiFi (Wireless Fidelity) network. In some embodiments, the radio frequency circuit 304 may further include a circuit related to NFC (Near Field Communication), and the present disclosure does not limit this.

[0070] The display screen 305 is used to display the UI (User Interface). The UI may include graphics, text, icons, videos, and any combination thereof. When the display screen 305 is a touch display screen, the display screen 305 also has the ability to collect touch signals on or above the surface of the display screen 305. The touch signals can be input as control signals to the processor 301 for processing. At this time, the display screen 305 can also be used to provide virtual buttons and / or virtual keyboards, also known as soft buttons and / or soft keyboards. In some embodiments, the display screen 305 can be one, the front panel of the electronic device; in other embodiments, the display screen 305 can be at least two, respectively arranged on different surfaces of the electronic device or in a folding design; in still other embodiments, the display screen 305 can be a flexible display screen, arranged on the curved surface or folding surface of the electronic device. Even, the display screen 305 can be set to an irregular non-rectangular shape, that is, a special-shaped screen. The display screen 305 can be prepared from materials such as LCD (Liquid Crystal Display) and OLED (Organic Light-Emitting Diode).

[0071] The power supply 306 is used to supply power to each component in the electronic device. The power supply 306 can be alternating current, direct current, a disposable battery, or a rechargeable battery. When the power supply 306 includes a rechargeable battery, the rechargeable battery can support wired charging or wireless charging. The rechargeable battery can also be used to support fast charging technology. Those skilled in the art can understand that Figure 1 the structure shown in does not constitute a limitation on the device, and may include more or fewer components than shown in the figure, or combine certain components, or have different component arrangements.

[0072] In addition, the embodiments of the present disclosure also propose a storage medium, on which a wing deflection deformation measurement program is stored. When the wing deflection deformation measurement program is executed by a processor, the steps of the wing deflection deformation measurement method as described above are implemented. Therefore, it will not be elaborated here. In addition, the description of the beneficial effects of using the same method will not be elaborated either. For the technical details not disclosed in the storage medium embodiments of the present disclosure, please refer to the description of the method embodiments of the present disclosure. By way of example, the program instructions can be deployed to be executed on one device, or on multiple devices located at one location, or on multiple devices distributed at multiple locations and interconnected by a communication network.

[0073] Those of ordinary skill in the art can understand that all or part of the processes of implementing the methods in the above embodiments can be completed by instructing relevant hardware through a computer program. The above program can be stored in a storage medium. When the program is executed, it can include the processes of the embodiments of the above methods. Among them, the above storage medium can be a magnetic disk, an optical disk, a read-only memory (ROM), a random access memory (RAM), or the like.

[0074] In related technologies, traditional rigid wing deflection measurement methods widely rely on video recording and image processing technologies, or monitor by pasting strain gauges on the wing surface, arranging fiber optic sensor networks, and using laser rangefinders and other means.

[0075] However, these methods have shown obvious limitations in practice: Video and image measurement technologies are limited by the accuracy and field of view of the shooting equipment, and it is difficult to comprehensively capture subtle deformations in a large range; the application of strain gauges and fiber optic sensors may involve complex wiring installation processes, which not only increase the system weight and complexity, but also face problems such as inflexible adjustment of fixed points and vulnerability of fiber optic materials; laser ranging technology is extremely vulnerable to environmental obstacle interference, resulting in increased measurement errors.

[0076] As for other common deflection measurement methods, such as monitoring technologies commonly used for static structures such as bridges or helicopter rotors, since they do not fully consider the unique dynamic characteristics and environmental conditions of ultra-long aspect ratio flexible wings during flight, they are not suitable for the deflection measurement of such wings.

[0077] In view of this, aiming at the technical problem of measuring the deflection deformation of ultra-long aspect ratio flexible wings, the present disclosure proposes a wing deflection deformation measurement method, system, storage medium, and electronic device. This method not only has the advantages of simple modification and flexible adjustment of the installation position, but also realizes distributed data acquisition, effectively reducing the overall system weight, reducing the number of measurement points, and at the same time, the supporting solution algorithm is simple and efficient. These characteristics together constitute a key technical breakthrough for accurately and reliably measuring the deflection deformation of ultra-long aspect ratio flexible wings.

[0078] Figure 2 It is a structural block diagram of a wing deflection deformation measurement system according to an embodiment of the present disclosure. The deflection deformation measurement system includes:

[0079] A data acquisition device, which is arranged at the target measurement point of the wing to be measured, and is used to collect the acceleration voltage data on the accelerometer sensor of the wing to be measured;

[0080] A data recording device is arranged in the aircraft equipment compartment corresponding to the wing to be measured, and is used to record the hexadecimal code value corresponding to the acceleration voltage data;

[0081] A separation and extension device, with one end connected to the data acquisition device and the other end connected to the data recording device, is used to connect the data acquisition device and the data recording device together;

[0082] A wing deflection deformation measuring device is used to determine the deflection deformation measurement result of the wing to be measured according to the acceleration voltage data collected by the data acquisition device.

[0083] Exemplarily, the data acquisition device can be arranged at the target measurement point of the wing to be measured. Its length * width * height is 21mm * 18mm * 3mm, and the weight is 1g. It has the characteristics of being ultra-light and ultra-thin, and can be fixed specifically with silicone. The data acquisition device is mainly designed by a triaxial MEMS accelerometer sensor, and the interface is a push-type FPC interface. It is mainly used to collect the acceleration voltage values in the X, Y, and Z directions of the MEMS accelerometer to obtain acceleration voltage data. The data recording device can be arranged in the aircraft equipment compartment corresponding to the wing to be measured. An FPC conversion interface is added to the data recording device. Its length * width * height is 20mm * 18mm * 3mm, and the weight is 1g.

[0084] The data acquisition device and the data recording device can be connected by an ultra-light flexible PFC cable. In the present disclosure, the FPC cable can be designed as a single-layer board with 8 internal electrical traces. Its length * width * height can be 1000mm * 7mm * 12.5um, and the weight is 1.54g. The weight is much lighter than that of 8 cables with a 28# wire gauge (AWG 28). The electrical connection is more stable and reliable compared to optical fibers. The connection with the FPC interface is quick to disassemble and can be completed by pressing.

[0085] Exemplarily, since the connection of the ultra-long wingspan flexible cable may be too long, a separation and extension device is arranged between the data acquisition device and the data recording device. One end of the separation and extension device is connected to the FPC interface of the data acquisition device, and the other end is connected to the FPC interface of the data recording device, which is used to connect the data acquisition device and the data recording device together. The length * width * height of the separation and extension device is 20mm * 15mm * 3mm, and the weight is 0.9g.

[0086] In addition, a switch controller of the data recording device and a data maintenance port can be installed at the portable hatch of the aircraft. The switch controller is used to control the voltage input and recording of the entire system, and the data maintenance port is used to record data, download data, and obtain data.

[0087] Exemplarily, Figure 3 This is a schematic diagram of the distribution of target test points related to the solution of the embodiment of the present disclosure, asFigure 3 As shown, multiple target test points can be set on the wing to be measured, and the position and arrangement of each target test point can be set and adjusted according to the actual situation. The specific position and setting method of the target test point are not limited in the embodiments of the present disclosure.

[0088] Referring to Figure 4 , Figure 4 FIG. is a schematic flowchart of a method for measuring wing deflection deformation according to an embodiment of the present disclosure, including the following steps:

[0089] Step S11: Obtain wing detection data of the wing to be measured, where the wing detection data includes a target file containing the physical quantity acceleration value.

[0090] Step S12: Based on the wing detection data, obtain the effective acceleration value.

[0091] Step S13: According to the effective acceleration value, calculate the deformation data of the wing to be measured, where the deformation data includes the deflection deformation and the torsional deformation angle generated by the wing to be measured relative to the earth coordinate system.

[0092] Step S14: According to the deformation data, determine the measurement result of the wing deflection deformation to be measured, where the measurement result of the wing deflection deformation includes the deformation angle and the deflection deformation distance corresponding to the target measurement point on the wing to be measured.

[0093] It should be noted that the present disclosure can be applied to flexible wings with an extremely long aspect ratio, and can also be applied to other types of wings. The embodiments of the present disclosure are not limited thereto.

[0094] Through the above technical solution, first, the physical quantity acceleration value of the wing to be measured is directly obtained as the wing detection data, and the effective acceleration value is calculated according to the wing detection data. Then, according to the calculated effective acceleration value, the deformation data is calculated. Finally, according to the deformation data, the measurement result of the wing deflection deformation to be measured is determined. In this way, it can accurately reflect the dynamic changes of the wing during flight, help to timely discover and accurately measure the deformation of the wing, and thus provide strong technical support for improving flight safety performance, optimizing wing design and maintenance.

[0095] Furthermore, this technical solution has strong flexibility and adaptability and can be applied to flexible wings of different models and sizes. By adjusting the algorithm parameters and data processing methods, it can easily handle the impacts of different flight conditions and complex environments on wing deformation measurement, ensuring the accuracy and reliability of the measurement results. Compared with traditional contact measurement methods such as pasting strain gauges and arranging fiber optic sensors, this technical solution adopts a non-contact data acquisition method, avoiding the risk of damaging the wing structure or increasing extra weight due to the installation of various measurement devices. At the same time, it also reduces the possibility of measurement interruption and data loss caused by measurement device failures or detachment. In addition, due to the reduction in the number of sensors used and the wiring complexity, the overall cost and maintenance difficulty of the system are reduced, thereby improving the economy and practicality.

[0096] In a possible way, obtain the wing detection data of the wing to be measured, including:

[0097] Obtain the original acceleration voltage value data of the wing to be measured at the target measurement point;

[0098] Obtain the line calibration formula corresponding to the original acceleration voltage value data;

[0099] Based on the line calibration formula, convert the original acceleration voltage value data into a target file containing the physical quantity acceleration value;

[0100] Determine the wing detection data according to the target file containing the physical quantity acceleration value.

[0101] Exemplarily, based on the above wing deflection deformation measurement system, the original acceleration voltage value data can be obtained from the data maintenance port, and then the corresponding relationship between the hexadecimal code value and the physical quantity acceleration value, that is, the line calibration formula corresponding to the original acceleration voltage value data, can be obtained. Through the ground conversion software for recording data parsing and the line calibration formula, the original acceleration voltage value data is converted into a target file containing the physical quantity acceleration value. In this way, the wing detection data can be determined according to the target file containing the physical quantity acceleration value.

[0102] In a possible way, based on the wing detection data, obtain the effective acceleration value, including:

[0103] Perform low-pass filtering on the target file containing the physical quantity acceleration value to filter out the vibration interference data in the target file containing the physical quantity acceleration value, and obtain the target file after low-pass filtering;

[0104] Determine the effective acceleration value based on the target file after low-pass filtering.

[0105] Exemplarily, due to the influence of high-frequency vibration signals during the operation of the aircraft, which will cause a large deviation in the subsequent calculation of the deformation amount, the target file containing the physical quantity of the acceleration value can be subjected to low-pass filtering to filter out the vibration interference data in the target file containing the physical quantity of the acceleration value, and obtain the target file after low-pass filtering. Specifically, the parameters of the low-pass filtering function can be set according to the sampling rate and the low-pass cut-off frequency of the three-axis MEMS accelerometer sensor to achieve high-frequency signal filtering. After effectively filtering out the vibration interference data, the effective acceleration value is determined based on the target file after low-pass filtering.

[0106] In a possible way, according to the effective acceleration value, calculate the deformation data of the wing to be measured, including:

[0107] According to the effective acceleration value, determine the first acceleration value generated by the X-axis of the measurement coordinate system of the wing to be measured, the second acceleration value generated by the Y-axis of the measurement coordinate system, and the third acceleration value generated by the Z-axis of the measurement coordinate system;

[0108] Obtain the principle conversion formula between acceleration and tilt angle;

[0109] According to the first acceleration value, the second acceleration value, the third acceleration value and the principle conversion formula, calculate the tilt angle data of the wing to be measured relative to the earth coordinate system;

[0110] According to the tilt angle data and the position of the target measurement point, determine the deformation data.

[0111] Exemplarily, based on the above content, the measurement coordinate system is the measurement coordinate of the three-axis accelerometer. The first acceleration value is the acceleration value generated by the X-axis of the three-axis accelerometer measurement coordinate system, the second acceleration value is the acceleration value generated by the Y-axis of the three-axis accelerometer measurement coordinate system, and the third acceleration value is the acceleration value generated by the Z-axis of the three-axis accelerometer measurement coordinate system.

[0112] In a possible way, according to the first acceleration value, the second acceleration value, the third acceleration value and the principle conversion formula, calculate the tilt angle data of the wing to be measured relative to the earth coordinate system, including:

[0113] Based on the following first formula, calculate the first included angle between the XOY plane of the measurement coordinate system after tilting along the XOZ plane of the measurement coordinate system and the XOY plane in the earth coordinate system:

[0114]

[0115] where θ is the first included angle, A x is the first acceleration value, A y is the second acceleration value, A zis the third acceleration value;

[0116] Based on the following second formula, calculate the second angle between the XOY plane of the measurement coordinate system after tilting along the YOZ plane of the measurement coordinate system and the XOY plane in the geodetic coordinate system:

[0117]

[0118] wherein, is the second angle;

[0119] Based on the following third formula, calculate the third angle, which is the angle between the Z-axis of the measurement coordinate system and the Z-axis of the geodetic coordinate system after the XOY plane of the measurement coordinate system tilts along the XOZ plane and the YOZ plane simultaneously:

[0120]

[0121] wherein, φ is the third angle.

[0122] Exemplarily, when the three-axis MEMS accelerometer sensor is conformally connected to the wing and deforms, angles between planes or between an axis and a plane will be generated. Figure 5 is a deformation schematic diagram related to the solution of the embodiment of the present disclosure. As Figure 5 shown, in Figure a, the measurement coordinate system coincides with the geodetic coordinate system. In Figures b, c, and d, the dashed coordinate system is the geodetic coordinate system XYZ, and the solidly shown part is the measurement coordinate system XYZ.

[0123] Specifically, as shown in Figure b, the XOY plane of the measurement coordinate system tilts along the XOZ plane of the measurement coordinate system, generating an angle with the XOY plane in the geodetic coordinate system, that is, the first angle θ.

[0124] As shown in Figure c, after the tilt shown in Figure a is performed, the XOY plane of the measurement coordinate system tilts again along the YOZ plane of the measurement coordinate system, also generating an angle with the XOY plane in the geodetic coordinate system, that is, the second angle

[0125] As shown in Figure d, after the tilts shown in Figures a and b are performed simultaneously, an angle is also generated between the Z-axis of the measurement coordinate system and the Z-axis of the geodetic coordinate system, that is, the third angle φ.

[0126] In a possible manner, according to the deformation data, determine the measurement result of the deflection deformation of the wing to be measured, including:

[0127] Obtain the digital mock-up design drawing of the wing to be measured;

[0128] According to the digital mock-up design drawing, determine the wing parameters of the wing to be measured;

[0129] Calculate the spanwise and chordwise deformation data corresponding to the target measurement points according to the wing parameters and deformation data;

[0130] Input the spanwise and chordwise deformation data into the trained deformation prediction model to obtain the deformation prediction result output by the deformation prediction model;

[0131] Determine the deflection deformation measurement result according to the deformation prediction result.

[0132] Exemplarily, the wing parameters of the wing to be measured may include the length information of the wing to be measured, the beam, and the rib. The spanwise and chordwise deformation data corresponding to the target measurement points can be calculated according to the wing parameters, the deformation data, and the following formula:

[0133] Δlspanwise deformation = Lwingspan * sinθ

[0134]

[0135] Wherein, the X-axis direction is along the spanwise direction, the Y-axis direction is along the chordwise direction, and the Z-axis is perpendicular to the ground as specified. Δlspanwise deformation is the deformation amount generated in the corresponding spanwise direction, Δlchordwise deformation is the deformation amount generated in the corresponding chordwise direction, Lwingspan is the wingspan length, and Lwing width is the wing width.

[0136] Then, the spanwise and chordwise deformation data, the angles of multiple target measurement points, and the deformation distance data can be used as input factors and input into the trained deformation prediction model to obtain the deformation prediction result output by the deformation prediction model. Furthermore, the deflection deformation measurement result can be determined according to the deformation prediction result.

[0137] In a possible manner, the deformation prediction model is a cubic spline interpolation model.

[0138] Exemplarily, using the cubic spline interpolation model, discrete data points can be smoothed and the values of unknown points can be predicted. In the present disclosure, the angles and deformation distance data of multiple target measurement points can be used as input factors, and the cubic spline interpolation model can be used to predict the deformation angles and deflection deformation distances of the entire wing. By inputting the data of multiple target measurement points, the cubic spline interpolation model will output the predicted deformation angles and deflection deformation distances of each point on the entire wing.

[0139] Among them, the angles and deformation distance data of multiple target measurement points can be collected and sorted out to ensure the accuracy and reliability of the data. Then, according to the collected data, a cubic spline interpolation model is established. Each target measurement point on the wing to be measured is used as a prediction point, and the established cubic spline interpolation model is used for prediction calculation. To output the predicted deformation angles and deflection deformation distances of each point on the entire wing. The training method of the cubic spline interpolation model in the embodiments of the present disclosure is not specifically limited.

[0140] The prediction results can be used to evaluate the deformation and stability of the wing, providing data support for subsequent maintenance and repair work. At the same time, by comparing the prediction results with the actual measurement results, the accuracy and reliability of the prediction model can be further verified and improved.

[0141] Referring to Figure 6 , Figure 6 is a structural block diagram of a wing deflection deformation measurement device according to an embodiment of the present disclosure. Based on the same inventive concept as the foregoing embodiment, the device includes:

[0142] A first acquisition module 10 for acquiring wing detection data of the wing to be measured, where the wing detection data includes a target file containing a physical quantity acceleration value;

[0143] A second acquisition module 20 for acquiring an effective acceleration value based on the wing detection data;

[0144] A calculation module 30 for calculating deformation data of the wing to be measured according to the effective acceleration value, where the deformation data includes a deflection deformation and a torsional deformation angle generated by the wing to be measured relative to the earth coordinate system;

[0145] A determination module 40 for determining a deflection deformation measurement result of the wing to be measured according to the deformation data, where the deflection deformation measurement result includes a deformation angle and a deflection deformation distance corresponding to a target measurement point on the wing to be measured.

[0146] Optionally, the determination module 40 is configured to:

[0147] Obtain a digital mock-up design drawing of the wing to be measured for the deflection deformation measurement of the wing to be measured;

[0148] Determine wing parameters of the wing to be measured according to the digital mock-up design drawing;

[0149] Calculate spanwise and chordwise deformation data corresponding to the target measurement point according to the wing parameters and the deformation data;

[0150] Input the spanwise and chordwise deformation data into a trained deformation prediction model to obtain a deformation prediction result output by the deformation prediction model;

[0151] Determine the deflection deformation measurement result according to the deformation prediction result.

[0152] Optionally, the first acquisition module 10 is configured to:

[0153] Acquire original acceleration voltage value data of the wing to be measured at the target measurement point;

[0154] Obtain the calibration line formula corresponding to the original acceleration voltage value data;

[0155] Based on the calibration line formula, convert the original acceleration voltage value data into the target file containing the physical quantity acceleration value;

[0156] Determine the wing detection data according to the target file containing the physical quantity acceleration value.

[0157] Optionally, the second acquisition module 20 is used for:

[0158] Perform low-pass filtering on the target file containing the physical quantity acceleration value to filter out the vibration interference data in the target file containing the physical quantity acceleration value, and obtain the target file after low-pass filtering;

[0159] Determine the effective acceleration value based on the target file after low-pass filtering.

[0160] Optionally, the calculation module 30 is used for the wing to be measured:

[0161] According to the effective acceleration value, determine the first acceleration value generated by the X-axis of the measurement coordinate system of the wing to be measured, the second acceleration value generated by the Y-axis of the measurement coordinate system, and the third acceleration value generated by the Z-axis of the measurement coordinate system;

[0162] Obtain the principle conversion formula between acceleration and tilt angle;

[0163] According to the first acceleration value, the second acceleration value, the third acceleration value and the principle conversion formula, calculate the tilt angle data generated by the wing to be measured relative to the earth coordinate system;

[0164] Determine the deformation data according to the tilt angle data and the position of the target measurement point.

[0165] Optionally, the calculation module 30 is used for the wing to be measured:

[0166] Based on the following first formula, calculate the first angle between the XOY plane of the measurement coordinate system after tilting along the XOZ plane of the measurement coordinate system and the XOY plane in the earth coordinate system:

[0167]

[0168] where θ is the first angle, A x is the first acceleration value, A y is the second acceleration value, A z is the third acceleration value;

[0169] Based on the following second formula, calculate the second angle between the XOY plane of the measurement coordinate system after tilting along the YOZ plane of the measurement coordinate system and the XOY plane in the geodetic coordinate system:

[0170]

[0171] Wherein, is the second angle;

[0172] Based on the following third formula, calculate the third angle, where the third angle is the angle between the Z-axis of the measurement coordinate system and the Z-axis of the geodetic coordinate system after the XOY plane of the measurement coordinate system tilts along the XOZ plane and the YOZ plane simultaneously:

[0173]

[0174] Wherein, φ is the third angle.

[0175] Optionally, the deformation prediction model is a cubic spline interpolation model.

[0176] It should be noted that since the steps performed by the device in this embodiment are the same as those in the foregoing method embodiment, the specific implementation manners and the achievable technical effects can be referred to the foregoing embodiment, and will not be elaborated here.

[0177] In addition, in one embodiment, the embodiments of the present disclosure further provide an electronic device, the device includes a processor, a memory, and a computer program stored in the memory, and the computer program realizes the steps of the method in the foregoing embodiment when being run by the processor.

[0178] In addition, in one embodiment, the embodiments of the present disclosure further provide a computer storage medium, and a computer program is stored on the computer storage medium, and the computer program realizes the steps of the method in the foregoing embodiment when being run by the processor.

[0179] In some embodiments, the computer-readable storage medium may be a memory such as FRAM, ROM, PROM, EPROM, EEPROM, flash memory, magnetic surface memory, optical disc, or CD-ROM; or may be various devices including one or any combination of the foregoing memories. The computer may be various computing devices including smart terminals and servers.

[0180] In some embodiments, the executable instructions may be in the form of a program, software, software module, script, or code, written in any form of programming language (including compiled or interpreted languages, or declarative or procedural languages), and may be deployed in any form, including being deployed as a stand-alone program or being deployed as a module, component, subroutine, or other unit suitable for use in a computing environment.

[0181] As an example, the executable instructions may or may not correspond to a file in a file system, may be stored as part of a file that holds other programs or data, for example, in one or more scripts in a Hyper Text Markup Language (HTML) document, stored in a single file dedicated to the program in question, or, stored in multiple cooperating files (such as files that store one or more modules, subroutines, or portions of code).

[0182] As an example, the executable instructions may be deployed to execute on one computing device, or on multiple computing devices located at one site, or, on multiple computing devices distributed across multiple sites and interconnected by a communication network.

[0183] It should be noted that, in this document, the terms "include", "may include", or any other variant thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or system that includes a series of elements includes not only those elements but also other elements not expressly listed, or elements that are inherent to such process, method, article, or system. Without further limitation, an element defined by the statement "including a..." does not exclude the existence of additional identical elements in the process, method, article, or system that includes the element.

[0184] The serial numbers of the above-described embodiments of the present disclosure are merely for description and do not represent the advantages or disadvantages of the embodiments.

[0185] From the description of the above embodiments, those skilled in the art can clearly understand that the above-described embodiment methods can be implemented by means of software plus a necessary general hardware platform. Of course, they can also be implemented by hardware, but in many cases the former is a better implementation. Based on such an understanding, the technical solution of the present disclosure, in essence, or the part that contributes to the prior art, can be embodied in the form of a software product. The computer software product is stored in a storage medium (such as a read-only memory / random access memory, magnetic disk, optical disk), and includes several instructions for causing a multimedia terminal device (which may be a mobile phone, a computer, a television receiver, or a network device, etc.) to execute the methods described in various embodiments of the present disclosure.

[0186] The above are only alternative embodiments of the present disclosure, and do not limit the patent scope of the present disclosure accordingly. Any equivalent structural transformation made by using the content of the specification and drawings of the present disclosure under the inventive concept of the present disclosure, or any direct / indirect application in other related technical fields is included in the patent protection scope of the present disclosure.

Claims

1. A method for measuring the deflection deformation of a wing, characterized in that, Including: Obtain wing detection data of the wing to be measured, where the wing detection data includes a target file containing a physical quantity acceleration value; Based on the wing detection data, obtain an effective acceleration value; According to the effective acceleration value, calculate the deformation data of the wing to be measured, where the deformation data includes the deflection deformation and the torsional deformation angle generated by the wing to be measured relative to the earth coordinate system; According to the deformation data, determine the deflection deformation measurement result of the wing to be measured, where the deflection deformation measurement result includes the deformation angle and the deflection deformation distance corresponding to the target measurement point on the wing to be measured.

2. The method according to claim 1, characterized in that, The determining the deflection deformation measurement result of the wing to be measured according to the deformation data includes: Obtain the digital mock-up design drawing of the wing to be measured; According to the digital mock-up design drawing, determine the wing parameters of the wing to be measured; According to the wing parameters and the deformation data, calculate the spanwise and chordwise deformation data corresponding to the target measurement point; Input the spanwise and chordwise deformation data into the trained deformation prediction model to obtain the deformation prediction result output by the deformation prediction model; According to the deformation prediction result, determine the deflection deformation measurement result.

3. The method according to claim 1, wherein The obtaining the wing detection data of the wing to be measured includes: Obtain the original acceleration voltage value data of the wing to be measured at the target measurement point; Obtain the line calibration formula corresponding to the original acceleration voltage value data; Based on the line calibration formula, convert the original acceleration voltage value data into the target file containing the physical quantity acceleration value; According to the target file containing the physical quantity acceleration value, determine the wing detection data.

4. The method according to claim 1, characterized in that, The obtaining the effective acceleration value based on the wing detection data includes: Perform low-pass filtering on the target file containing the physical quantity acceleration value to filter out the vibration interference data in the target file containing the physical quantity acceleration value, and obtain the target file after low-pass filtering; Based on the target file after low-pass filtering, determine the effective acceleration value.

5. The method according to claim 1, characterized in that, The calculating the deformation data of the wing to be measured according to the effective acceleration value includes: According to the effective acceleration value, determine the first acceleration value generated by the X-axis of the measurement coordinate system of the wing to be measured, the second acceleration value generated by the Y-axis of the measurement coordinate system, and the third acceleration value generated by the Z-axis of the measurement coordinate system; Obtain the principle conversion formula between acceleration and tilt angle; According to the first acceleration value, the second acceleration value, the third acceleration value, and the principle conversion formula, calculate the tilt angle data generated by the wing to be measured relative to the earth coordinate system; According to the tilt angle data and the position of the target measurement point, determine the deformation data.

6. The method according to claim 5, characterized in that, The calculating the tilt angle data generated by the wing to be measured relative to the earth coordinate system according to the first acceleration value, the second acceleration value, the third acceleration value, and the principle conversion formula includes: Calculate a first angle between the XOY plane of the measurement coordinate system after tilting along the XOZ plane of the measurement coordinate system and the XOY plane in the geodetic coordinate system based on the following first formula: Where θ is the first included angle, A x is the first acceleration value, A y is the second acceleration value, A z is the third acceleration value; Calculate a second angle between the XOY plane of the measurement coordinate system after tilting along the YOZ plane of the measurement coordinate system and the XOY plane in the geodetic coordinate system based on the following second formula: Wherein, is the second included angle; Calculate a third angle based on the following third formula, where the third angle is the angle between the Z-axis of the measurement coordinate system and the Z-axis of the geodetic coordinate system after the XOY plane of the measurement coordinate system tilts along the XOZ plane and the YOZ plane simultaneously: where φ is the third angle.

7. The method according to any one of claims 2-7, characterized in that, The deformation prediction model is a cubic spline interpolation model.

8. An aircraft wing deflection deformation measurement system, characterized in that, Including: A data acquisition device, arranged at a target measurement point of the wing to be measured, for acquiring acceleration voltage data on an accelerometer sensor of the wing to be measured; A data recording device, arranged in an aircraft equipment compartment corresponding to the wing to be measured, for recording hexadecimal code values corresponding to the acceleration voltage data; A separation and extension device, with one end connected to the data acquisition device and the other end connected to the data recording device, for connecting the data acquisition device and the data recording device together; A wing deflection deformation measurement device, for determining a wing deflection deformation measurement result of the wing to be measured according to the acceleration voltage data acquired by the data acquisition device.

9. The system according to claim 8, wherein the wing deflection deformation measurement device includes: A first acquisition module, for acquiring wing detection data of the wing to be measured, where the wing detection data includes a target file containing a physical quantity acceleration value; A second acquisition module, for acquiring an effective acceleration value based on the wing detection data; A calculation module, for calculating deformation data of the wing to be measured according to the effective acceleration value, where the deformation data includes deflection deformation and torsional deformation angles generated by the wing to be measured relative to the geodetic coordinate system; A determination module, for determining a wing deflection deformation measurement result according to the deformation data, where the wing deflection deformation measurement result includes a deformation angle and a deflection deformation distance corresponding to a target measurement point on the wing to be measured.

10. A computer-readable storage medium, characterized in that, A computer program is stored on the computer-readable storage medium, and the processor executes the computer program to implement the method according to any one of claims 1-7.

11. An electronic device, characterized in that, The electronic device includes a memory and a processor, a computer program is stored in the memory, and the processor executes the computer program to implement the method according to any one of claims 1-7.

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