Spectrum identification and position calibration system for aircraft connecting piece

Abstract

The embodiment of the invention discloses a spectrum identification and position calibration system for an aircraft connecting piece. A spectrum identification module in the system obtains spectrum data of the aircraft connecting piece; the adaptive noise filtering module is used for removing environmental noise in the spectral data based on an adaptive noise filtering algorithm; the data processing module identifies the material and characteristics of the aircraft connecting piece based on the spectral data after the environmental noise is removed; the thermal deformation prediction and compensation module is used for predicting thermal deformation of the connecting piece based on a thermodynamic model and temperature monitoring data obtained through real-time measurement of a temperature sensor, and performing real-time thermal deformation compensation on the aircraft connecting piece; the position calibration module is used for calibrating the position of the aircraft connecting piece according to the identification result of the material and the characteristic of the aircraft connecting piece in combination with the thermal deformation compensation result of the thermal deformation prediction and compensation module on the aircraft connecting piece; and the control and display module executes a control calibration process of the aircraft connecting piece and displays a spectrum identification result and a position calibration result. According to the technical scheme provided by the invention, the problems of low recognition precision, incapability of predicting and compensating deformation of the connecting piece caused by temperature change in real time, difficulty in guaranteeing accuracy and stability of a calibration result and the like in the existing detection and calibration mode of the airplane connecting piece are solved.

Description

Technical Field

[0001] The present invention relates to, but is not limited to, the technical field of aircraft structure detection, and in particular to a spectrum recognition and position calibration system for aircraft connectors. Background Art

[0002] In the aviation field, aircraft connectors are key components to ensure the stability and safety of aircraft structures. These connectors work in high temperature, high humidity and other extreme environments, requiring them to have extremely high stability and precise assembly. Traditional detection and calibration methods for aircraft connectors mainly rely on manual inspection and basic measuring instruments. However, due to the influence of environmental factors and material properties on detection accuracy, traditional methods often face the following challenges in practical applications, including environmental noise interference, thermal deformation caused by temperature changes, and the influence of changes in material properties on recognition results.

[0003] At present, the existing detection and calibration methods for aircraft connectors have the following shortcomings: First, under the influence of environmental noise, traditional spectral recognition technology is often unable to accurately extract the spectral data of connectors, resulting in low recognition accuracy; second, for the problem of thermal deformation, the existing technology usually relies on static measurement and simple compensation methods, and cannot predict and compensate for the deformation of connectors caused by temperature changes in real time; in addition, the existing system often ignores the combined effects of material properties and thermal deformation during the position calibration process, making it difficult to ensure the accuracy and stability of the final calibration results. These shortcomings affect the detection accuracy of aircraft connectors and the overall reliability of the system. Summary of the invention

[0004] Purpose of the present invention: In order to solve the above-mentioned technical problems, an embodiment of the present invention provides a spectral recognition and position calibration system for aircraft connectors, so as to solve the problems of existing detection and calibration methods for aircraft connectors, such as low recognition accuracy, inability to predict and compensate for connector deformation caused by temperature changes in real time, and difficulty in ensuring the accuracy and stability of calibration results.

[0005] Technical solution of the present invention: An embodiment of the present invention provides a spectrum recognition and position calibration system for aircraft connectors, comprising: a spectrum recognition module, an adaptive noise filtering module, a data processing module, a position calibration module and a control and display module connected in sequence, a thermal deformation prediction and compensation module connected to the position calibration module, and a plurality of temperature sensors electrically connected to the thermal deformation prediction and compensation module;

[0006] The spectrum recognition module is used to obtain spectrum data of aircraft connectors;

[0007] The adaptive noise filtering module is used to remove environmental noise in the spectrum data acquired by the spectrum recognition module based on an adaptive noise filtering algorithm;

[0008] The data processing module is used to identify the material and characteristics of the aircraft connection parts based on the spectral data after removing the environmental noise;

[0009] The thermal deformation prediction and compensation module is used to predict the thermal deformation of the connector based on the thermodynamic model and the temperature monitoring data obtained by real-time measurement using the temperature sensor, and to perform real-time thermal deformation compensation on the aircraft connector; the processing method of the thermal deformation prediction and compensation module includes:

[0010] Sa, temperature monitoring: the temperature of aircraft connectors is monitored in real time through multiple temperature sensors arranged on the aircraft connectors;

[0011] Sb, Thermodynamic modeling: Establish a thermodynamic model of the connector to predict the thermal deformation behavior under different temperature conditions;

[0012] Sc, real-time analysis: input the real-time monitored temperature of aircraft connectors into the thermodynamic model to calculate the real-time thermal deformation;

[0013] Sd, thermal deformation compensation: Generate compensation instructions based on the calculated thermal deformation;

[0014] Se, execution feedback: perform thermal deformation compensation according to the generated compensation instructions and monitor the compensation effect in real time;

[0015] The position calibration module is used to calibrate the position of the aircraft connection part according to the recognition result of the material and characteristics of the aircraft connection part by the data processing module and the thermal deformation compensation result of the aircraft connection part by the thermal deformation prediction and compensation module;

[0016] The control and display module is used to control the execution of the calibration process of the aircraft connection parts and display the spectrum identification results and the position calibration results.

[0017] Optionally, in the spectrum recognition and position calibration system for aircraft connectors as described above, the spectrum recognition module includes: a light source unit, a spectrum sensor, and a scanning unit;

[0018] Wherein, the light source unit is used to emit a light beam within a predetermined wavelength range to the surface of the aircraft connecting part;

[0019] The spectral sensor is used to receive the light beam reflected or transmitted from the surface of the aircraft connection part and convert it into a spectral signal;

[0020] The scanning unit is used to control the movement of the light source unit and the spectrum sensor to perform a comprehensive spectrum scan on the entire surface of the aircraft connecting part.

[0021] Optionally, in the above-mentioned spectrum recognition and position calibration system for aircraft connectors, the adaptive noise filtering module includes: a noise sensor and an adaptive filter; the adaptive noise filtering module executes the adaptive noise filtering algorithm in the following manner:

[0022] S11, initialization: Set the initial filter coefficient w(0) to a zero vector and the learning rate μ to a positive number, expressed as:

[0023] w(0)=0,μ>0;

[0024] S12, noise monitoring: recording the environmental noise signal x(n) in real time through the noise sensor;

[0025] S13, spectrum data recording: recording spectrum data d(n) including noise;

[0026] S14, Noise Estimation: Estimated noise signal through adaptive filter output It is expressed as:

[0027]

[0028] Among them, w(n) T is the transpose of the adaptive filter coefficient vector at the nth iteration;

[0029] S15, error signal calculation: Calculate the difference between the actual spectrum data and the estimated noise signal, expressed as:

[0030]

[0031] Where, e(n) is the error signal at the nth iteration;

[0032] S16, filter coefficient update: update the filter coefficient w(n) according to the error signal, expressed as:

[0033] w(n+1)=w(n)+vx(n)e(n);

[0034] Wherein, w(n+1) is the adaptive filter coefficient vector at the n+1th iteration time, w(n) is the adaptive filter coefficient vector at the nth iteration time, and μx(n)e(n) is the amount adjusted according to the current environmental noise signal and error signal.

[0035] Optionally, in the above-mentioned spectrum recognition and position calibration system for aircraft connectors, the processing method of the data processing module includes:

[0036] S21, spectral data preprocessing: normalizing the spectral data after removing environmental noise;

[0037] S22, feature extraction: extract key features from the normalized spectral data, including peak position, peak intensity and half-peak width, expressed as:

[0038] λ peak = argmax λ d norm (λ);

[0039] I peak =max λ d norm (λ);

[0040] FWHM = λ2-λ1;

[0041] Among them, λ peak is the peak position, I peak is the peak intensity, FWHM is the half maximum width, λ is the wavelength, d norm (λ) is the intensity value of the normalized spectral data at wavelength λ, and λ1 and λ2 are the spectral intensities at half the peak intensity (I peak / 2) corresponding to the wavelength position;

[0042] S23, Classification and Recognition: Use the support vector machine algorithm to classify the extracted key features and identify the materials and characteristics of aircraft connectors.

[0043] Optionally, in the above-mentioned spectrum recognition and position calibration system for aircraft connectors, a plurality of temperature sensors are pre-arranged at different positions of the aircraft connectors; the thermal deformation prediction and compensation module performs temperature monitoring in the following manner:

[0044] S-a1, data collection: periodically collect temperature data from each temperature sensor, expressed as:

[0045] T i (t) = T i (t);

[0046] Among them, T i (t) is the temperature data recorded by the temperature sensor at position i at time t;

[0047] S-a2, temperature data analysis: Analyze the collected temperature data to generate the overall temperature distribution diagram of the aircraft connector, expressed as:

[0048] T dist =f(T1(t),T2(t),...,T n (t));

[0049] Among them, T dist is the overall temperature distribution diagram of the connector, and f(·) is the temperature distribution calculation function.

[0050] Optionally, in the above-mentioned spectrum recognition and position calibration system for aircraft connectors, the thermodynamic model adopts a thermal fluid dynamics model, and the thermal deformation prediction and compensation module performs thermodynamic modeling in the following manner:

[0051] S-b1, initialization and meshing, including: 3D modeling of aircraft connectors, and decomposition of them into multiple finite volume units using meshing technology, expressed as:

[0052]

[0053] Where Ω is the overall domain of the connector, Ω i is the i-th finite volume element, N is the total number of elements;

[0054] S-b2, establish the fluid motion equation, including: describing the flow behavior of the fluid on the surface of the aircraft connection, expressed as:

[0055]

[0056] Where u is the fluid velocity, p is the pressure, μ is the dynamic viscosity, and f is the body force;

[0057] S-b3, establish the energy equation to describe the heat transfer and temperature change between the fluid and the aircraft connection parts, expressed as:

[0058]

[0059] Where ρ is the density, c p is the specific heat capacity at constant pressure, T is the temperature, k is the thermal conductivity, and Q is the internal heat source;

[0060] S-b4, establish the solid thermal stress equation to describe the stress-strain relationship of aircraft connectors under temperature changes, expressed as:

[0061] σ ij =C ijkl (∈ kl -α kl ΔT);

[0062] Among them, σ ij is the stress tensor, C ijkl is the elastic modulus, ∈ kl is the strain tensor, α kl is the coefficient of thermal expansion, ΔT is the temperature change;

[0063] S-b5, set the interface coupling condition for the solid thermal stress equation to describe the interface heat exchange and thermal stress transfer between the fluid and the aircraft connector, expressed as:

[0064] qinterface =h(T f -T s );

[0065] Among them, q interface is the interface heat flux, h is the convective heat transfer coefficient, T f is the fluid temperature, T s is the solid surface temperature;

[0066] S-b6, iterative solution: the numerical iterative method is used to solve the equations from S-b2 to S-b5 to obtain the temperature field and stress field of the fluid and the aircraft connection parts;

[0067] The temperature field is expressed as:

[0068]

[0069] Among them, T n+1 is the temperature field at the n+1th iteration, T n is the temperature field at the nth iteration, Δt is the time step, α is the thermal diffusion coefficient, Q is the internal heat source, and u n is the fluid velocity at the nth iteration;

[0070] The stress field is expressed as:

[0071]

[0072] in, is the stress tensor at the n+1th iteration, is the strain tensor at the n+1th iteration, α kl is the coefficient of thermal expansion, ΔT n+1 is the temperature change at the n+1th iteration.

[0073] Optionally, in the above-mentioned spectrum recognition and position calibration system for aircraft connectors, the thermal deformation prediction and compensation module performs real-time analysis in the following manner:

[0074] S-c1, temperature data input: the temperature data {T i (t)} is input into the thermal fluid thermodynamic model in real time;

[0075] S-c2, solve the thermodynamic model: based on the input temperature data, use the thermofluid dynamics model to calculate the temperature field T(t) and stress field σ(t) of the aircraft connector;

[0076] S-c3, calculation of thermal deformation: by solving the temperature field and stress field, the real-time thermal deformation ΔL of the aircraft connector is calculated, which is expressed as:

[0077] ΔL=αL0ΔT;

[0078] Where ΔL is the length change, α is the thermal expansion coefficient, L0 is the initial length, and ΔT is the temperature change.

[0079] Optionally, in the above-mentioned spectrum recognition and position calibration system for aircraft connectors, the thermal deformation prediction and compensation module performs thermal deformation compensation in the following manner:

[0080] S-d1, thermal deformation input: receiving the calculated thermal deformation ΔL;

[0081] S-d2, calculate compensation parameters: calculate the required compensation parameters according to the thermal deformation, including displacement and angle adjustment, expressed as:

[0082] C displacement =β displacement ΔL;

[0083] Among them, C displacement is the displacement compensation parameter, β displacement is the displacement compensation coefficient, ΔL is the thermal deformation;

[0084] C angle =β angle ΔL;

[0085] Among them, C angle is the angle compensation parameter, β angle is the angle compensation coefficient, ΔL is the thermal deformation;

[0086] S-d3, compensation instruction generation: compensation instructions are generated based on compensation parameters and temperature monitoring results, and the compensation instructions include position adjustment instructions, angle adjustment instructions, stress release instructions, temperature control instructions and mechanical correction instructions; wherein, the stress release instructions are obtained through displacement and angle adjustment caused by thermal deformation of aircraft connectors and changes in material properties, the temperature control instructions are generated through real-time temperature monitoring results, and the mechanical correction instructions are obtained through physical correction of the overall mechanical system based on comprehensive position, angle, stress and temperature factors.

[0087] Optionally, in the above-mentioned spectrum recognition and position calibration system for aircraft connectors, the thermal deformation prediction and compensation module performs feedback in the following manner:

[0088] S-e1, compensation execution: perform actual compensation operations according to compensation instructions;

[0089] S-e2, effect monitoring: real-time monitoring of compensation effect and collection of status data after compensation;

[0090] S-e3, effect evaluation: analyze the state data after compensation, compare it with the target state, and use the root mean square error to evaluate the compensation effect;

[0091] S-e4, feedback adjustment: adjust compensation parameters and compensation instructions according to the results of effect evaluation.

[0092] Optionally, in the above-mentioned spectrum recognition and position calibration system for aircraft connecting parts, the position calibration module calibrates the position of the aircraft connecting parts in the following manner:

[0093] S31, obtaining material and characteristic data: obtaining material characteristic data and spectrum recognition results of aircraft connecting parts;

[0094] S32, obtaining thermal deformation compensation data;

[0095] S33, Position calibration: Using the position calibration formula, the material and characteristics of the aircraft connector and the thermal deformation compensation data are used as input to calculate the calibration position P cal , expressed as:

[0096] P cal =P measured +ΔP mat +ΔP therm ;

[0097] Among them, P cal is the calibrated aircraft connector position, P measured is the original measurement position, ΔP mat is the calibration quantity based on the material and characteristics, ΔP therm is the calibration quantity based on thermal deformation;

[0098] ΔP mat =k mat ·(TT ref );

[0099] ΔP therm =k therm ·D;

[0100] Among them, k mat is the material property calibration coefficient, T is the actual temperature, T ref is the reference temperature, k therm is the thermal deformation compensation coefficient, and D is the thermal deformation compensation data;

[0101] S34, perform position calibration: according to the calculated calibration position P cal Adjust the position of the aircraft connector.

[0102] Beneficial effects of the present invention: The embodiment of the present invention provides a spectral identification and position calibration system for aircraft connectors. On the one hand, by combining the spectral identification module with the adaptive noise filtering algorithm, the system can effectively remove the interference of environmental noise on spectral data, thereby improving the accuracy and reliability of spectral data. This process ensures the accurate identification of the material and characteristics of aircraft connectors, and provides a solid data foundation for subsequent thermal deformation compensation and position calibration. The adaptive noise filtering algorithm used has the ability to dynamically adjust the filter coefficient, can adapt to different noise environments in real time, and further improves the accuracy of spectral identification;

[0103] On the other hand, by real-time monitoring of the temperature of the connector and combining thermodynamic modeling to accurately calculate the thermal deformation at different temperatures, the system can generate effective compensation instructions. These compensation instructions include displacement, angle adjustment, stress release, etc., ensuring the accurate position and functional stability of the connector under different temperature conditions. The feedback mechanism in the compensation process also optimizes the compensation effect through real-time monitoring and effect evaluation, reduces errors, and improves the stability and reliability of the system.

[0104] On the other hand, through comprehensive analysis of material properties and thermal deformation data, the system can achieve high-precision adjustment of the connector position, ensuring the accurate assembly of the connector in the actual working environment. This calibration process significantly improves the efficiency of aircraft maintenance and manufacturing, optimizes the assembly quality of aircraft connectors, and improves the performance and safety of the aircraft under various working conditions. BRIEF DESCRIPTION OF THE DRAWINGS

[0105] The accompanying drawings are used to provide a further understanding of the technical solution of the present invention and constitute a part of the specification. Together with the embodiments of the present application, they are used to explain the technical solution of the present invention and do not constitute a limitation on the technical solution of the present invention.

[0106] Figure 1 A schematic diagram of the overall structure of a spectrum recognition and position calibration system for aircraft connectors provided by an embodiment of the present invention;

[0107] Figure 2 for Figure 1 The illustrated embodiment provides a schematic diagram of the workflow of a thermal deformation prediction and compensation module in a spectral recognition and position calibration system for aircraft connectors. DETAILED DESCRIPTION

[0108] In order to make the purpose, technical solution and advantages of the present invention more clear, the embodiments of the present invention will be described in detail with reference to the accompanying drawings. It should be noted that the embodiments and features in the embodiments of the present application can be combined with each other arbitrarily without conflict.

[0109] The above background technology has explained the importance of aircraft connectors in aircraft structures, and the requirements for high stability and precise assembly of aircraft connectors during use; this requires the inspection and calibration of aircraft connectors, and lists many problems with existing inspection and calibration methods for aircraft connectors.

[0110] There are many problems with the existing detection and calibration methods for aircraft connectors. An embodiment of the present invention provides a spectral recognition and position calibration system for aircraft connectors, which effectively addresses the impact of environmental noise and temperature changes on the detection accuracy of aircraft connectors, ensures stability and reliability under various working conditions, and thus improves the maintenance and manufacturing efficiency and quality of aircraft.

[0111] The present invention provides the following specific embodiments which can be combined with each other. The same or similar concepts or processes may not be described in detail in some embodiments.

[0112] Figure 1 The overall structure diagram of a spectrum recognition and position calibration system for aircraft connectors provided by an embodiment of the present invention is shown in FIG. Figure 1 As shown, the spectral recognition and position calibration system for aircraft connectors provided by an embodiment of the present invention includes: a spectral recognition module, an adaptive noise filtering module, a data processing module, a position calibration module and a control and display module connected in sequence, a thermal deformation prediction and compensation module connected to the position calibration module, and a plurality of temperature sensors electrically connected to the thermal deformation prediction and compensation module.

[0113] like Figure 1 In the system shown, the spectrum recognition module in the embodiment of the present invention is used to obtain spectrum data of aircraft connecting parts.

[0114] The adaptive noise filtering module in the embodiment of the present invention is used to remove environmental noise in the spectrum data acquired by the spectrum recognition module based on an adaptive noise filtering algorithm.

[0115] The data processing module in the embodiment of the present invention is used to identify the material and characteristics of the aircraft connecting parts based on the spectral data after the environmental noise is removed.

[0116] The thermal deformation prediction and compensation module in the embodiment of the present invention is used to predict the thermal deformation of the connecting parts based on the thermodynamic model and the temperature monitoring data obtained by real-time measurement using the temperature sensor, and to perform real-time thermal deformation compensation on the aircraft connecting parts; Figure 2 for Figure 1 The illustrated embodiment provides a schematic diagram of the workflow of a thermal deformation prediction and compensation module in a spectrum recognition and position calibration system for aircraft connectors; the processing method of the thermal deformation prediction and compensation module includes:

[0117] Sa, temperature monitoring: the temperature of aircraft connectors is monitored in real time through multiple temperature sensors arranged on the aircraft connectors;

[0118] Sb, Thermodynamic modeling: Establish a thermodynamic model of the connector to predict the thermal deformation behavior under different temperature conditions;

[0119] Sc, real-time analysis: input the real-time monitored temperature of aircraft connectors into the thermodynamic model to calculate the real-time thermal deformation;

[0120] Sd, thermal deformation compensation: Generate compensation instructions based on the calculated thermal deformation;

[0121] Se, execution feedback: perform thermal deformation compensation according to the generated compensation instructions, and monitor the compensation effect in real time.

[0122] The position calibration module in the embodiment of the present invention is used to calibrate the position of the aircraft connecting part according to the recognition result of the material and characteristics of the aircraft connecting part by the data processing module and the thermal deformation compensation result of the aircraft connecting part by the thermal deformation prediction and compensation module.

[0123] The control and display module in the embodiment of the present invention is used to control the execution of the calibration process of the aircraft connection parts and display the spectrum recognition result and the position calibration result.

[0124] The spectral identification and position calibration system for aircraft connectors provided in the embodiment of the present invention realizes high-precision and high-reliability aircraft connector detection and calibration through the functions realized by the above-mentioned functional modules, can effectively cope with the influence of environmental noise and temperature changes on detection accuracy, ensure stability and reliability under various working conditions, thereby improving the efficiency and quality of aircraft maintenance and manufacturing.

[0125] In one implementation of the embodiment of the present invention, the spectrum recognition module includes: a light source unit, a spectrum sensor, and a scanning unit. The implementation functions of each functional unit in this implementation are described as follows:

[0126] A light source unit for emitting a light beam within a predetermined wavelength range to a surface of an aircraft connecting part;

[0127] A spectral sensor for receiving a light beam reflected or transmitted from a surface of an aircraft connection part and converting the light beam into a spectral signal;

[0128] The scanning unit is used to control the movement of the light source unit and the spectrum sensor to perform a comprehensive spectrum scan on the entire surface of the aircraft connection part.

[0129] In this implementation, the above-mentioned functional units not only improve the coverage and accuracy of spectral data, but also ensure the comprehensiveness and consistency of data, provide a reliable basis for subsequent analysis and processing and position calibration, and significantly improve the detection efficiency and accuracy of the system.

[0130] In an implementation of the embodiment of the present invention, the adaptive noise filtering module includes: a noise sensor and an adaptive filter; the adaptive noise filtering module executes the adaptive noise filtering algorithm in the following manner:

[0131] S11, initialization: Set the initial filter coefficient w(0) to a zero vector and the learning rate μ to a positive number, expressed as:

[0132] w(0)=0,μ>0;

[0133] S12, noise monitoring: recording the environmental noise signal x(n) in real time through the noise sensor;

[0134] S13, spectrum data recording: recording spectrum data d(n) including noise;

[0135] S14, Noise Estimation: Estimated noise signal through adaptive filter output It is expressed as:

[0136]

[0137] Among them, w(n) T is the transpose of the adaptive filter coefficient vector at the nth iteration;

[0138] S15, error signal calculation: Calculate the difference between the actual spectrum data and the estimated noise signal, expressed as:

[0139]

[0140] Where, e(n) is the error signal at the nth iteration;

[0141] S16, filter coefficient update: update the filter coefficient w(n) according to the error signal, expressed as:

[0142] w(n+1)=w(n)+μx(n)e(n);

[0143] Wherein, w(n+1) is the adaptive filter coefficient vector at the n+1th iteration time, w(n) is the adaptive filter coefficient vector at the nth iteration time, and μx(n)e(n) is the amount adjusted according to the current environmental noise signal and error signal.

[0144] In this implementation, the above steps of the adaptive noise filtering algorithm are executed by the adaptive noise filtering module, which can monitor the environmental noise in real time, and dynamically adjust the filter coefficients using the adaptive noise filtering algorithm to remove the environmental noise in the spectral data. By initializing the filter coefficients and setting the learning rate, the system can adapt to different noise environments and gradually optimize the filtering effect. The environmental noise signal recorded by the noise sensor is combined with the spectral data recorded by the spectral sensor, and the noise signal is estimated and the error signal is calculated through the adaptive filter, and finally the filter coefficients are adjusted to ensure the filtering accuracy and the reliability of spectral recognition.

[0145] In one implementation of the embodiment of the present invention, the processing method of the above data processing module includes the following steps:

[0146] S21, spectral data preprocessing: normalize the spectral data after removing the environmental noise to reduce the influence of spectral intensity fluctuations, expressed as:

[0147]

[0148] Among them, d(i) is the intensity value of the spectral data at wavelength i after noise removal, d norm (i) is the intensity value of the normalized spectral data at wavelength i, min(d) and max(d) are the minimum and maximum values ​​of the spectral data after noise removal;

[0149] S22, feature extraction: extract key features from the normalized spectral data, including peak position, peak intensity and half-peak width, expressed as:

[0150] λ peak = argmax λ d norm (λ);

[0151] I peak =max λ d norm (λ);

[0152] FWHM = λ2-λ1;

[0153] Among them, λ peak is the peak position, I peak is the peak intensity, FWHM is the half maximum width, λ is the wavelength, d norm (λ) is the intensity value of the normalized spectral data at wavelength λ, and λ1 and λ2 are the spectral intensities at half the peak intensity (I peak / 2) corresponding to the wavelength position;

[0154] S23, Classification and Identification: Use the support vector machine algorithm to classify the extracted key features and identify the material and characteristics of the aircraft connectors, expressed as:

[0155]

[0156] Among them, x is the input feature vector, N is the number of training samples, α i is the Lagrange multiplier, y i is the label (material and characteristics) of the training sample, K(x i ,x) is the radial basis function (RBF) kernel function.

[0157] In this implementation, the data processing module executes the above steps of its processing method, thereby improving the accuracy and reliability of spectral recognition, being able to effectively identify the material and characteristics of aircraft connectors, and significantly improving the accuracy and efficiency of detection.

[0158] In an implementation of the embodiment of the present invention, a plurality of temperature sensors are pre-arranged at different positions of the aircraft connection parts; based on the arrangement of the temperature sensors, the thermal deformation prediction and compensation module performs temperature monitoring in the following manner:

[0159] S-a1, data collection: periodically collect temperature data from each temperature sensor, expressed as:

[0160] T i (t) = T i (t);

[0161] Among them, T i (t) is the temperature data recorded by the temperature sensor at position i at time t;

[0162] S-a2, temperature data analysis: Analyze the collected temperature data to generate the overall temperature distribution diagram of the aircraft connector, expressed as:

[0163] T dist =f(T1(t),T2(t),...,T n (t));

[0164] Among them, T dist is the overall temperature distribution diagram of the connector, and f(·) is the temperature distribution calculation function.

[0165] In this implementation, the temperature distribution calculation function adopts a linear interpolation algorithm, for example, and can be expressed as:

[0166]

[0167] Among them, T dist (x) is the interpolated temperature at position x, T iis the position temperature data of the i-th sensor, w i (x) is the weight associated with the ith sensor at position x, satisfying

[0168] Weight w i (x) is calculated based on the inverse distance weighted method of the sensor location, expressed as:

[0169]

[0170] Among them, d i (x) is the distance between position x and the position of the i-th sensor, and p is the curtain parameter of the distance, which is 2.

[0171] In this implementation, by executing the above steps of temperature monitoring, the temperatures of different key positions of aircraft connectors are monitored in real time, and the overall temperature distribution diagram is generated by combining the data acquisition and processing unit. Interpolation algorithms such as linear interpolation are used to achieve fusion and analysis of temperature data to ensure the accuracy and comprehensiveness of temperature monitoring, effectively improve the real-time response capability and accuracy of the system, and ensure the stability and reliability of aircraft connectors under different temperature conditions.

[0172] In an implementation of the embodiment of the present invention, the thermodynamic model adopts a thermal fluid dynamics model; the thermal deformation prediction and compensation module performs thermodynamic modeling, which may include the following steps:

[0173] S-b1, initialization and meshing, including: 3D modeling of aircraft connectors, and decomposition of them into multiple finite volume units using meshing technology, expressed as:

[0174]

[0175] Where Ω is the overall domain of the connector, Ω i is the i-th finite volume element, N is the total number of elements;

[0176] S-b2, establish the fluid motion equation, including: describing the flow behavior of the fluid on the surface of the aircraft connection, expressed as:

[0177]

[0178] Where u is the fluid velocity, p is the pressure, μ is the dynamic viscosity, and f is the body force;

[0179] S-b3, establish the energy equation to describe the heat transfer and temperature change between the fluid and the aircraft connection parts, expressed as:

[0180]

[0181] Where ρ is the density, cp is the specific heat capacity at constant pressure, T is the temperature, k is the thermal conductivity, and Q is the internal heat source;

[0182] S-b4, establish the solid thermal stress equation to describe the stress-strain relationship of aircraft connectors under temperature changes, expressed as:

[0183] σ ij =C ijkl (∈ kl -α kl ΔT);

[0184] Among them, σ ij is the stress tensor, C ijkl is the elastic modulus, ∈ kl is the strain tensor, α kl is the coefficient of thermal expansion, ΔT is the temperature change;

[0185] S-b5, set the interface coupling condition for the solid thermal stress equation to describe the interface heat exchange and thermal stress transfer between the fluid and the aircraft connector, expressed as:

[0186] q interface =h(T f -T s );

[0187] Among them, q interface is the interface heat flux, h is the convective heat transfer coefficient, T f is the fluid temperature, T s is the solid surface temperature;

[0188] S-b6, iterative solution: the numerical iterative method is used to solve the equations from S-b2 to S-b5 to obtain the temperature field and stress field of the fluid and the aircraft connection parts;

[0189] The temperature field is expressed as:

[0190]

[0191] Among them, T n+1 is the temperature field at the n+1th iteration, T n is the temperature field at the nth iteration, Δt is the time step, α is the thermal diffusion coefficient, Q is the internal heat source, and u n is the fluid velocity at the nth iteration;

[0192] The stress field is expressed as:

[0193]

[0194] in, is the stress tensor at the n+1th iteration, is the strain tensor at the n+1th iteration, α kl is the coefficient of thermal expansion, ΔT n+1 is the temperature change at the n+1th iteration

[0195] In this implementation, by executing the above steps of thermodynamic modeling, the aircraft connector is decomposed into multiple finite volume units through mesh division, the Navier-Stokes equations are used to describe the fluid motion, the heat conduction equation is used to simulate the heat exchange between the fluid and the solid, and the solid thermal stress equation is introduced to describe the stress-strain relationship of the connector under temperature changes. Through the interface coupling condition, the fluid temperature and the solid temperature are coupled and calculated, and the above equations are solved using the numerical iteration method. Finally, the accurate temperature field and stress field distribution are obtained, which can more accurately simulate the thermal deformation behavior of the aircraft connector in a complex thermal environment, provide accurate data support for the subsequent thermal deformation compensation, and improve the prediction accuracy and reliability of the system.

[0196] In one implementation of the embodiment of the present invention, the thermal deformation prediction and compensation module performs real-time analysis in the following manner:

[0197] S-c1, temperature data input: the temperature data {T i (t)} is input into the thermal fluid thermodynamic model in real time;

[0198] S-c2, solve the thermodynamic model: based on the input temperature data, use the thermofluid dynamics model to calculate the temperature field T(t) and stress field σ(t) of the aircraft connector;

[0199] S-c3, calculation of thermal deformation: by solving the temperature field and stress field, the real-time thermal deformation ΔL of the aircraft connector is calculated, which is expressed as:

[0200] ΔL=αL0ΔT;

[0201] Where ΔL is the length change, α is the thermal expansion coefficient, L0 is the initial length, and ΔT is the temperature change.

[0202] In this implementation, by performing the above steps of real-time analysis, the system's responsiveness to changes in complex thermal environments is enhanced, accurate data support is provided, and the accuracy and reliability of thermal deformation compensation are effectively improved, thereby ensuring the stability and safety of aircraft connectors under various working conditions.

[0203] In one implementation of the embodiment of the present invention, the thermal deformation prediction and compensation module performs thermal deformation compensation in the following steps:

[0204] S-d1, thermal deformation input: receiving the calculated thermal deformation ΔL;

[0205] S-d2, calculate compensation parameters: calculate the required compensation parameters according to the thermal deformation, including displacement and angle adjustment, expressed as:

[0206] C displacement =β displacement ΔL;

[0207] Among them, C displacement is the displacement compensation parameter, expressed as the displacement required to be applied, β displacement is the displacement compensation coefficient, which indicates the proportional coefficient of the displacement compensation required for unit thermal deformation; ΔL is the thermal deformation, which indicates the change in the length of the connector due to temperature change;

[0208] C angle =β angle ΔL;

[0209] Among them, C angle is the angle compensation parameter, expressed as the angle adjustment amount to be applied, β angle is the angle compensation coefficient, which indicates the proportional coefficient of the angle compensation required for unit thermal deformation; ΔL is the thermal deformation, which indicates the change in the length of the connector due to temperature change;

[0210] S-d3, compensation instruction generation: compensation instructions are generated based on compensation parameters and temperature monitoring results. The compensation instructions include position adjustment instructions (for displacement compensation), angle adjustment instructions (for rotation compensation), stress release instructions, temperature control instructions, and mechanical correction instructions (physical adjustment by actuators); among them, stress release instructions are obtained through displacement and angle adjustment caused by thermal deformation and material property changes of aircraft connectors, temperature control instructions are generated through real-time temperature monitoring results, and mechanical correction instructions are obtained through physical correction of the overall mechanical system based on comprehensive position, angle, stress and temperature factors. The generation method and function of each instruction are explained as follows:

[0211] Position adjustment instructions: Instructions generated by combining displacement compensation and angle compensation are used to accurately adjust the position of the connector to ensure that it can return to the predetermined state after thermal deformation compensation;

[0212] Angle adjustment command: A command generated based on the angle compensation parameter, used to adjust the installation angle of the connector to ensure the correctness of its direction;

[0213] Stress release instruction: During the compensation process, the displacement and angle adjustment caused by thermal deformation and changes in material properties should be promptly released to prevent material damage or fatigue.

[0214] Temperature control instructions: Instructions generated based on real-time temperature monitoring results adjust the temperature of the connector to ensure that the material is within the appropriate working range to maintain its performance;

[0215] Mechanical Correction Instructions: Physical correction of the overall mechanical system taking into account factors such as position, angle, stress and temperature to ensure proper alignment and function of each component.

[0216] In this implementation, by executing the above steps of thermal deformation compensation, the error caused by thermal deformation is effectively reduced, thereby improving the reliability and stability of the overall system. This precise compensation mechanism not only enhances the maintenance efficiency of the aircraft, but also improves the safety and performance of the aircraft in various operating environments.

[0217] In an implementation of the embodiment of the present invention, the thermal deformation prediction and compensation module performs feedback in a manner that may include the following steps:

[0218] S-e1, compensation execution: perform actual compensation operations according to compensation instructions;

[0219] S-e2, effect monitoring: real-time monitoring of compensation effect and collection of status data after compensation;

[0220] S-e3, effect evaluation: Analyze the state data after compensation, compare it with the target state, and use the root mean square error to evaluate the compensation effect, which is expressed as:

[0221]

[0222] Among them, D i is the actual measured data after compensation, D target,i is the target data, N is the number of data points;

[0223] S-e4, feedback adjustment: adjust compensation parameters and compensation instructions according to the results of effect evaluation.

[0224] In this implementation, by executing the above steps of feedback, the compensation error is effectively reduced, the reliability and stability of the system are improved, thereby optimizing the overall compensation process and ensuring high-precision and high-efficiency operation.

[0225] In an implementation of the embodiment of the present invention, the position calibration module calibrates the position of the aircraft connection component, which may include the following steps:

[0226] S31, obtaining material and characteristic data: obtaining material characteristic data and spectrum recognition results of aircraft connecting parts;

[0227] S32, obtaining thermal deformation compensation data;

[0228] S33, Position calibration: Using the position calibration formula, the material and characteristics of the aircraft connector and the thermal deformation compensation data are used as input to calculate the calibration position P cal , expressed as:

[0229] P cal =P measured +ΔP mat +ΔP therm ;

[0230] Among them, P cal is the calibrated aircraft connector position, P measured is the original measurement position, ΔP mat is the calibration quantity based on the material and characteristics, ΔP therm is the calibration quantity based on thermal deformation;

[0231] ΔP mat =k mat ·(TT ref );

[0232] ΔP therm =k therm ·D;

[0233] Among them, k mat is the material property calibration coefficient, T is the actual temperature, T ref is the reference temperature, k therm is the thermal deformation compensation coefficient, and D is the thermal deformation compensation data;

[0234] S34, perform position calibration: according to the calculated calibration position P cal Adjust the position of the aircraft connector.

[0235] In this implementation, the above-mentioned steps of calibrating the position of the aircraft connector are implemented, and the material properties and thermal deformation compensation data of the aircraft connector are comprehensively considered, so that the position of the connector can be accurately adjusted, thereby ensuring the accurate assembly and functional stability of the aircraft connector in the actual working environment.

[0236] The embodiment of the present invention provides a spectral recognition and position calibration system for aircraft connectors. On the one hand, by combining a spectral recognition module with an adaptive noise filtering algorithm, the system can effectively remove the interference of environmental noise on spectral data, thereby improving the accuracy and reliability of spectral data. This process ensures accurate recognition of the material and characteristics of aircraft connectors, and provides a solid data foundation for subsequent thermal deformation compensation and position calibration. The adaptive noise filtering algorithm used has the ability to dynamically adjust the filter coefficient, can adapt to different noise environments in real time, and further improves the accuracy of spectral recognition.

[0237] On the other hand, by real-time monitoring of the temperature of the connector and combining thermodynamic modeling to accurately calculate the thermal deformation at different temperatures, the system can generate effective compensation instructions. These compensation instructions include displacement, angle adjustment, stress release, etc., ensuring the accurate position and functional stability of the connector under different temperature conditions. The feedback mechanism in the compensation process also optimizes the compensation effect through real-time monitoring and effect evaluation, reduces errors, and improves the stability and reliability of the system.

[0238] On the other hand, through comprehensive analysis of material properties and thermal deformation data, the system can achieve high-precision adjustment of the connector position, ensuring the accurate assembly of the connector in the actual working environment. This calibration process significantly improves the efficiency of aircraft maintenance and manufacturing, optimizes the assembly quality of aircraft connectors, and improves the performance and safety of the aircraft under various working conditions.

[0239] Although the embodiments disclosed in the present invention are as above, the contents are only embodiments adopted to facilitate understanding of the present invention and are not intended to limit the present invention. Any technician in the field to which the present invention belongs can make any modifications and changes in the form and details of implementation without departing from the spirit and scope disclosed in the present invention, but the patent protection scope of the present invention shall still be subject to the scope defined in the attached claims.

Claims

1. A spectrum recognition and position calibration system for aircraft connectors, characterized in that: include: A spectrum recognition module, an adaptive noise filtering module, a data processing module, a position calibration module and a control and display module connected in sequence, a thermal deformation prediction and compensation module connected to the position calibration module, and a plurality of temperature sensors electrically connected to the thermal deformation prediction and compensation module; Wherein, the spectrum recognition module is used to obtain spectrum data of aircraft connectors; The adaptive noise filtering module is used to remove environmental noise in the spectrum data acquired by the spectrum recognition module based on an adaptive noise filtering algorithm; The data processing module is used to identify the material and characteristics of the aircraft connection parts based on the spectral data after removing the environmental noise; The thermal deformation prediction and compensation module is used to predict the thermal deformation of the connector based on the thermodynamic model and the temperature monitoring data obtained by real-time measurement using the temperature sensor, and to perform real-time thermal deformation compensation on the aircraft connector; the processing method of the thermal deformation prediction and compensation module includes: Sa, temperature monitoring: the temperature of aircraft connectors is monitored in real time through multiple temperature sensors arranged on the aircraft connectors; Sb, Thermodynamic modeling: Establish a thermodynamic model of the connector to predict the thermal deformation behavior under different temperature conditions; Sc, real-time analysis: input the real-time monitored temperature of aircraft connectors into the thermodynamic model to calculate the real-time thermal deformation; Sd, thermal deformation compensation: Generate compensation instructions based on the calculated thermal deformation; Se, execution feedback: perform thermal deformation compensation according to the generated compensation instructions and monitor the compensation effect in real time; The position calibration module is used to calibrate the position of the aircraft connection part according to the recognition result of the material and characteristics of the aircraft connection part by the data processing module and the thermal deformation compensation result of the aircraft connection part by the thermal deformation prediction and compensation module; The control and display module is used to control the execution of the calibration process of the aircraft connection parts and display the spectrum identification results and the position calibration results.

2. The spectrum recognition and position calibration system for aircraft connectors according to claim 1, characterized in that: The spectrum recognition module includes: a light source unit, a spectrum sensor, and a scanning unit; Wherein, the light source unit is used to emit a light beam within a predetermined wavelength range to the surface of the aircraft connecting part; The spectral sensor is used to receive the light beam reflected or transmitted from the surface of the aircraft connection part and convert it into a spectral signal; The scanning unit is used to control the movement of the light source unit and the spectrum sensor to perform a comprehensive spectrum scan on the entire surface of the aircraft connecting part.

3. The spectrum recognition and position calibration system for aircraft connectors according to claim 1, characterized in that: The adaptive noise filtering module includes: a noise sensor and an adaptive filter; the adaptive noise filtering module executes the adaptive noise filtering algorithm in the following manner: S11, initialization: Set the initial filter coefficient w(0) to a zero vector and the learning rate μ to a positive number, expressed as: w(0)=0,μ>0; S12, noise monitoring: recording the environmental noise signal x(n) in real time through the noise sensor; S13, spectrum data recording: recording spectrum data d(n) including noise; S14, Noise Estimation: Estimated noise signal through adaptive filter output It is expressed as: Among them, w(n) T is the transpose of the adaptive filter coefficient vector at the nth iteration; S15, error signal calculation: Calculate the difference between the actual spectrum data and the estimated noise signal, expressed as: Where, e(n) is the error signal at the nth iteration; S16, filter coefficient update: update the filter coefficient w(n) according to the error signal, expressed as: w(n+1)=w(n)+vx(n)e(n); Among them, w(n+1) is the adaptive filter coefficient vector at the n+1th iteration time, w(n) is the adaptive filter coefficient vector at the nth iteration time, and μx(n)e(n) is the amount adjusted according to the current environmental noise signal and error signal.

4. The spectrum recognition and position calibration system for aircraft connectors according to claim 1, characterized in that: The processing method of the data processing module includes: S21, spectral data preprocessing: normalizing the spectral data after removing environmental noise; S22, feature extraction: extract key features from the normalized spectral data, including peak position, peak intensity and half-peak width, expressed as: l peak =argmax λ d norm (l); I peak =max λ d norm (l); FWHM = λ2-λ1; Among them, λ peak is the peak position, I peak is the peak intensity, FWHM is the half maximum width, λ is the wavelength, d norm (λ) is the intensity value of the normalized spectral data at wavelength λ, and λ1 and λ2 are the spectral intensities at half the peak intensity (I peak / 2) corresponding to the wavelength position; S23, Classification and Recognition: Use the support vector machine algorithm to classify the extracted key features and identify the materials and characteristics of aircraft connectors.

5. The spectrum recognition and position calibration system for aircraft connectors according to claim 1, characterized in that: A plurality of temperature sensors are pre-arranged at different positions of the aircraft connector; the thermal deformation prediction and compensation module performs temperature monitoring in the following manners: S-a1, data collection: periodically collect temperature data from each temperature sensor, expressed as: T i (t)=T i (t); Among them, T i (t) is the temperature data recorded by the temperature sensor at position i at time t; S-a2, temperature data analysis: Analyze the collected temperature data to generate the overall temperature distribution diagram of the aircraft connector, expressed as: T dist =f(T1(t),T2(t),...,T n (t)); Among them, T dist is the overall temperature distribution diagram of the connector, and f(·) is the temperature distribution calculation function.

6. The spectrum recognition and position calibration system for aircraft connectors according to claim 5, characterized in that: The thermodynamic model adopts a thermal fluid dynamics model, and the thermal deformation prediction and compensation module performs thermodynamic modeling in the following ways: S-b1, initialization and meshing, including: 3D modeling of aircraft connectors, and decomposition of them into multiple finite volume units using meshing technology, expressed as: Where Ω is the overall domain of the connector, Ω i is the i-th finite volume element, N is the total number of elements; S-b2, establish the fluid motion equation, including: describing the flow behavior of the fluid on the surface of the aircraft connection, expressed as: Where u is the fluid velocity, p is the pressure, μ is the dynamic viscosity, and f is the body force; S-b3, establish the energy equation to describe the heat transfer and temperature change between the fluid and the aircraft connection parts, expressed as: Where ρ is the density, c p is the specific heat capacity at constant pressure, T is the temperature, k is the thermal conductivity, and Q is the internal heat source; S-b4, establish the solid thermal stress equation to describe the stress-strain relationship of aircraft connectors under temperature changes, expressed as: s ij =C ijkl (∈ kl -a kl ΔT); Among them, σ ij is the stress tensor, C ijkl is the elastic modulus, ∈ kl is the strain tensor, α kl is the coefficient of thermal expansion, ΔT is the temperature change; S-b5, set the interface coupling condition for the solid thermal stress equation to describe the interface heat exchange and thermal stress transfer between the fluid and the aircraft connector, expressed as: q interface =h(T f -T s ); Among them, q interface is the interface heat flux, h is the convective heat transfer coefficient, T f is the fluid temperature, T s is the solid surface temperature; S-b6, iterative solution: the numerical iterative method is used to solve the equations from S-b2 to S-b5 to obtain the temperature field and stress field of the fluid and the aircraft connection parts; The temperature field is expressed as: Among them, T n+1 is the temperature field at the n+1th iteration, T n is the temperature field at the nth iteration, Δt is the time step, α is the thermal diffusion coefficient, Q is the internal heat source, and u n is the fluid velocity at the nth iteration; The stress field is expressed as: in, is the stress tensor at the n+1th iteration, is the strain tensor at the n+1th iteration, α kl is the coefficient of thermal expansion, ΔT n+1 is the temperature change at the n+1th iteration.

7. The spectrum recognition and position calibration system for aircraft connectors according to claim 6, characterized in that: The thermal deformation prediction and compensation module performs real-time analysis in the following ways: S-c1, temperature data input: the temperature data {T i (t)} is input into the thermal fluid thermodynamic model in real time; S-c2, solve the thermodynamic model: based on the input temperature data, use the thermofluid dynamics model to calculate the temperature field T(t) and stress field σ(t) of the aircraft connector; S-c3, calculation of thermal deformation: by solving the temperature field and stress field, the real-time thermal deformation ΔL of the aircraft connector is calculated, which is expressed as: ΔL=αL0ΔT; Where ΔL is the length change, α is the thermal expansion coefficient, L0 is the initial length, and ΔT is the temperature change.

8. The spectrum recognition and position calibration system for aircraft connectors according to claim 7, characterized in that: The thermal deformation prediction and compensation module performs thermal deformation compensation in the following manner: S-d1, thermal deformation input: receiving the calculated thermal deformation ΔL; S-d2, calculate compensation parameters: Calculate the required compensation parameters according to the thermal deformation, including displacement and angle adjustment, expressed as: C displacement =b displacement ΔL; Among them, C displacement is the displacement compensation parameter, β displacement is the displacement compensation coefficient, ΔL is the thermal deformation; C angle =b angle ΔL; Among them, C angle is the angle compensation parameter, β angle is the angle compensation coefficient, ΔL is the thermal deformation; S-d3, compensation instruction generation: compensation instructions are generated based on compensation parameters and temperature monitoring results, and the compensation instructions include position adjustment instructions, angle adjustment instructions, stress release instructions, temperature control instructions and mechanical correction instructions; wherein, the stress release instructions are obtained through displacement and angle adjustment caused by thermal deformation of aircraft connectors and changes in material properties, the temperature control instructions are generated through real-time temperature monitoring results, and the mechanical correction instructions are obtained through physical correction of the overall mechanical system based on comprehensive position, angle, stress and temperature factors.

9. The spectrum recognition and position calibration system for aircraft connectors according to claim 8, characterized in that: The thermal deformation prediction and compensation module performs feedback in the following manner: S-e1, compensation execution: perform actual compensation operations according to compensation instructions; S-e2, effect monitoring: real-time monitoring of compensation effect and collection of status data after compensation; S-e3, effect evaluation: analyze the state data after compensation, compare it with the target state, and use the root mean square error to evaluate the compensation effect; S-e4, feedback adjustment: adjust compensation parameters and compensation instructions according to the results of effect evaluation.

10. The spectrum recognition and position calibration system for aircraft connectors according to claim 1, characterized in that: The position calibration module calibrates the position of the aircraft connection component in the following manner: S31, obtaining material and characteristic data: obtaining material characteristic data and spectrum recognition results of aircraft connecting parts; S32, obtaining thermal deformation compensation data; S33, Position calibration: Using the position calibration formula, the material and characteristics of the aircraft connector and the thermal deformation compensation data are used as input to calculate the calibration position P cal , expressed as: P cal =P measured +ΔP mat +ΔP therm ; Among them, P cal is the calibrated aircraft connector position, P measured is the original measurement position, ΔP mat is the calibration quantity based on the material and characteristics, ΔP therm is the calibration quantity based on thermal deformation; ΔP mat =k mat ·(T-T ref ); ΔP therm =k therm ·D; Among them, k mat is the material property calibration coefficient, T is the actual temperature, T ref is the reference temperature, k therm is the thermal deformation compensation coefficient, and D is the thermal deformation compensation data; S34, perform position calibration: according to the calculated calibration position P cal Adjust the position of the aircraft connector.

Images