An airport indoor light control method and system

Abstract

This application provides an airport indoor lighting control method and system, applied in the field of airport lighting control technology. It extracts the intensity, direction, and rate of disturbances on the flight display screen through spectral decomposition and inter-frame difference analysis to generate disturbance propagation results. It collects light signals reflected, refracted, and scattered by glass curtain walls, metal components, and composite material panels to construct a multi-media light flux correlation matrix, generating a regional luminous flux coordinated variation distribution. It uses the gate sensor array to calculate the angle change rate and interference bandwidth intensity as feedforward inputs, which are then weighted and superimposed with the illuminance feedback error to form a composite control. Simultaneously, it identifies the adaptive matching compensation coefficient during the docking phase, performing three-degree-of-freedom scheduling of the luminous flux, illumination direction, and beam spread angle of the lighting units. This invention effectively suppresses the dual interference of dynamic screen images and moving aircraft light sources, improving the stability and uniformity of lighting in the waiting area.

Description

Technical Field

[0001] This application relates to the field of airport lighting control technology, and in particular to an airport indoor lighting control method and system. Background Technology

[0002] Airport waiting areas typically have numerous flight information display screens. As these screens dynamically display flight information, the constantly changing content causes rapid disturbances in the emitted light spectrum. This disturbed light, combined with the original illumination, results in uneven local lighting, color temperature shifts, and increased flicker, negatively impacting passenger visual comfort.

[0003] Meanwhile, the waiting area contains large areas of glass curtain walls, metal structural components, and composite material panels. These media reflect, refract, and scatter the disturbance light from the screen, causing it to propagate in a complex manner in three-dimensional space. Traditional lighting control systems only treat the screen as overall ambient light and cannot accurately model the spatial distribution of the disturbance light.

[0004] During aircraft docking operations, external light sources, such as landing lights and taxi lights, change their incident angle and intensity as the aircraft moves, further exacerbating the unpredictability of the lighting environment. Existing technologies mostly employ fixed lighting schemes or rely solely on illuminance sensors for feedback adjustment, which cannot simultaneously address dynamic disturbances on the screen and interference from the movement of external light sources. Summary of the Invention

[0005] The embodiments of this application provide an airport indoor lighting control method and system, which realizes accurate prediction and rapid compensation for dual interference from dynamic screen images and aircraft moving light sources, and improves the lighting stability and uniformity of the waiting area. To achieve the above objectives, this application adopts the following technical solution:

[0006] An airport indoor lighting control method, the method comprising:

[0007] The dynamic display screen of the flight display device is acquired, and the continuous frame images in the display screen are subjected to spectral decomposition and inter-frame difference. The intensity, spatial propagation direction and rate of change of the spectral disturbance are quantitatively extracted to generate the flight display spectral disturbance propagation result.

[0008] The propagation result of the spectral disturbance of the flight display is used as the original light disturbance source of the screen. The light signal transmission path after reflection, refraction and secondary scattering of the screen spectral disturbance light through the glass curtain wall, metal structural parts and composite material plate in the waiting area is collected.

[0009] Based on the propagation results of the spectral disturbance of the flight display and combined with the optical signal transmission path, the correlation of light energy flux at each medium interface is determined; based on the linkage between the correlation and the disturbance propagation results, a regional light flux coordinated change distribution is generated.

[0010] When the aircraft is docked at the bridge, the incident light signal of the external light source of the aircraft is collected, the changes in optical parameters of the incident light signal caused by the movement of the aircraft are calculated, and the stable control relationship of light interference is determined by combining the coordinated change distribution of light flux in the region.

[0011] Based on the aforementioned light interference stability control relationship, the output luminous flux, illumination direction, and beam diffusion angle of multiple lighting units in the waiting area are scheduled.

[0012] In some possible implementations, the quantitative extraction of the intensity, spatial propagation direction, and rate of change of the spectral perturbation to generate the flight sign spectral perturbation propagation results includes:

[0013] Gradient calculation is performed on the spectral difference maps of consecutive frames to obtain the perturbation intensity distribution field;

[0014] The optical flow vector field is solved by the disturbance intensity distribution field to obtain the disturbance motion vector field;

[0015] The spatial propagation direction field and the rate of change field are decomposed from the disturbed motion vector field;

[0016] The disturbance intensity distribution field, spatial propagation direction field, and rate of change field are combined to generate the flight display spectral disturbance propagation results.

[0017] In some possible implementations, determining the optical flux correlation between each medium interface based on the propagation results of the flight display spectral disturbance and the optical signal transmission path includes:

[0018] The initial refractive index and initial transmittance of the glass curtain wall, the initial reflectivity and initial roughness of the metal structural components, and the initial scattering coefficient and initial anisotropy factor of the composite material panel were obtained.

[0019] Using a multi-source optical signal set, the initial refractive index, initial transmittance, initial reflectance, initial roughness, initial scattering coefficient, and initial anisotropy factor are corrected to obtain the calibrated refractive index, transmittance, reflectance, roughness, scattering coefficient, and anisotropy factor; based on the spatial propagation direction field in the propagation results of the flight display spectral disturbance, the incident angle distribution of each medium interface is calculated;

[0020] Based on the incident angle distribution and the calibrated refractive index, reflectivity, and scattering coefficient, the energy transfer coefficients of the refracted optical path, the reflected optical path, and the scattered optical path are calculated respectively.

[0021] The energy transfer coefficients of each optical path are superimposed according to their spatial location to form a multi-medium optical flux correlation matrix as the correlation relationship.

[0022] In some possible implementations, the calculation of the optical parameter changes of the incident light signal caused by aircraft movement, combined with the regional luminous flux co-variation distribution, includes:

[0023] The perturbation intensity distribution field in the propagation results of the flight display spectral perturbation is used as the excitation input;

[0024] The optical flux correlation matrix of the multi-media optical energy transmission is multiplied with the excitation input to obtain the optical flux response value of each optical acquisition node.

[0025] Spatial interpolation is performed on the light flux response value to generate a light flux distribution field covering the waiting area;

[0026] The light flux distribution field is output as the regional light flux coordinated change distribution.

[0027] In some possible implementations, calculating the changes in optical parameters of the incident light signal caused by aircraft movement includes:

[0028] Acquire the incident light intensity timing signal collected by at least three photosensitive sensors located at the boarding gate;

[0029] Calculate the peak time difference between the incident light intensity time-series signals corresponding to different sensors, and calculate the angular change rate of the incident light signal based on the peak time difference and the preset sensor spacing;

[0030] Spectral analysis is performed on the incident light intensity time-series signal to extract the frequency offset and interference bandwidth intensity;

[0031] The angle change rate, the frequency offset, and the interference bandwidth intensity are combined as optical parameter variations.

[0032] In some possible implementations, determining the optical interference stability control relationship by combining the coordinated variation distribution of the regional luminous flux includes:

[0033] The luminous flux distribution field in the coordinated luminous flux variation distribution of the region is used as the reference illumination value; the rate of change of angle and the rate of change of interference intensity in the optical parameter variation are used as feedforward perturbation inputs;

[0034] The illuminance in the waiting area is obtained, the difference between the reference illuminance value and the illuminance is calculated, and the difference is used as the feedback error.

[0035] The feedforward disturbance input and the feedback error are weighted and superimposed to generate an optical interference stability control relationship.

[0036] In some possible implementations, the step of scheduling the output luminous flux, illumination direction, and beam spread angle of multiple lighting units within the waiting area according to the light interference stability control relationship includes:

[0037] Based on the spatial error distribution in the light interference stability control relationship, the illumination direction deflection angle of each lighting unit is calculated, and a first control command including the illumination direction deflection angle is generated. The first control command is then sent to the stepper motor of the corresponding lighting unit.

[0038] Based on the deflection angle of the illumination direction, the local non-uniformity in the light interference stability control relationship is corrected to obtain the corrected local non-uniformity. Based on the corrected local non-uniformity, the beam diffusion angle adjustment value of each illumination unit is calculated, and a second control command including the beam diffusion angle adjustment value is generated. The second control command is sent to the zoom mechanism of the corresponding illumination unit.

[0039] Based on the irradiation direction deflection angle and the beam diffusion angle adjustment value, the reference luminous flux in the light interference stability control relationship is compensated and calculated. The target luminous flux adjustment amount of each lighting unit is analyzed, a third control command including the target luminous flux adjustment amount is generated, and the third control command is sent to the driving circuit of the corresponding lighting unit.

[0040] In some possible implementations, the acquisition of the light signal transmission path after reflection, refraction, and secondary scattering by the screen spectral perturbation light through glass curtain walls, metal structural components, and composite material panels within the waiting area includes:

[0041] The signal data output by optical acquisition nodes set at multiple spatial nodes in the waiting area is acquired. The signal data of each optical acquisition node includes refracted light signal from a first sensor, reflected light signal from a second sensor, and secondary scattered light signal from a third sensor. The first sensor is set towards the glass curtain wall, the second sensor is set towards the metal structure, and the third sensor is set towards the composite material panel.

[0042] The refracted light signal, the reflected light signal, and the secondary scattered light signal at the same node are time-aligned to form a multipath light signal group for the node;

[0043] The multipath optical signal groups of all nodes are aggregated into a multisource optical signal set for the waiting area;

[0044] Based on the multi-source optical signal set and the propagation results of the spectral disturbance of the flight display, combined with the multi-path geometric relationship, an optical signal transmission path is generated.

[0045] In some possible implementations, the method further includes:

[0046] Obtain the curve of the rate of change of the angle over time in the changes of the optical parameters;

[0047] Based on the curve of the angle change rate over time, determine the current stage of the aircraft docking operation;

[0048] Based on the current stage, the corresponding feedforward compensation coefficient is matched from the pre-stored control parameter library;

[0049] The feedforward compensation coefficient is spatially weighted and calculated point-by-point with the luminous flux distribution field in the regional luminous flux cooperative variation distribution to generate a spatially adaptive illumination compensation amount.

[0050] The illumination compensation amount is superimposed on the light interference stability control relationship.

[0051] An airport indoor lighting control system, the system comprising:

[0052] The flight display spectral disturbance analysis module is used to acquire the dynamic display screen of the flight display device, perform spectral decomposition and inter-frame difference on the continuous frame images in the display screen, quantitatively extract the intensity, spatial propagation direction and change rate of the spectral disturbance, and generate the flight display spectral disturbance propagation results.

[0053] The optical signal transmission path acquisition module is used to take the propagation result of the flight display spectral disturbance as the original optical disturbance source of the screen, and to acquire the optical signal transmission path after the screen spectral disturbance light is reflected, refracted and secondary scattered by the glass curtain wall, metal structure and composite material plate in the waiting area.

[0054] The regional luminous flux coordinated distribution generation module is used to determine the correlation of luminous flux at each medium interface based on the propagation results of the spectral disturbance of the flight display and the optical signal transmission path; and to generate a regional luminous flux coordinated change distribution based on the linkage between the correlation and the disturbance propagation results.

[0055] The optical interference stability control relationship determination module is used to collect the incident light signal of the external light source of the aircraft when the aircraft is docked at the bridge, calculate the changes in optical parameters of the incident light signal caused by the movement of the aircraft, and determine the optical interference stability control relationship by combining the coordinated change distribution of the light flux in the region.

[0056] The lighting unit scheduling module is used to schedule the output luminous flux, illumination direction and beam diffusion angle of multiple lighting units in the waiting area according to the light interference stability control relationship.

[0057] As can be seen from the above technical solution, this application has the following beneficial effects:

[0058] 1. This application quantitatively extracts the intensity, spatial propagation direction, and rate of change of spectral disturbances by performing spectral decomposition and inter-frame difference analysis on continuous frame images of the flight display screen, generating accurate propagation results of spectral disturbances in the flight display. This result no longer treats the screen as a general ambient light change, but rather describes the spatiotemporal distribution of disturbances on the screen plane, providing a physically accurate excitation source for subsequent light propagation modeling. Based on this, by collecting multipath light signals reflected, refracted, and scattered by glass curtain walls, metal structural components, and composite material panels, and combining reverse tracing with physical optical models such as Fresnel formulas, Cooktorens models, and Heinrich Grinstein phase functions, a multi-medium light flux correlation matrix is ​​constructed. This matrix quantitatively characterizes how the screen disturbance energy is distributed to various spatial locations in the waiting area through different media, thereby accurately calculating the coordinated change distribution of regional light flux and reducing the calculation errors caused by neglecting the complex optical paths of multiple media in traditional methods.

[0059] 2. This application utilizes three linearly arranged photosensitive sensors at the boarding gate to synchronously collect incident light signals during aircraft docking operations. The angle change rate is calculated using the peak time difference, and frequency offset and interference bandwidth intensity are extracted through spectral analysis, enabling feedforward measurement of the aircraft's external light source movement trend. The angle change rate and bandwidth change rate are used as feedforward disturbance inputs, weighted and superimposed with the measured illuminance feedback error to form a composite control relationship of feedforward and feedback. The feedforward part can respond in advance before interference affects the sensors, while the feedback part eliminates residual errors. Simultaneously, the docking stage is identified through the angle change rate curve, and corresponding feedforward compensation coefficients are matched and spatially weighted to generate illumination compensation, allowing the control parameters to adapt to different stages of aircraft movement. Finally, the output luminous flux, illumination direction, and beam spread angle of the illumination unit are scheduled with three degrees of freedom, achieving refined compensation of spatial illumination distribution and ensuring the stability and uniformity of illumination in the waiting area under dual interference. Attached Figure Description

[0060] The invention will now be further described with reference to the accompanying drawings.

[0061] Figure 1 A flowchart illustrating the generation of spectral disturbance propagation results for flight display systems provided in this application embodiment;

[0062] Figure 2 A flowchart illustrating the construction of the multi-media optical flux correlation matrix provided in this application embodiment;

[0063] Figure 3 A flowchart for generating regional luminous flux coordinated variation distribution provided in this application embodiment;

[0064] Figure 4 A flowchart for determining the optical interference stability control relationship provided in the embodiments of this application;

[0065] Figure 5 A flowchart of lighting unit scheduling provided for an embodiment of this application. Detailed Implementation

[0066] The terms "first," "second," and "third," etc., used in this application specification, claims, and drawings are for distinguishing different objects, not for specifying a particular order.

[0067] In the embodiments of this application, the words "exemplary" or "for example" are used to indicate examples, illustrations, or descriptions. Any embodiment or design described as "exemplary" or "for example" in the embodiments of this application should not be construed as being more preferred or advantageous than other embodiments or designs. Specifically, the use of the words "exemplary" or "for example" is intended to present the relevant concepts in a specific manner.

[0068] Research has revealed that airport lighting control typically treats flight display screens as part of the overall ambient light source, failing to quantitatively extract the spatiotemporal distribution of screen spectral disturbances. It also neglects the reflection, refraction, and scattering of disturbed light by glass curtain walls, metal structural components, and composite material panels, leading to inaccurate modeling of the disturbed light propagation path. Furthermore, the rapid movement of external light sources during aircraft docking causes inherent lag in traditional illuminance feedback adjustment, making it difficult to simultaneously suppress the dual interference of dynamic screen disturbances and moving aircraft light sources.

[0069] To address the aforementioned problems, this application provides a method and system for controlling indoor lighting in airports:

[0070] Example 1

[0071] To solve the above problems, such as Figures 1-5 As shown, this embodiment relates to an airport indoor lighting control method and system, particularly suitable for waiting areas of large hub airports. Airport waiting areas typically have numerous flight information display screens (hereinafter referred to as flight display screens). When these screens dynamically display flight information, such as page turning, scrolling text, and flight status updates, the content of the images constantly changes, causing rapid disturbances in the spectrum emitted by the screens. Simultaneously, the waiting area contains large areas of glass curtain walls, metal structural components such as columns, trusses, and decorative strips, as well as composite material panels such as ceilings, partitions, and seat back panels. These media reflect, refract, and scatter the disturbed light emitted from the screens, causing the disturbed light to propagate complexly within the area. Ultimately, this disturbed light superimposes with the original lighting, resulting in problems such as uneven local illumination, color temperature drift, and increased flicker.

[0072] During aircraft docking at the bridge, the aircraft's external light sources, such as landing lights, taxi lights, wing lights, and collision avoidance lights, change their incident angle and intensity as the aircraft moves. These external light signals enter the waiting area through the boarding gate's glass facade, interacting with the disturbance light from the flight information display screens and the area's lighting, further exacerbating the unpredictability of the lighting environment. Current airport lighting control systems typically employ fixed lighting schemes or rely solely on illuminance sensors for feedback adjustment, failing to simultaneously address the two highly dynamic factors: dynamic disturbances from the flight information display screens and interference from the movement of external aircraft light sources.

[0073] Before implementing this embodiment, the following hardware equipment needs to be installed and configured in the airport waiting area.

[0074] For each flight display screen, a high-speed industrial camera is installed approximately two meters directly in front of it. The camera lens's optical axis is perpendicular to the screen plane, and its field of view should completely cover the entire screen display area. The camera uses a global shutter sensor to avoid inter-frame distortion caused by rolling shutters. The camera's spectral response range should cover the entire visible light spectrum (approximately 380nm to 780nm), and it should be spectrally calibrated before leaving the factory, meaning the conversion matrix between the output values ​​of the red, green, and blue color channels and the incident spectral power density is known. The camera's frame rate is set to at least 20 frames per second to ensure that it can capture details of changes in the screen content.

[0075] Within the waiting area, optical data acquisition nodes are arranged at a density of one node per 20 to 30 square meters. Each node is installed on a pole approximately 1.5 meters high, with the pole location avoiding main passenger traffic routes while ensuring that the node can see the corresponding media surface.

[0076] The first sensor (refracting light sensor): Its photosensitive surface faces the nearest glass curtain wall surface, and the normal direction of the photosensitive surface forms a 30-degree angle with the normal direction of the glass curtain wall. This configuration prioritizes receiving light emitted from the curtain wall after refraction. A narrow-band filter wheel is mounted at the front end of the sensor, allowing for sequential measurement of the intensity of the red, green, and blue bands, as well as the integrated intensity across the entire band. This sensor is used to acquire the intensity of the light signal after refraction through the glass medium.

[0077] The second sensor (reflected light sensor): Its photosensitive surface faces the surface of the metal structure, such as the side of a steel column or the surface of an aluminum plate. The normal direction of the photosensitive surface forms a 20-degree angle with the normal direction of the metal surface to receive reflected light, which is dominated by specular reflection. This sensor is used to acquire the intensity of the light signal reflected from the metal interface.

[0078] The third sensor (scattered light sensor): Its photosensitive surface faces the composite material panel, such as a carbon fiber composite partition or ceiling. The photosensitive surface is parallel to the panel surface to receive diffused light. This sensor is used to acquire the intensity of the light signal scattered by the composite material panel surface.

[0079] All sensors employ high-sensitivity photodiodes and are equipped with logarithmic amplifiers, ensuring that the output signal is proportional to the logarithm of the incident light intensity. This allows them to adapt to both strong light conditions, such as direct sunlight, and weak light conditions, such as nighttime screen lighting environments. The analog voltage signals output by the sensors are converted into 16-bit digital signals by analog-to-digital converters and transmitted to the central controller via a fieldbus.

[0080] At least three photosensitive sensors are linearly arranged horizontally on the inner side of the glass curtain wall at the fixed end of each boarding bridge where it connects to the terminal building. The sensors are evenly spaced, for example, 0.5 meters apart. The sensors are installed at a height approximately 1.2 meters, roughly equivalent to the typical height of external aircraft light sources, such as landing lights. These sensors capture the incident light signal formed after the light emitted from external aircraft light sources passes through the glass curtain wall. The sensors employ silicon photodiodes with microsecond-level response times and a sampling rate of at least 20,000 times per second to capture rapidly changing light source signals. The three sensors sample synchronously, and their spatial coordinates are known.

[0081] All existing LED lights in the waiting area have been replaced with adjustable lights. Each light integrates the following three actuators:

[0082] A two-degree-of-freedom gimbal driven by a stepper motor: It can achieve precise pointing within a range of 360 degrees horizontally and ±90 degrees in pitch. The stepper motor has a step angle of 1.8 degrees, and with microstepping drive, a control accuracy of 0.015 degrees can be achieved.

[0083] The motorized zoom lens assembly consists of a set of movable lenses. The lens position is driven by a miniature linear motor, which can continuously change the beam diffusion angle. The diffusion angle ranges from 10 degrees (narrow beam, used for long-distance projection) to 60 degrees (wide beam, used for large-area uniform illumination).

[0084] Dimmable LED driver circuit: Employs pulse width modulation to adjust output luminous flux. Dimming resolution is no less than 12 bits, or 4096 levels, with a modulation frequency of 2000Hz or higher to avoid visible flicker.

[0085] Each lighting unit has a unique identification number, and the three-dimensional coordinates of its installation location are measured and entered into the central controller database during construction.

[0086] Multiple illuminance sensors are evenly distributed within the waiting area to measure the actual total illuminance on the ground or work surfaces in real time. These sensors differ from the aforementioned optical acquisition nodes; they are specifically designed for feedback control. The illuminance sensors utilize silicon photodiodes in conjunction with visual spectral response correction filters to output illuminance values ​​consistent with human visual perception. The sensors are arranged at a density of approximately one sensor per 50 square meters, installed at a height of 0.8 meters above the ground.

[0087] The central controller employs an industrial-grade embedded computer, equipped with a multi-core processor, large-capacity memory, and a solid-state drive. The controller runs a real-time operating system and connects to all the aforementioned devices via multiple communication interfaces. The controller internally stores the following preset data:

[0088] Geometric parameters (size, position, orientation) of each flight display screen.

[0089] The three-dimensional coordinates of each optical acquisition node.

[0090] Initial optical parameters of each medium (glass, metal, composite material).

[0091] The sensor spacing of the gate sensor array.

[0092] The position, initial orientation, and light distribution curve of each lighting unit (measured in advance).

[0093] The position coordinates of the illuminance sensor.

[0094] Templates for the rate of change of angle during the aircraft docking phase (three typical templates).

[0095] Control parameter library (feedforward compensation coefficient matrix corresponding to each bridge approach stage).

[0096] The controller also runs real-time control software that executes the steps described in this embodiment in a cyclical manner at a fixed period (e.g., 0.1 seconds).

[0097] To ensure clarity and ambiguity in the description of this embodiment, key terms and physical quantities that will appear repeatedly in the following sections are predefined.

[0098] Spectral power density: radiant power per unit wavelength interval, measured in watts per square meter per nanometer. For light emitted from a screen, it describes the energy distribution of each pixel at each wavelength.

[0099] Spectral perturbation: The change in spectral power density at the same pixel location and wavelength between adjacent frames of the flight display screen. Perturbations can be positive or negative, representing an increase or decrease in light intensity.

[0100] Perturbation intensity distribution field: A two-dimensional array, where each element represents the combined intensity of spectral perturbations at the corresponding pixel location on the screen. This intensity is obtained by performing a human visual weighted integral on the spectral differences and calculating the gradient magnitude; it is dimensionless (relative value).

[0101] Optical flow vector: A velocity vector describing the motion of pixels in an image, containing a horizontal velocity component. and vertical velocity components The unit is pixels per frame. It represents the speed and direction of the perturbation pattern's movement on the screen.

[0102] Spatial propagation direction field: The direction angle decomposed from the optical flow vector, representing the direction of disturbance propagation. The direction angle is 0 degrees to the right of the screen horizontally, and positive counterclockwise, with a value range of 0 degrees to 360 degrees.

[0103] Rate of change field: The magnitude of the optical flow vector, representing how fast the perturbation pattern moves, in pixels per frame.

[0104] Results of spectral disturbance propagation in flight display: The combined data structure of the above three fields—disturbance intensity distribution field, spatial propagation direction field, and rate of change field—serves as the excitation source for subsequent optical path calculations.

[0105] Multipath optical signal group: A ternary group consisting of the intensity of refracted light, reflected light, and scattered light simultaneously acquired by the first, second, and third sensors at the same optical acquisition node.

[0106] Multi-source optical signal set: The sum of multipath optical signal groups from all optical acquisition nodes at the same time.

[0107] Initial optical parameters of the medium include the refractive index and transmittance of the glass curtain wall, the reflectivity and roughness of the metal structural components, and the scattering coefficient and anisotropy factor of the composite material panels. These parameters are set according to the manufacturer's data during installation, but require on-site calibration.

[0108] Angle of incidence: The angle between the direction of the ray and the normal to the interface of the medium, ranging from 0 degrees to 90 degrees. 0 degrees indicates perpendicular incidence.

[0109] Energy transfer coefficient: For a given optical path (refractive, reflected, or scattered), the ratio of the energy of the outgoing light to the energy of the incident light, ranging from 0 to 1. This coefficient incorporates physical processes such as interface reflection, transmission, absorption, and scattering.

[0110] Multi-media optical flux correlation matrix: a two-dimensional matrix in which rows correspond to optical acquisition nodes and columns correspond to blocks of the screen. The matrix elements represent the total energy transfer coefficient of perturbation light emitted from a certain screen block through all paths to a certain node.

[0111] Regional luminous flux coordinated variation distribution: A continuous two-dimensional distribution field obtained by spatial interpolation of the luminous flux response values ​​of discrete nodes, representing the additional illuminance distribution covering the entire waiting area caused by screen disturbance.

[0112] Optical parameter variation: A vector measured and calculated by the gate sensor array, containing three components: angular change rate, frequency offset, and interference bandwidth intensity.

[0113] Angular change rate: The horizontal angular velocity of the aircraft's external light source relative to the gate sensor, in degrees per second.

[0114] Frequency offset: The difference between the modulation frequency of the received optical signal and the inherent modulation frequency of the light source due to the Doppler effect, expressed in Hertz.

[0115] Interference bandwidth intensity: the half-power bandwidth of the power spectrum of the incident light intensity time-series signal, in Hertz.

[0116] Reference illuminance value: The distribution field obtained by subtracting the regional luminous flux variation distribution from the target illuminance distribution, representing the illuminance that the lighting unit should output.

[0117] Feedback error: The difference between the reference illuminance value and the illuminance measured by the illuminance sensor.

[0118] Feedforward disturbance input: a vector consisting of the rate of change of angle and the derivative of the disturbance bandwidth intensity with respect to time.

[0119] Optical interference stability control relationship: The formula for calculating the control quantity formed by weighted superposition of feedforward disturbance input and feedback error.

[0120] Spatial point-by-point weighting: A two-dimensional convolution kernel (feedforward compensation coefficient matrix) is slid across the light flux distribution field, and the weighted sum of the convolution kernel and the coverage area is calculated at each position to obtain a new distribution field.

[0121] Specific implementation steps.

[0122] Step A: Generation of the propagation results of the spectral disturbance of the flight display.

[0123] A.1 Acquire the dynamic display screen and decompose it into a spectral image.

[0124] The central controller sends a hardware trigger signal to the industrial camera corresponding to each flight display screen at fixed time intervals, such as 0.05 seconds. Upon receiving the trigger signal, the camera immediately exposes and reads a frame of image. The resolution of each frame is the screen's original resolution, such as 1920×1080 pixels, and each pixel is stored as values ​​for three channels: red, green, and blue, with each channel being an 8-bit or 10-bit digital value.

[0125] The controller converts the red, green, and blue channel values ​​into spectral power density. Since the camera has been spectrally calibrated, a 3×N transformation matrix is ​​known (N is the number of wavelength sampling points, e.g., 31 points, covering 380nm to 780nm, with one point every 10nm). Each column of this matrix corresponds to a wavelength, and each row corresponds to the response coefficients of the red, green, and blue channels. For each pixel, the column vector composed of the red, green, and blue values ​​is multiplied by the transformation matrix to obtain an N-dimensional vector, which represents the spectral power density distribution of that pixel. This same operation is performed on all pixels to obtain the spectral image of the current frame, which is stored as a three-dimensional array: horizontal coordinate × vertical coordinate × wavelength index.

[0126] A.2 Grayscale image of adjacent frame difference and spectral difference.

[0127] Take the spectral image of the current frame and the spectral image of the previous frame (if the previous frame is empty in the first frame, skip it). For each pixel and each wavelength, calculate the difference in spectral power density to obtain a three-dimensional spectral difference array.

[0128] To simplify the differences across multiple wavelengths into a single scalar intensity, a weighting based on human eye sensitivity is required. The photopic spectral luminous efficiency function published by the International Commission on Illumination (ICI) is adopted. This function gives the relative sensitivity of the human eye to different wavelengths of light. For each pixel, a weighted sum is calculated: the difference value at each wavelength is multiplied by... Multiply by the wavelength interval, then sum. The sum is the spectral difference grayscale value of that pixel. The grayscale values ​​of all pixels constitute a two-dimensional grayscale image, called the spectral difference grayscale image.

[0129] A.3 Calculate the disturbance intensity distribution field.

[0130] Spatial gradient calculation is performed on the spectral difference grayscale image. The Sobel operator is used, which contains two 3×3 convolution kernels:

[0131] Horizontal convolution kernel:

[0132]

[0133] Vertical convolution kernel:

[0134]

[0135] The grayscale image is convolved with a horizontal convolution kernel to obtain the horizontal gradient component of each pixel. Convolve with a vertical convolution kernel to obtain the vertical gradient component. Then calculate the gradient magnitude for each pixel:

[0136]

[0137] The larger the gradient magnitude, the more drastic the spectral change at that location, i.e., the greater the disturbance intensity.

[0138] The gradient magnitudes of all pixels are organized into a two-dimensional array, called the perturbation intensity distribution field. The physical meaning of this field is the strength of the spectral perturbation at each point on the screen, and its value is a relative value (dimensionless), which will be used as a relative weight in subsequent calculations.

[0139] A.4 Calculate the optical flow vector to obtain the perturbation motion vector field.

[0140] The motion of the perturbation pattern was calculated using the Lucas-Kanade optical flow method. Three consecutive frames of spectral difference grayscale images were selected. For each pixel, it is assumed that all pixels within its small neighborhood, such as a 5×5 pixel window, have the same motion vector. Based on the assumption of constant brightness:

[0141]

[0142] Taylor expansion yields the optical flow constraint equation:

[0143]

[0144] in For spatial gradient, The temporal gradient is the difference in grayscale between adjacent frames divided by... ).

[0145] For each pixel within the window, an equation can be written. Solving multiple equations simultaneously yields an overdetermined system of linear equations. The least squares method is then used to solve this system. and Constructing a matrix (Each line contains) ) and vector (each line) Then solve the normal equation:

[0146]

[0147] Solution This is the optical flow vector of that pixel.

[0148] Perform the above calculations on all pixels to obtain the perturbation motion vector field, with each pixel corresponding to a two-dimensional vector. .

[0149] A.5 Decompose the spatial propagation direction field and the rate of change field.

[0150] Two independent fields are decomposed from the perturbation motion vector field:

[0151] Spatial propagation direction field: For each pixel, calculate the direction angle.

[0152]

[0153] in The range of return values ​​is arrive .like If it is negative, then Need to be added Make it fall arrive Between. Ultimately The unit is radians or degrees. This angle indicates the direction of perturbation propagation at that pixel.

[0154] Rate of change field: For each pixel, calculate the rate.

[0155]

[0156] The unit is pixels per frame. If the frame rate is known, it can be converted to pixels per second.

[0157] A.6 represents the propagation results of spectral disturbances in flight display data.

[0158] The three two-dimensional arrays of disturbance intensity distribution field, spatial propagation direction field, and rate of change field are packaged into a composite data structure, which is named the flight display spectral disturbance propagation result.

[0159] The dynamic image displayed on a flight display screen is essentially a spatiotemporally varying light radiation field. Through spectral decomposition, it can be converted from the red-green-blue color space to the physical light radiation space; through inter-frame differencing and gradient calculation, the magnitude of the change can be quantified; and through optical flow, the motion of the change can be quantified. This information from three orthogonal dimensions together constitutes a complete description of the screen perturbation, providing accurate source terms for subsequent propagation modeling.

[0160] Step B: Acquisition of optical signal transmission path and construction of multi-media optical energy flux correlation matrix.

[0161] B.1 Synchronous acquisition of multipath optical signals.

[0162] The central controller sends acquisition commands to all optical acquisition nodes via a synchronization bus at a fixed sampling period, such as once every millisecond. Upon receiving the command, each node simultaneously reads the output values ​​of the first, second, and third sensors, converts them from analog to digital, and returns them to the controller.

[0163] The controller stores the three values ​​returned by each node (refracted light intensity, reflected light intensity, and scattered light intensity) along with the node's spatial coordinates into a multipath optical signal set. All multipath optical signal sets from all nodes are then combined into a multisource optical signal set. Since the sampling frequency is much higher than the frame rate of the flight display screen, screen disturbances can be considered quasi-static over a short period.

[0164] B.2 Obtain the initial optical parameters of the medium and perform calibration using multi-source optical signals.

[0165] The controller has the following initial optical parameters pre-stored (typical values; actual values ​​may vary depending on the material):

[0166] Glass curtain wall: refractive index (Initial value 1.5), transmittance (Initial value 0.92). Refractive index is defined as the ratio of the speed of light in a vacuum to the speed of light in glass; transmittance is defined as the proportion of energy that passes through glass when incident perpendicularly.

[0167] Metal structural components: reflectivity (Initial value 0.7), roughness (Initial value 0.1 micrometers). Reflectivity is defined as the ratio of reflected energy to incident energy; roughness is defined as the root mean square height of the micro-undulations of the surface, affecting the diffuse reflection component.

[0168] Composite material plate surface: scattering coefficient (Initial value 0.5 per meter), anisotropy factor (Initial value 0.8). The scattering coefficient defines the average number of times light is scattered per unit length within a material; the anisotropy factor defines the directional preference of scattering, with values ​​close to +1 indicating forward scattering, close to -1 indicating backscattering, and 0 indicating isotropic scattering.

[0169] Because the parameters of the medium surface may change due to factors such as dust, aging, and humidity in the actual environment, on-site calibration is required. The basic principle of calibration is as follows: Given the original disturbance light intensity emitted by the flight display screen (the disturbance intensity distribution field obtained from step A), and the known geometric distance and angle from the screen to each optical acquisition node, the light intensity that each node should receive is calculated through the optical model and compared with the measured light intensity (a set of multi-source optical signals). The medium parameters are adjusted to minimize the error between the calculated and measured values.

[0170] The specific calibration process employs least-squares optimization. First, the current medium parameters are assumed to be initial values. For each optical acquisition node, the total radiant power of the screen is calculated based on the screen perturbation intensity distribution field and geometric relationships. Then, the propagation path of light from the screen to the node is considered: it needs to pass through air, and possibly undergo one reflection / refraction / scattering. Since the waiting area is spacious, only one interaction is considered, and the contribution of multiple interactions is small and negligible. Therefore, the light intensity received by the node can be expressed as: screen radiant power multiplied by the geometric attenuation factor (inversely proportional to the square of the distance) multiplied by the energy transfer coefficient of the medium interface (depending on the incident angle and medium parameters). The formula for calculating the energy transfer coefficient will be detailed in B.4.

[0171] The controller establishes an objective function: the sum of squares of the differences between the calculated light intensity and the measured light intensity at all nodes. Gradient descent is used to calculate the sum of squares of these differences. Calculate the partial derivatives and iteratively update the parameter values ​​until the objective function converges (the difference between two adjacent iterations is less than a preset threshold). After the iteration is complete, obtain the calibrated medium parameters and store them for subsequent calculations.

[0172] B.3 Calculate the incident angle distribution at each medium interface.

[0173] The angle of incidence is the angle between the direction of the ray and the interface normal. To calculate the angle of incidence of the ray received by each optical acquisition node on the medium interface, it is necessary to trace backwards: starting from the node position, extend backwards along the straight line from the node to the screen to find the intersection point with the medium interface.

[0174] Taking a glass curtain wall as an example: A glass curtain wall is a plane in space, and its plane equation (normal vector and coordinates of a point) is known. Draw a ray from the node coordinates towards the screen and calculate the intersection point of the ray and the glass plane. If the intersection point lies within the glass plane, calculate the angle of incidence at that point: the angle of incidence is equal to the supplementary angle between the ray direction and the glass normal, because the ray travels from the node to the screen, while the actual light ray travels from the screen to the node, in opposite directions. For reflection and scattering, calculate the angle of incidence similarly on metal surfaces and composite material panels.

[0175] B.4 Calculate the energy transfer coefficients of refracted, reflected, and scattered light paths.

[0176] Based on the incident angle and the calibrated medium parameters, the energy transfer coefficients for the three optical paths were calculated. All coefficients are dimensionless real numbers, ranging from 0 to 1.

[0177] (1) Energy transfer coefficient of refracted light path (for glass curtain walls).

[0178] Light enters the glass from the air and then from the glass back into the air. For each interface, the transmittance is calculated using Fresnel's formula. Fresnel's formula decomposes the incident light into S-polarized and P-polarized components; for unpolarized light, the transmittance is taken as the average value. Simplified formula: Transmittance at perpendicular incidence. When incident at an oblique angle, the reflectivity increases with the increase of the incident angle, while the transmittance decreases accordingly.

[0179] This embodiment uses the following approximation: for the angle of incidence (Angle between ray and normal), air refractive index glass refractive index First, calculate the angle of refraction:

[0180]

[0181] Then calculate the S-polarized reflectivity:

[0182]

[0183] P-polarized reflectivity:

[0184]

[0185] Total reflectance transmittance For glass plates, the transmittance at two interfaces (air-glass and glass-air) and the absorption within the glass itself need to be considered. Absorption factor ,in Let be the absorption coefficient of the glass material (a known constant). Where is the glass thickness. The final energy transfer coefficient of the refracted light path:

[0186]

[0187] (2) Energy transfer coefficient of reflected light path (for metal structural parts).

[0188] The Cook-Torrance model is adopted. This model divides reflection into specular reflection and diffuse reflection. For a rough metallic surface, the specular reflection component consists of the product of three factors: the Fresnel term... Micro-element distribution function Geometric attenuation factor .

[0189] Fresnel neck:

[0190]

[0191] in , , and Let be the real and imaginary parts of the complex refractive index of the metal (given constants).

[0192] Micro-element distribution function:

[0193]

[0194] in For roughness.

[0195] Geometric attenuation factor:

[0196]

[0197] in It is half-width. , For the incident and exit angles, Let be the azimuth difference. For simplification, we can approximate it as... .

[0198] Specular reflection coefficient:

[0199]

[0200] in , These are the incident angle and the exit angle. (Diffuse reflection portion) ,in This represents diffuse reflectance (which is typically low). Total reflectance:

[0201]

[0202] (3) Scattered light path energy transfer coefficient (for composite material plate surface).

[0203] The angular distribution of a single scattering is described using the Henyey-Greenstein phase function:

[0204]

[0205] in It is the scattering angle (the angle between the incident direction and the scattering direction). For anisotropy factors.

[0206] For multiple scattering, a transport theory approximation is used. Assume the plate thickness is... The scattering coefficient is Then the total scattering energy transfer coefficient is:

[0207]

[0208] in Take the angle between the incident direction and the sensor direction. Since the sensor is usually directly facing the plate surface, It is approximately equal to the angle of incidence.

[0209] B.5 Construct a multi-media optical flux correlation matrix.

[0210] Divide the ground (or the horizontal plane of interest) of the waiting area into There are [number] blocks. Each block corresponds to a region of the screen, and its perturbation intensity is obtained by downsampling the perturbation intensity distribution field from step A. Each optical acquisition node is considered a receiving point, and there are a total of [number] blocks. Each node.

[0211] For each node and each screen block Calculate from block To the node The total energy transfer coefficient. Since multiple paths may exist, such as refraction followed by reflection, summation is required. However, for simplicity, this embodiment only considers one interaction, i.e., direct access from the screen to the node, passing through only one medium interface. Therefore, the transfer coefficient = geometric attenuation factor × energy transfer coefficient of the corresponding optical path. Geometric attenuation factor This is because light intensity is inversely proportional to the square of the distance.

[0212] In specific calculations, known blocks center coordinates and nodes Calculate the straight-line distance from the coordinates. Then, it is determined whether this straight line intersects with a medium interface. If it intersects with a glass curtain wall, the energy transfer coefficient of the refracted light path is used; if it intersects with a metal structural component, the coefficient of the reflected light path is used; if it intersects with a composite material panel, the coefficient of the scattered light path is used. If it intersects with multiple interfaces, the first intersection point is taken. If there is no intersection point, i.e., a direct line of sight, the transfer coefficient is 0, because this embodiment only cares about the disturbed light after passing through the medium, and the direct light is already covered by the lighting system.

[0213] All nodes and blocks The transmission coefficient is filled in a OK The matrix of columns is called the multi-medium optical flux correlation matrix, denoted as Each element of the matrix Indicates from the first The unit perturbation light intensity emitted by each screen block, after propagation through the medium, reaches its maximum value on the 1st... The luminous flux response generated at each node.

[0214] The principle behind this step is the linear superposition principle, a fundamental law of optics. Since the light propagation process (reflection, refraction, and scattering) in this embodiment is linear under low light intensity, the contributions of each screen block can be calculated independently and then superimposed. (Intent matrix) This is the discretized representation of the linear relationship.

[0215] Step C: Generation of the regional light flux coordinated variation distribution.

[0216] C.1 Convert the disturbance intensity distribution field into an excitation vector.

[0217] The disturbance intensity distribution field obtained from step A is a high-resolution two-dimensional array (pixel-level). To correlate with the correlation matrix... number of columns Matching requires sampling it as The average intensity of each block. Divide the screen into... A rectangular block (for example, if the screen resolution is 1920×1080, We can take 16 × 9 = 144 (each block size is 120 × 120 pixels). For each block, calculate the average perturbation intensity of all pixels within that block to obtain a... 3D column vector This is called the activation vector.

[0218] C.2 Calculate the node response value using matrix multiplication.

[0219] The correlation matrix ( OK (column) and activation vector ( Multiply by ( ), we get 3D response vector:

[0220]

[0221] vector Each element Indicates the first The expected luminous flux (relative value) at each optical acquisition node caused by screen disturbance. Due to The elements already include geometric attenuation and dielectric transfer coefficient. Dimensions and Same (relative intensity).

[0222] C.3 Spatial interpolation generates a continuous distribution field.

[0223] Response vector Only given The values ​​are located at discrete nodes. To obtain the luminous flux at any location within the entire waiting area, spatial interpolation is required. The radial basis function interpolation method is used, and the specific steps are as follows:

[0224] Choose the Gaussian function as the basis function:

[0225]

[0226] in As a smoothing parameter, it is taken as 0.5 times the average node spacing. The average node spacing is obtained by calculating the average distance between all node pairs.

[0227] Constructing interpolation weight vectors This ensures that, at known nodes, the interpolation result equals the response value. That is, solving the system of linear equations:

[0228]

[0229] in It is matrix, .because It is a symmetric positive definite matrix, which can be solved using Cholesky decomposition. .

[0230] For any point to be interpolated Calculate the distance from the point to each node, and then calculate the interpolation result:

[0231]

[0232] The ground surface (XY plane) of the waiting area is divided into a uniform grid with a grid spacing of, for example, 0.2 meters. The interpolation calculation described above is performed on each grid point, resulting in a two-dimensional array called the "regional luminous flux co-variation distribution." This result represents the additional illuminance (relative value) at each location on the waiting area ground caused by screen disturbances. This result will be used in subsequent steps to compensate for the lighting system.

[0233] Step D: Calculation of changes in optical parameters of external light sources for the aircraft.

[0234] D.1 Signal acquisition from the boarding gate sensor array.

[0235] When the aircraft is docked at the bridge, external light sources on the aircraft, such as landing lights, illuminate and move with the aircraft. The central controller synchronously reads the outputs of the three gate photosensors at a sampling rate of 20,000 times per second. Each sensor outputs a voltage signal that varies with time, which is converted from analog to digital to obtain the incident light intensity timing signal. The controller stores these signals in a circular buffer with a length equal to the most recent second of data.

[0236] Determining whether to dock: The central controller continuously monitors the average signal values ​​of three sensors. If the average signal value of any sensor exceeds a preset threshold (e.g., twice the average ambient light value), it determines that the aircraft has begun docking operations and initiates step D and subsequent feedforward control; otherwise, step D is skipped, the feedforward disturbance input is set to a zero vector, and only feedback control is used.

[0237] D.2 Calculate the rate of change of angle.

[0238] For each sensor signal, a peak detection algorithm is used to find the moment when the signal strength is highest. Since the aircraft's light source sweeps across the three sensors sequentially during its movement, there is a time difference between the peak times of the three signals. Let the peak times be... (In order of sensors from left to right). Calculate the time difference. , Due to the sensor spacing Given that the beam movement speed can be calculated:

[0239]

[0240] Assume the distance between the light source and the sensor array is (This value is a constant and can be obtained from the geometric measurements of the boarding bridge), then the rate of change of angle is:

[0241]

[0242] in The sampling period is the time interval between two consecutive calculations. More precisely, if the direction angles obtained from two consecutive calculations are... and ,but The rate of change of angle is measured in degrees per second or radians per second. Typical range: during the approach phase, the rate of change of angle gradually increases from 0 to approximately 5° / s, peaking at 10° / s during the docking phase, and approaching 0° / s during the stabilization phase. It reflects the horizontal rotational angular velocity of the aircraft's external light source relative to the boarding gate.

[0243] D.3 Spectrum analysis extracts frequency offset and interference bandwidth intensity.

[0244] Select the incident light intensity time-series signal from the intermediate sensor (second sensor) and extract the most recent time window (e.g., 0.1 seconds). Perform a Fast Fourier Transform on this window signal to obtain the power spectral density curve. Find the frequency corresponding to the peak power in the power spectrum and denote it as the center frequency. Query the pre-stored inherent modulation frequency of the aircraft's light source. (This may vary depending on the aircraft, but a typical value can be used, such as 400Hz). Frequency offset:

[0245]

[0246] The unit is Hertz. The magnitude of the frequency offset is proportional to the radial velocity of the light source relative to the sensor and can be used as feedforward information.

[0247] On the power spectrum, find the two frequency points corresponding to when the power drops to half of the peak power, calculate their difference, and obtain the half-power bandwidth. The unit is Hertz (Hz). A wider bandwidth indicates more severe spectral perturbations or a faster change in the speed of motion of the light source. This is called the interference bandwidth strength.

[0248] D.4 is a combination of optical parameter variation vectors.

[0249] Rate of change of angle Frequency offset Interference bandwidth strength Combined into a three-dimensional vector:

[0250]

[0251] This vector changes over time, updating every millisecond, and reflects the current dynamic characteristics of the aircraft's external light source.

[0252] Step E: Determining the stable control relationship for optical interference.

[0253] E.1 Calculate the reference illumination value.

[0254] Let the target illuminance distribution in the waiting area be... This distribution can be set according to the regional function, for example, 300 lux near the boarding gate, 200 lux in the center of the waiting area, and 150 lux in the corridor. The regional luminous flux coordinated variation distribution obtained from step C is as follows: This represents the additional illuminance caused by screen disturbance. To counteract screen disturbance, the illuminance output by the lighting system should be the target value minus the additional illuminance caused by screen disturbance, i.e.:

[0255]

[0256] Notice, Negative values ​​may appear in some locations, indicating that the screen disturbance has exceeded the target value. In this case, the lighting system should be completely turned off, and... Clamp to zero.

[0257] E.2 Extract feedforward disturbance input.

[0258] The optical parameter change vector obtained from step D In the middle, extract the rate of change of angle. The derivative of the interference bandwidth strength with respect to time. The derivative of the interference bandwidth strength with respect to time is denoted as... Calculated through numerical difference:

[0259]

[0260] in The sampling interval is [specified]. and Composition of the feedforward perturbation input vector:

[0261]

[0262] choose and The rationale for feedforward input: It directly reflects the angular velocity of the external light source and can predict the area that the light spot will sweep. It reflects the changing trend of the light source disturbance intensity and can predict the increase or decrease of interference energy.

[0263] E.3 Calculate the feedback error.

[0264] The current total illuminance distribution is collected in real time through a network of illuminance sensors deployed in the waiting area. Since the number of sensors is limited (e.g., a few dozen), spatial interpolation is still required to obtain a continuous distribution. Using the same radial basis function interpolation method as in step C.3, the discrete illuminance sensor measurements are interpolated into a continuous distribution. .

[0265] Feedback error is defined as the difference between the reference illuminance and the measured total illuminance:

[0266]

[0267] Notice, This includes the sum of screen disturbances, external light source interference, and the output of the lighting system itself. Therefore, The sign of indicates the deviation between the current output and the desired output of the lighting system: if A positive value indicates insufficient actual lighting, requiring increased lighting output; if... A negative value indicates excessive light, and the lighting output needs to be reduced.

[0268] E.4 Weighted superposition generates control relationships.

[0269] The feedforward disturbance input and feedback error are weighted and superimposed to obtain the final control quantity distribution. Using a linear weighted form:

[0270]

[0271] in It is The feedforward gain matrix (i.e., the two coefficients). It is a scalar feedback gain. and Obtained through offline system identification or online adaptive tuning. Typically, The two elements correspond to the gains of the rate of change of angle and the rate of change of bandwidth, respectively, with values ​​ranging from 0.1 to 10; The value ranges from 0.01 to 1.

[0272] This relationship is the optical interference stability control relationship. Its physical meaning is: the feedforward section adjusts the illumination in advance based on the motion trend of the aircraft's external light source, while the feedback section corrects for actual measurement deviations. The combination of these two ensures both rapid response and steady-state zero steady-state error.

[0273] Will As a control output, it is used for the next step of scheduling the lighting units. The unit is the same as illuminance (lux), indicating the location. The lighting system needs to increase (positive) or decrease (negative) the luminous flux.

[0274] Step F: Lighting unit scheduling.

[0275] F.1 Calculate the deflection angle of the illumination direction based on the spatial error distribution.

[0276] The lighting unit has a total of Each lighting unit The coordinates are ,in The installation height is typically greater than 3 meters. Its initial illumination direction is vertically downwards. This step requires calculating the horizontal and vertical angles that each lighting unit should deflect to align its beam center with the control quantity. The region with the largest mean square error.

[0277] First, regarding the control quantity Calculate the spatial gradient. Discretize into a grid with a grid spacing of 0.2 meters. For each grid point, use central difference:

[0278]

[0279] Gradient direction angle:

[0280] Gradient magnitude:

[0281]

[0282] Gradient pointing Increase the light in the direction that needs the most light, i.e., the direction that needs the most supplemental lighting.

[0283] For each lighting unit , with its projected coordinates Choose a radius centered on For example, a circular area of ​​5 meters, calculate the area within that region. The average gradient direction. Specifically, the average gradient vector is obtained by averaging the gradient vectors at the grid points within the circular region. .

[0284] Horizontal deflection angle:

[0285]

[0286] That is, the angle between the projection of the gradient direction onto the horizontal plane and the X-axis. Pitch angle:

[0287]

[0288] in Let be the magnitude of the gradient vector. This refers to the installation height of the light fixture. The pitch angle indicates the angle at which the light fixture needs to be tilted downwards. The larger the gradient, the further away from the center the area needs supplemental lighting, and the larger the pitch angle.

[0289] To prevent frequent jitter in the stepper motor, a low-pass filter is applied to the angle:

[0290]

[0291] The value is set to 0.3. Finally, the target horizontal angle and pitch angle are packaged into the first control command and sent to the stepper motor driver of the corresponding lighting unit via the bus.

[0292] F.2 Adjust the beam diffusion angle according to the deflection angle.

[0293] When the illumination direction changes, the shape and coverage area of ​​the light spot will change. If the original beam diffusion angle remains unchanged, the edge of the light spot may become too concentrated or too dispersed. Therefore, it is necessary to adjust the diffusion angle to make the coverage area of ​​the light spot more uniform. Distribution matching.

[0294] First, establish the light spot model of the illumination unit. For a given diffusion angle... (Defined as the angle from the center of the beam to the half-peak intensity), at a distance of On the plane, the radius of the light spot In practice, since the light distribution curve of the luminaire is approximately Gaussian, the illuminance within the light spot decreases with radial distance.

[0295] For lighting units In the direction of deflection Then, the center of its light spot will fall on point:

[0296]

[0297] Calculate the area covered by the light spot (in terms of...) Centered on, radius (The circle). Calculate the control quantity within this area. Local non-uniformity:

[0298]

[0299] in and They are within the region The maximum and minimum values ​​(avoid division by zero, if) (Then set it to a small positive number). Here, a control variable is used. Rather than the measured illuminance, because the diffusion angle adjustment should be based on the desired control target.

[0300] The target non-uniformity is set to 1.2. If the current non-uniformity is greater than 1.2, the spot size is too narrow, and the diffusion angle needs to be increased; if it is less than 1.1, the spot size is too wide, and the diffusion angle can be decreased. Adjustment amount:

[0301]

[0302] in This is a scaling factor (e.g., 5 degrees). The new diffusion angle... It is limited to between the minimum diffusion angle (10 degrees) and the maximum diffusion angle (60 degrees).

[0303] A second control command is generated, containing the illumination unit identifier and the target diffusion angle, and sent to the electric motor of the zoom mechanism.

[0304] F.3 Calculate the target luminous flux adjustment.

[0305] Once the direction and diffusion angle are determined, the output luminous flux of each lighting unit needs to be adjusted so that the actual superimposed illuminance distribution is as close as possible to the control value. This is a typical inverse problem: given the position, orientation, diffusion angle of each lighting unit and the mapping relationship between the output luminous flux and the ground illuminance, find the output luminous flux that makes the total illuminance equal to the desired value.

[0306] Pre-establish the illumination contribution matrix of the lighting units. Discretize the ground of the waiting area into... Each sampling point, for example, with a grid spacing of 0.5 meters, Approximately several thousand. For each lighting unit At standard output luminous flux (e.g., at 1000 lumens) measure or calculate its value at each sampling point. Illuminance contribution generated above This can be obtained through measured light distribution curves or optical simulation. A Lambertian (cosine radiator) is an ideal diffuser whose emitted radiation intensity is proportional to the cosine of the observation direction relative to the normal. In this embodiment, the light distribution curve of the illumination unit is approximated as a Lambertian, with the approximate formula:

[0307]

[0308] in Sampling points The directional angle relative to the principal optical axis of the luminaire, For distance, The angle between the sampling point normal and the incident ray (usually the ground normal is perpendicular upwards, therefore...). (Equal to the zenith angle). When the beam spread angle When adjustable, multiply by the diffusion angle correction factor. In a dark room, the lighting units are fixed at a certain height, and different diffusion angles are set for each unit. Measure the illuminance at the center point of the ground directly below. With minimum diffusion angle Based on the illuminance below, define

[0309] So, when the lighting unit The actual output luminous flux is At that time, it was at point The contributions made are as follows:

[0310]

[0311] All lighting units at point The total illuminance contribution above is:

[0312]

[0313] We hope that this total illuminance equals the control amount. At point The value on (note) It's an increment, but here it's directly used as the target because the baseline reference value already accounts for screen disturbances and external interference. Therefore, we obtain the linear equation system:

[0314]

[0315] in yes The matrix, ; yes A dimensional vector (the output luminous flux of each illumination unit to be determined); yes Dimensional vector (control quantity in) (Values ​​at each sampling point).

[0316] because Usually greater than The system of equations is overdetermined and has no exact solution. The least squares method is used to solve it.

[0317]

[0318] in yes The matrix is ​​invertible (provided the number of lighting units is sufficient and their layout is reasonable). The calculated value is... This refers to the luminous flux required to output for each lighting unit. Since the output luminous flux cannot be negative, negative values ​​are clamped to zero.

[0319] For each lighting unit, the target luminous flux The pulse width modulation duty cycle is converted to the driving circuit. The duty cycle is linearly related to the luminous flux (within the rated range) and is calculated using pre-calibrated conversion coefficients. A third control command is generated and sent to the driving circuit.

[0320] Step G: Stage-adaptive feedforward compensation.

[0321] G.1 Obtain the curve of the rate of change of angle over time.

[0322] Throughout the entire process of the aircraft docking operation, triggered by the docking determination condition in step D.1, the controller continuously records the rate of angle change calculated in step D. And plot the continuous data points on the horizontal axis with time as the horizontal axis. Plot a curve on the vertical axis. Due to the high sampling rate, the curve is approximately continuous.

[0323] G.2 Determine the current stage of the aircraft docking operation.

[0324] The controller internally stores three typical angle change rate curve templates, which were obtained through statistical analysis of a large amount of actual bridge-side operation data:

[0325] Approaching Phase Template: Starting from 0, the curve rises monotonically with an increasing slope. This corresponds to an aircraft moving from a distance towards the gate, with its angular velocity increasing rapidly. Typical... Range 0~5° / s.

[0326] Template for docking phase: The aircraft first ascends rapidly to its peak speed (up to 10° / s), then descends rapidly, forming a sharp peak in the curve. This corresponds to the aircraft decelerating and adjusting its attitude before finally coming to a stop.

[0327] Dock stabilization phase template: It fluctuates slightly around 0, with a very small root mean square value (<0.5° / s). This corresponds to the aircraft coming to a complete stop, the engines being off, and the external light source remaining essentially stationary.

[0328] The controller calculates the current time period in real time, such as the last 5 seconds. The cross-correlation coefficients between the curve and the three templates are used. The stage corresponding to the template with the highest correlation coefficient is selected as the current stage. To improve robustness, proximity sensor signals from the aircraft (such as boarding bridge position switches) can also be used for voting.

[0329] G.3 Matches the corresponding feedforward compensation coefficient.

[0330] The control parameter library pre-stores a feedforward compensation coefficient matrix for each stage. The size of this matrix is ​​the same as the illumination contribution matrix in step F.3. The number of rows is the same, that is, the number of discrete sampling points. The number of columns is 2, corresponding to and Two feedforward inputs. The element values ​​of the matrix are optimized through offline simulation or field experiments: at different stages, a unit feedforward input is applied, the actual illumination response is measured, and then the optimal compensation coefficient is identified through a least-squares system.

[0331] For example, during the approach phase, due to the high speed of the aircraft, a larger feedforward gain is required. The element values ​​are relatively large; in the steady phase, the feedforward gain can be very small or even zero, mainly relying on feedback.

[0332] G.4 Generate illumination compensation.

[0333] The stage compensation coefficient matrix With the current feedforward input vector Combined, the illumination compensation amount is generated. This embodiment uses a spatial point-by-point weighting method: for each spatial location... The illumination compensation is:

[0334]

[0335] in:

[0336] It is The row vectors from the compensation coefficient matrix Extract from the corresponding position Two feedforward channels (angle change rate) and bandwidth change rate The compensation coefficient;

[0337] It is the current feedforward input vector.

[0338] This formula states that at each spatial location, the illumination compensation is equal to the dot product of the row vector of the feedforward compensation coefficient and the feedforward input vector at that location. The compensation amounts at different spatial locations are calculated independently, without neighborhood coupling or sliding window operations.

[0339] Compensation coefficient matrix Each row corresponds to a discrete sampling point (one-to-one with the ground sampling point in step F.3). In continuous space, any position... compensation coefficient The compensation coefficients of the discrete sampling points can be obtained through the radial basis function interpolation method described in step C.3. Because The parameters are pre-stored in the control parameter library, and can be directly looked up in the table or quickly interpolated during actual control.

[0340] Calculated This is the final amount of illumination compensation.

[0341] G.5 is superimposed on the optical interference stability control relationship.

[0342] Add the illumination compensation amount to the control value obtained in step E.4. superior:

[0343]

[0344] Then use replace Perform lighting scheduling in step F.

[0345] V. Overall System Operation Flow.

[0346] The central controller executes the following tasks cyclically according to a fixed control cycle (e.g., 0.1 seconds):

[0347] 1. Trigger the flight display screen camera to capture a new image, execute step A, and update the flight display spectral perturbation propagation results.

[0348] 2. Read sensor data from all optical acquisition nodes and execute step B.1 to update the multi-source optical signal set. Perform the medium parameter calibration in step B.2 every ten cycles, i.e., every second, because the medium parameters change slowly.

[0349] 3. Perform steps B.3 to B.5 to calculate the multi-medium optical flux correlation matrix. If the medium parameters have not been updated, the matrix from the previous period can be reused.

[0350] 4. Perform step C to downsample the disturbance intensity distribution field into an excitation vector, multiply it with the correlation matrix and interpolate it to generate the regional luminous flux cooperative variation distribution.

[0351] 5. Read the data from the boarding gate sensor array and proceed to step D.1 to determine if the gate is docked:

[0352] If the bridge is in use, proceed to steps D.2 to D.4 to calculate the changes in optical parameters and update the angle change rate curve; then proceed to step G to determine the current bridge-in stage, match the compensation coefficient, and calculate the illumination compensation amount.

[0353] If the bridge is not in use, set the feedforward disturbance input to a zero vector and the compensation amount to zero.

[0354] 6. Read the illuminance sensor network data, interpolate to obtain the measured illuminance distribution, execute step E, calculate the reference value, feedback error, and feedforward input, generate the light interference stability control relationship, and superimpose the stage compensation amount (if non-zero).

[0355] 7. Execute step F: For each lighting unit, calculate the deflection angle, diffusion angle adjustment, and target luminous flux, and generate three control commands.

[0356] 8. Control commands are sent in parallel to the stepper motors, zoom mechanisms, and drive circuits of each lighting unit.

[0357] 9. Wait for the next control cycle to begin.

[0358] The foregoing has shown and described the basic principles, main features, and advantages of this application. Those skilled in the art should understand that this application is not limited to the above embodiments. The embodiments and descriptions in the specification are merely illustrative of the principles of this application. Various changes and modifications can be made to this application without departing from the spirit and scope thereof, and all such changes and modifications fall within the scope of this application as claimed. The scope of protection of this application is defined by the appended claims and their equivalents.

Claims

1. A method for controlling indoor lighting in an airport, characterized in that, The method includes: The dynamic display screen of the flight display device is acquired, and the continuous frame images in the display screen are subjected to spectral decomposition and inter-frame difference. The intensity, spatial propagation direction and rate of change of the spectral disturbance are quantitatively extracted to generate the flight display spectral disturbance propagation result. The propagation result of the spectral disturbance of the flight display is used as the original light disturbance source of the screen. The light signal transmission path after reflection, refraction and secondary scattering of the screen spectral disturbance light through the glass curtain wall, metal structural parts and composite material plate in the waiting area is collected. Based on the propagation results of the spectral disturbance of the flight display and combined with the optical signal transmission path, the correlation of light energy flux at each medium interface is determined; based on the linkage between the correlation and the disturbance propagation results, a regional light flux coordinated change distribution is generated. When the aircraft is docked at the bridge, the incident light signal of the external light source of the aircraft is collected, the changes in optical parameters of the incident light signal caused by the movement of the aircraft are calculated, and the stable control relationship of light interference is determined by combining the coordinated change distribution of light flux in the region. Based on the aforementioned light interference stability control relationship, the output luminous flux, illumination direction, and beam diffusion angle of multiple lighting units in the waiting area are scheduled.

2. The method according to claim 1, characterized in that, The quantitative extraction of the intensity, spatial propagation direction, and rate of change of the spectral perturbation generates the propagation results of the spectral perturbation for flight visibility, including: Gradient calculation is performed on the spectral difference maps of consecutive frames to obtain the perturbation intensity distribution field; The optical flow vector field is solved by the disturbance intensity distribution field to obtain the disturbance motion vector field; The spatial propagation direction field and the rate of change field are decomposed from the disturbed motion vector field; The disturbance intensity distribution field, spatial propagation direction field, and rate of change field are combined to generate the flight display spectral disturbance propagation results.

3. The method according to claim 2, characterized in that, The determination of the optical energy flux correlation between each medium interface based on the propagation results of the spectral disturbance of the flight display, combined with the optical signal transmission path, includes: The initial refractive index and initial transmittance of the glass curtain wall, the initial reflectivity and initial roughness of the metal structural components, and the initial scattering coefficient and initial anisotropy factor of the composite material panel were obtained. Using a multi-source optical signal set, the initial refractive index, initial transmittance, initial reflectance, initial roughness, initial scattering coefficient, and initial anisotropy factor are corrected to obtain the calibrated refractive index, transmittance, reflectance, roughness, scattering coefficient, and anisotropy factor; based on the spatial propagation direction field in the propagation results of the flight display spectral disturbance, the incident angle distribution of each medium interface is calculated; Based on the incident angle distribution and the calibrated refractive index, reflectivity, and scattering coefficient, the energy transfer coefficients of the refracted optical path, the reflected optical path, and the scattered optical path are calculated respectively. The energy transfer coefficients of each optical path are superimposed according to their spatial location to form a multi-medium optical flux correlation matrix as the correlation relationship.

4. The method according to claim 3, characterized in that, The calculation of the optical parameter changes of the incident light signal caused by aircraft movement, combined with the regional luminous flux variation distribution, includes: The perturbation intensity distribution field in the propagation results of the flight display spectral perturbation is used as the excitation input; The optical flux correlation matrix of the multi-media optical energy transmission is multiplied with the excitation input to obtain the optical flux response value of each optical acquisition node. Spatial interpolation is performed on the light flux response value to generate a light flux distribution field covering the waiting area; The light flux distribution field is output as the regional light flux coordinated change distribution.

5. The method according to claim 1, characterized in that, The calculation of the optical parameter changes of the incident light signal caused by the aircraft's movement includes: Acquire the incident light intensity timing signal collected by at least three photosensitive sensors located at the boarding gate; Calculate the peak time difference between the incident light intensity time-series signals corresponding to different sensors, and calculate the angular change rate of the incident light signal based on the peak time difference and the preset sensor spacing; Spectral analysis is performed on the incident light intensity time-series signal to extract the frequency offset and interference bandwidth intensity; The angle change rate, the frequency offset, and the interference bandwidth intensity are combined as optical parameter variations.

6. The method according to claim 1, characterized in that, The determination of the stable control relationship for optical interference by combining the coordinated change distribution of the regional luminous flux includes: The luminous flux distribution field in the coordinated luminous flux variation distribution of the region is used as the reference illumination value; the rate of change of angle and the rate of change of interference intensity in the optical parameter variation are used as feedforward perturbation inputs; The illuminance in the waiting area is obtained, the difference between the reference illuminance value and the illuminance is calculated, and the difference is used as the feedback error. The feedforward disturbance input and the feedback error are weighted and superimposed to generate an optical interference stability control relationship.

7. The method according to claim 1, characterized in that, The step of scheduling the output luminous flux, illumination direction, and beam spread angle of multiple lighting units in the waiting area according to the aforementioned light interference stability control relationship includes: Based on the spatial error distribution in the light interference stability control relationship, the illumination direction deflection angle of each lighting unit is calculated, and a first control command including the illumination direction deflection angle is generated. The first control command is then sent to the stepper motor of the corresponding lighting unit. Based on the deflection angle of the illumination direction, the local non-uniformity in the light interference stability control relationship is corrected to obtain the corrected local non-uniformity. Based on the corrected local non-uniformity, the beam diffusion angle adjustment value of each illumination unit is calculated, and a second control command including the beam diffusion angle adjustment value is generated. The second control command is sent to the zoom mechanism of the corresponding illumination unit. Based on the irradiation direction deflection angle and the beam diffusion angle adjustment value, the reference luminous flux in the light interference stability control relationship is compensated and calculated. The target luminous flux adjustment amount of each lighting unit is analyzed, a third control command including the target luminous flux adjustment amount is generated, and the third control command is sent to the driving circuit of the corresponding lighting unit.

8. The method according to claim 1, characterized in that, The acquisition of the light signal transmission path after reflection, refraction, and secondary scattering by the screen spectral perturbation light through the glass curtain wall, metal structural components, and composite material panels in the waiting area includes: The signal data output by optical acquisition nodes set at multiple spatial nodes in the waiting area is acquired. The signal data of each optical acquisition node includes refracted light signal from a first sensor, reflected light signal from a second sensor, and secondary scattered light signal from a third sensor. The first sensor is set towards the glass curtain wall, the second sensor is set towards the metal structure, and the third sensor is set towards the composite material panel. The refracted light signal, the reflected light signal, and the secondary scattered light signal at the same node are time-aligned to form a multipath light signal group for the node; The multipath optical signal groups of all nodes are aggregated into a multisource optical signal set for the waiting area; Based on the multi-source optical signal set and the propagation results of the spectral disturbance of the flight display, combined with the multi-path geometric relationship, an optical signal transmission path is generated.

9. The method according to claim 6, characterized in that, The method further includes: Obtain the curve of the rate of change of the angle over time in the changes of the optical parameters; Based on the curve of the angle change rate over time, determine the current stage of the aircraft docking operation; Based on the current stage, the corresponding feedforward compensation coefficient is matched from the pre-stored control parameter library; The feedforward compensation coefficient is spatially weighted and calculated point-by-point with the luminous flux distribution field in the regional luminous flux cooperative variation distribution to generate a spatially adaptive illumination compensation amount. The illumination compensation amount is superimposed on the light interference stability control relationship.

10. An airport indoor lighting control system, characterized in that, The system includes: The flight display spectral disturbance analysis module is used to acquire the dynamic display screen of the flight display device, perform spectral decomposition and inter-frame difference on the continuous frame images in the display screen, quantitatively extract the intensity, spatial propagation direction and change rate of the spectral disturbance, and generate the flight display spectral disturbance propagation results. The optical signal transmission path acquisition module is used to take the propagation result of the flight display spectral disturbance as the original optical disturbance source of the screen, and to acquire the optical signal transmission path after the screen spectral disturbance light is reflected, refracted and secondary scattered by the glass curtain wall, metal structure and composite material plate in the waiting area. The regional luminous flux coordinated distribution generation module is used to determine the correlation of luminous flux at each medium interface based on the propagation results of the spectral disturbance of the flight display and the optical signal transmission path; and to generate a regional luminous flux coordinated change distribution based on the linkage between the correlation and the disturbance propagation results. The optical interference stability control relationship determination module is used to collect the incident light signal of the external light source of the aircraft when the aircraft is docked at the bridge, calculate the changes in optical parameters of the incident light signal caused by the movement of the aircraft, and determine the optical interference stability control relationship by combining the coordinated change distribution of the light flux in the region. The lighting unit scheduling module is used to schedule the output luminous flux, illumination direction and beam diffusion angle of multiple lighting units in the waiting area according to the light interference stability control relationship.

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