Ground-based evaluation method for fire point detection performance of spaceborne infrared instrument

Abstract

This disclosure relates to a ground-based evaluation method, ground testing system, equipment, and medium for the fire detection performance of a spaceborne infrared instrument. The method includes: acquiring scene parameters of the actual scenario to be evaluated; setting up a simulated evaluation scenario using a radiation energy transfer model based on atmospheric attenuation; performing fire detection based on the simulated evaluation scenario and acquiring multiple image output values ​​using the spaceborne infrared instrument; calculating an energy multiple for each image output value based on the image output value and calibration parameters; and comparing each calculated energy multiple with a multiple threshold to generate an evaluation result of the spaceborne infrared instrument's fire detection performance for the actual scenario to be evaluated. According to the technical solution of this disclosure, the detection capability of a spaceborne infrared instrument under different backgrounds, atmospheric conditions, and fire conditions of different sizes and temperatures can be repeatedly and systematically evaluated on the ground.

Description

Technical Field

[0001] This disclosure relates to the fields of remote sensing and power system safety monitoring technology, and in particular to a ground evaluation method, ground testing system, equipment and medium for fire detection performance of a spaceborne infrared instrument. Background Technology

[0002] When power transmission lines and their corridors traverse mountainous areas overgrown with weeds, they may be affected by human activities or meteorological conditions such as drought and high temperatures, triggering small-scale wildfires, which in turn cause line tripping and large-scale power outages. Existing spaceborne infrared instruments have low resolution, with the highest meteorological infrared satellite NPP only reaching 375 meters, making it difficult to detect fires at the 10-meter level (10m×10m). There is an urgent need to develop spaceborne infrared instruments specifically designed for detecting small-scale wildfires.

[0003] However, the development of existing spaceborne infrared instruments lacks specialized testing methods for fire characteristics, making it difficult to accurately assess their detection capabilities for different fire areas and temperatures, and consequently, to determine their applicability in power grid wildfire monitoring. Therefore, there is an urgent need to develop a systematic evaluation method and supporting testing system for verifying the detection performance of spaceborne infrared instruments in small-scale power grid wildfire scenarios, in order to support the development of spaceborne infrared instruments suitable for small-scale power grid wildfires. Summary of the Invention

[0004] To address the aforementioned technical issues, this disclosure provides a ground-based evaluation method, ground testing system, equipment, and medium for the fire detection performance of spaceborne infrared instruments.

[0005] In a first aspect, embodiments of this disclosure provide a ground-based evaluation method for the fire detection performance of a spaceborne infrared instrument, including: Obtain the scene parameters of the actual scenario to be evaluated; the scene parameters include the actual fire point size, the spatial resolution of the spaceborne infrared instrument, the orbital altitude, and the wave value; A radiative energy transfer model based on atmospheric attenuation is used to determine a first expression corresponding to the orbital altitude and the wave value; Solve the first expression with distance as the unknown to obtain the simulated detection range of the spaceborne infrared instrument; Based on the simulated detection distance, the spatial resolution of the spaceborne infrared instrument, and the actual fire point size, the simulated fire point size is determined to achieve the simulation evaluation scenario setting; Fire point detection is performed based on the simulated evaluation scenario, and multiple image output values ​​are acquired through the spaceborne infrared instrument. Obtain the pre-calibrated calibration parameters of the spaceborne infrared instrument; the calibration parameters include calibration coefficients and spaceborne infrared instrument noise. For each image output value, the radiation energy of each pixel of the spaceborne infrared instrument and the noise equivalent energy of the spaceborne infrared instrument are determined according to the image output value and the calibration parameters. The energy multiple is calculated by the ratio of the difference in radiation energy between each pixel of the spaceborne infrared instrument and the surrounding background to the noise equivalent energy. Each calculated energy multiplier is compared with a multiplier threshold to generate a fire detection performance evaluation result of the spaceborne infrared instrument for the actual scenario to be evaluated.

[0006] Secondly, embodiments of this disclosure provide a ground testing system, including: Blackbody calibration device, controllable fire source device, thermal imager, rangefinder, three-dimensional rotation device, temperature and humidity detection device, data acquisition and synchronization unit, radiation transfer model calculation unit and evaluation algorithm processing unit.

[0007] Thirdly, embodiments of this disclosure provide an electronic device, including: a processor; a memory for storing executable instructions of the processor; the processor being configured to read the executable instructions from the memory and execute the instructions to implement the ground evaluation method for fire detection performance of spaceborne infrared instruments as described in the first aspect.

[0008] Fourthly, embodiments of this disclosure provide a computer-readable storage medium storing a computer program that, when executed by a processor, implements the ground evaluation method for fire detection performance of a spaceborne infrared instrument as described in the first aspect.

[0009] Compared with the prior art, the technical solution provided in this disclosure has the following advantages: it enables ground assessment of small-scale wildfires in power grids, quantitatively analyzes the detection accuracy of small-scale wildfires by spaceborne infrared instruments, and can repeatedly and systematically evaluate the detection capability of spaceborne infrared instruments under different backgrounds, atmospheric conditions, and fire point conditions of different sizes and temperatures on the ground. It can provide quantitative basis for on-orbit threshold setting, algorithm screening, and instrument parameter optimization, and reduce the risk of missed detections on orbit. Attached Figure Description

[0010] The accompanying drawings, which are incorporated in and form a part of this specification, illustrate embodiments consistent with this disclosure and, together with the description, serve to explain the principles of this disclosure.

[0011] To more clearly illustrate the technical solutions in the embodiments of this disclosure or the prior art, the accompanying drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, for those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0012] Figure 1 A schematic flowchart illustrating a ground-based evaluation method for the fire detection performance of a spaceborne infrared instrument provided in an embodiment of this disclosure; Figure 2 This is a schematic diagram of an outdoor fire detection test provided in an embodiment of the present disclosure; Figure 3 This is a comparative schematic diagram of an atmospheric radiation attenuation model provided in an embodiment of this disclosure; Figure 4 This is a schematic diagram of laboratory radiation calibration provided in an embodiment of the present disclosure; Figure 5 This is a schematic diagram of a measurement response result provided in an embodiment of the present disclosure; Figure 6 This is a schematic diagram of the absolute calibration coefficients and fitting results of a mid-wavelength wave provided in an embodiment of this disclosure; Figure 7 A schematic diagram of the noise equivalent energy of a fire pixel provided in an embodiment of this disclosure; Figure 8 This is a schematic diagram illustrating the ratio of signal energy to equivalent noise energy of a spaceborne infrared instrument provided in an embodiment of this disclosure. Detailed Implementation

[0013] To better understand the above-mentioned objectives, features, and advantages of this disclosure, the solutions disclosed herein will be further described below. It should be noted that, unless otherwise specified, the embodiments and features described herein can be combined with each other.

[0014] Numerous specific details are set forth in the following description in order to provide a full understanding of this disclosure, but this disclosure may also be implemented in other ways different from those described herein; obviously, the embodiments in the specification are only some, and not all, of the embodiments of this disclosure.

[0015] Figure 1 This is a flowchart illustrating a ground-based evaluation method for the fire detection performance of a spaceborne infrared instrument provided in an embodiment of this disclosure. The method provided in this embodiment can be executed by a ground-based evaluation device for the fire detection performance of a spaceborne infrared instrument. This device can be implemented using software and / or hardware and can be integrated into any electronic device with computing capabilities.

[0016] like Figure 1 As shown, the ground-based evaluation method for the fire detection performance of spaceborne infrared instruments provided in this disclosure embodiment may include: Step 101: Obtain the scene parameters of the actual scene to be evaluated.

[0017] The method of this disclosure is used to quantitatively evaluate the fire detection performance of a spaceborne infrared instrument in a real-world scenario to be evaluated. For evaluation requirements of different real-world scenarios, the ground evaluation method provided in this disclosure can be used to set up corresponding simulated evaluation scenarios and perform quantitative evaluation.

[0018] In this embodiment, the scene parameters of the actual scenario to be evaluated include the actual fire point size, the spatial resolution of the spaceborne infrared instrument, the orbital altitude, the wave value, and the actual fire point temperature. For example, if it is necessary to evaluate the detection performance of a spaceborne infrared instrument with a spatial resolution of 60 meters at an altitude of 500 kilometers for a 10-meter-level fire point, then the scene parameters would be a spatial resolution of 60 meters, an orbital altitude of 500 kilometers, an actual fire point size of 10m×10m, and an actual fire point temperature of 400℃.

[0019] Step 102: Set up the simulated evaluation scenario corresponding to the actual scenario to be evaluated.

[0020] In this embodiment, the simulated evaluation scenario is used to simulate the actual detection scenario at the corresponding orbital altitude on the ground. The scenario parameters of the simulated evaluation scenario are calculated and processed according to the scenario parameters of the actual scenario to be evaluated in order to realize the setting of the simulated evaluation scenario.

[0021] Among them, a radiation energy transfer model based on atmospheric attenuation is adopted to determine the first expression corresponding to the orbital altitude and wave value. Then, the first expression is solved with distance as the unknown quantity to obtain the simulated detection range of the spaceborne infrared instrument. Based on the simulated detection range, orbital altitude, and actual fire point size, the simulated fire point size is determined to realize the simulation evaluation scenario setting.

[0022] Optionally, a radiation energy transfer model based on atmospheric attenuation is used to extrapolate the radiation energy from the target point at the fire point location to the entrance pupil of the spaceborne infrared instrument, as shown in the following formula:

[0023] in, It is the radiated energy of the wave value λ after passing through path H (the energy in front of the lens of the infrared instrument). It is the radiated energy at the target point of the wave value λ. Atmospheric transmittance with wave value λ Let T(s) be the spectral brightness of the blackbody corresponding to the target temperature T at position s, where T(s) is the target temperature at position s. λ is the absorption coefficient, representing the absorption capacity of the wave value λ at position s.

[0024] A radiation energy transfer model based on atmospheric attenuation is used to determine the first expression corresponding to the orbital altitude and wave value. This includes: given the scene parameters of the actual scene to be evaluated, the first atmospheric transmittance of the wave value can be calculated based on the orbital altitude, and the first radiation energy of the fire point with assumed temperature and size at the wave value is calculated. The first atmospheric transmittance and the first radiation energy are then substituted into the radiation energy transfer model based on atmospheric attenuation to determine the first expression.

[0025] As an example, given a fire point of 400℃, 10m×10m, H=500km, and wave value λ, the first atmospheric transmittance can be determined. And calculate the first radiated energy Substitute the above formula and solve for H as the unknown distance to obtain the simulated detection distance h as the ground test distance, for example, h is 3 kilometers.

[0026] In this example, the radiation energy transfer model and the pixel mixing model are used to extrapolate the target radiation energy and the radiation energy in front of the lens of the spaceborne infrared instrument from the observation data. The first radiation energy is calculated using the pixel mixing model f(L1), where the pixel mixing model can be a linear model, as shown in the following formula: =f(L1)=N×L1+(1-N)×L2, where f(L1) represents the radiation energy of the pixel containing the target of the spaceborne infrared instrument, L1 represents the radiation energy of the target within the pixel, L2 represents the background radiation energy within the pixel, and N represents the ratio of the target burning area to the area of ​​this pixel. For the scene parameters of the actual scenario to be evaluated, such as the known orbital altitude, actual fire point size, and actual fire point temperature, combined with the instrument parameters such as the spatial resolution of the spaceborne infrared instrument, L1, L2, and N can be determined.

[0027] It should be noted that the pixel mixing model can also use a nonlinear model, such as L1 squared or cubic, etc., and no specific restrictions are made here.

[0028] In one embodiment of this disclosure, setting up the simulated evaluation scenario further includes: determining the equivalent rotational speed of the three-dimensional rotating device based on the orbital linear velocity of the spaceborne infrared instrument, the simulated detection distance, the actual fire point size, and the simulated fire point size, in order to set up the simulated evaluation scenario. The equivalent rotational speed of the three-dimensional rotating device is used to simulate the speed of the spaceborne infrared instrument.

[0029] Specifically, the orbital linear velocity v and actual fire point size D of the spaceborne infrared instrument are obtained. Based on the ground test distance h and simulated fire point size d, the equivalent rotational speed w of the turntable is obtained to simulate the speed of the spaceborne infrared instrument. The formula for calculating the equivalent rotational speed is as follows:

[0030] As an example, such asFigure 2 As shown, a blackbody was used as the simulated fire point. The temperature was controlled at 400℃ and 600℃ according to the evaluation requirements. The spatial resolution was 60 meters. By obtaining the linear velocity of 7km / s at an orbital altitude of 500km, the actual fire point size of 10m×10m, and the simulated fire point size of 6cm×6cm based on the ground test distance of 3km, the equivalent rotation speed of the turntable was obtained as 0.8° / s. The load was fixed on the turntable and rotated at a speed of 0.8° / s to simulate the satellite motion state.

[0031] Figure 3 A comparison of atmospheric radiation attenuation models at 3 km and 500 km is shown.

[0032] Step 103: Conduct a temperature-controlled combustion test in a simulated evaluation scenario and collect data.

[0033] In this embodiment, a ground-based testing system is set up to conduct long-distance temperature-controlled combustion tests on target points. Fire point detection is performed using a spaceborne infrared instrument to obtain multiple image output values. The ground-based testing system includes: a controllable fire source device (gas nozzle, controllable solid combustion platform, hot plate, or target blackbody), a thermal imager (high-precision thermal imager / handheld radiometer), a rangefinder, a three-dimensional rotation device, a temperature and humidity detection device, a data acquisition and synchronization unit, a radiation transfer model calculation unit, and an evaluation algorithm processing unit.

[0034] Step 104: Data processing and evaluation of spaceborne infrared instruments.

[0035] In this embodiment, pre-calibrated calibration parameters of the spaceborne infrared instrument are obtained, including calibration coefficients, spaceborne infrared instrument noise, and NETD. For each image output value, based on the image output value and calibration parameters, the radiant energy of each pixel of the spaceborne infrared instrument and the noise equivalent energy of the spaceborne infrared instrument are determined. The energy multiple is calculated by the ratio of the difference in radiant energy between each pixel of the spaceborne infrared instrument and the surrounding background to the noise equivalent energy. Then, each calculated energy multiple is compared with a multiple threshold to generate an evaluation result of the fire detection performance of the spaceborne infrared instrument for the actual scene to be evaluated.

[0036] The calibration process is explained below.

[0037] A blackbody light source was used to perform laboratory radiometric calibration of the instrument, measuring responsivity, NETD, and radiometric calibration coefficients. The formulas for NETD and radiometric calibration are as follows: NETD=(T1-T2) / ((DN1-DN2) / RMES) DN = A × L + B Where NETD is the noise equivalent temperature difference, DN1 and DN2 are the image output values ​​of the spaceborne infrared instrument at the detection temperatures T1 and T2, respectively, and DN is the image output value; L is the radiation energy, which can be calculated based on Planck's formula using the target temperature and the response band of the spaceborne infrared instrument; A and B are the calibration coefficients, and RMES is the noise of the spaceborne infrared instrument.

[0038] As an example, in a laboratory calibration environment, the blackbody temperature is controlled at seven temperature points: 27℃, 37℃, 47℃, 57℃, 67℃, 77℃, and 97℃. The seven temperature points are continuously imaged using a spaceborne infrared instrument. Then, the NETD is calculated based on the imaging at 77℃ and 97℃, and the calibration coefficient is calculated based on the imaging at 37℃, 47℃, and 67℃.

[0039] In this example, the ground testing system also includes a blackbody calibration device. The instruments prepared are as follows: a blackbody calibration device (temperature adjustable (0-100℃), temperature control accuracy 0.1℃), a controllable flame source device (size adjustable (0-30mm), temperature adjustable (0-600℃), temperature control accuracy 0.1℃), a high-resolution thermal imager (temperature measurement accuracy 2℃, temperature measurement range (-20℃-800℃)), a rangefinder (10km), a three-dimensional rotation device (X, Y, Z rotation, rotation speed adjustable (0-60°)), a computer, the mid-wave infrared imager on the satellite under test, and a thermometer and hygrometer. Laboratory radiation calibration of the instrument is carried out using a blackbody light source, such as... Figure 4 As shown, the responsiveness, NETD, and scaling factor are measured.

[0040] The blackbody temperature was controlled at seven points: 27℃, 37℃, 47℃, 57℃, 67℃, 77℃, and 97℃. One hundred frames of continuous imaging were performed at each of these seven blackbody temperatures using the onboard mid-wave infrared imager. Then, the net potential density (NETD) was calculated using a formula based on the 77℃ and 97℃ temperatures, and the calibration coefficients were calculated using the formula based on the 37℃, 47℃, and 67℃ temperatures. The results are shown below:

[0041] Figure 5 The schematic diagram of the measurement response results shows that the instrument was fitted using 300K, 320K, 330K, 350K, and 370K. The diagram illustrates that the spaceborne infrared instrument did not reach saturation at 97℃, and there was a nonlinear relationship between 27℃ and 97℃. However, as the temperature increases, it tends to become linear.

[0042] Figure 6 In the schematic diagram of the absolute calibration coefficients and fitting results of the medium wave, the calibration coefficients A = 0.0035 and B = -23.1178.

[0043] The evaluation process is described below.

[0044] In this embodiment, the multiplier threshold is determined based on the pre-calibrated NETD of the spaceborne infrared instrument. Specifically, when NETD ≤ 0.05K, the difference between the multiplier threshold and 2 is less than a preset value, meaning the multiplier threshold is approximately 2; when 0.05K < NETD ≤ 0.5K, the difference between the multiplier threshold and 5 is less than a preset value, meaning the multiplier threshold is approximately 5; and when 0.5K < NETD, the multiplier threshold is greater than 10. Therefore, the ability of the infrared instrument to detect fire points is quantitatively evaluated. The stronger the signal-to-noise ratio, the lower the multiplier threshold can be. For fire points of size D and temperature T, if the energy multiplier is greater than the multiplier threshold, the spaceborne infrared instrument can be considered fully capable of detecting fire points (fire points of size ≥ D at temperature T, or fire points of size D with temperature ≥ T).

[0045] In one embodiment of this disclosure, each calculated energy multiple is compared with a multiple threshold to generate a fire detection performance evaluation result of the spaceborne infrared instrument for the actual scene to be evaluated, including: if the energy multiple is greater than the multiple threshold, the count is incremented by one; the number of images with actual fire points in the multiple image output values ​​is determined; and the fire detection performance evaluation result of the spaceborne infrared instrument for the actual scene to be evaluated is generated according to the proportion of the count to the number of images.

[0046] In this embodiment, for each image output value, the radiation energy of each pixel of the spaceborne infrared instrument is determined based on the image output value and the calibration coefficient, and the noise equivalent energy is calculated based on the noise of the spaceborne infrared instrument. The energy multiple is calculated by the ratio of the radiation energy difference between each pixel of the spaceborne infrared instrument and the surrounding background to the noise equivalent energy.

[0047] The formula is as follows: R' = R × × P=L i / R i ', where R is the noise equivalent energy, R' is the noise equivalent energy after atmospheric attenuation, the noise equivalent energy is obtained from F(RMES), RMES is obtained for each instrument during the calibration process, and the F() function represents linear processing, and Referring to the aforementioned formula, i represents the i-th image, Li is the difference in radiation energy between each pixel of the spaceborne infrared instrument and the surrounding background (including the target energy), Ri' is the noise equivalent energy, and P is the energy multiple.

[0048] As an example, taking 0.05K < NETD ≤ 0.5K as an example, with a multiplier threshold of 5, the results of the spaceborne infrared instrument are evaluated according to the formula as follows: The R' of the firepoint pixels of this spaceborne infrared instrument is between 0.18 and 0.35, with most concentrated around 0.2, such as... Figure 7As shown, the horizontal axis represents the number of images, and the vertical axis is R'. If, with R' = 0.2, 100% of 600℃, 10m×10m fire points can be identified in a real-world scene, but only 3.7% of 400℃, 10m×10m fire points can be identified, then the spaceborne infrared instrument is ultimately assessed as capable of identifying 600℃, 10m×10m fire points, with a limit of detecting 400℃ fire points, but with a low accuracy of 3.7%. Figure 8 As shown, the horizontal axis represents the number of images, and the vertical axis represents the energy multiplier. For a fire point temperature of 400℃, the number of images with actual fire points is 54, and the energy multiplier is greater than the threshold (number of images with fire points identified) is 2, with a proportion of 3.7%. For a fire point temperature of 600℃, the number of images with actual fire points is 81, and the energy multiplier is greater than the threshold (number of images with fire points identified) is 81, with a proportion of 100%.

[0049] According to the technical solution of this disclosure, through laboratory precision calibration, controlled small-scale combustion experiments, and the construction of an equivalent evaluation model of atmosphere, transmission, energy, and noise, ground-based assessment of small-scale wildfires in power grids can be achieved. The detection accuracy of small-scale wildfires by spaceborne infrared instruments can be quantitatively analyzed. The detection capability of spaceborne infrared instruments under different backgrounds, atmospheric conditions, and fire point conditions of different sizes and temperatures can be repeatedly and systematically evaluated on the ground. This can provide quantitative basis for on-orbit threshold setting, algorithm screening, and instrument parameter optimization, and reduce the risk of missed detections in orbit.

[0050] This disclosure also provides a ground-based evaluation device for the fire detection performance of a spaceborne infrared instrument, the device comprising: The acquisition module is used to acquire scene parameters of the actual scenario to be evaluated; scene parameters include actual fire point size, spatial resolution of spaceborne infrared instruments, orbital altitude, and wave value; The first determining module is used to determine the first expression corresponding to the orbital altitude and wave value by adopting a radiation energy transfer model based on atmospheric attenuation. The second determining module is used to solve the first expression with distance as the unknown quantity to obtain the simulated detection range of the spaceborne infrared instrument; The setting module is used to determine the size of the simulated fire point based on the simulated detection distance, the spatial resolution of the spaceborne infrared instrument, and the actual fire point size, so as to realize the setting of the simulated evaluation scenario; The test module is used to detect fire points based on simulated evaluation scenarios and acquire multiple image output values ​​through spaceborne infrared instruments. The calibration module is used to acquire the pre-calibrated calibration parameters of the spaceborne infrared instrument; the calibration parameters include calibration coefficients and spaceborne infrared instrument noise. The calculation module is used to determine the radiation energy of each pixel of the spaceborne infrared instrument and the noise equivalent energy of the spaceborne infrared instrument for each image output value, based on the image output value and calibration parameters. The energy multiple is calculated by the ratio of the radiation energy difference between each pixel of the spaceborne infrared instrument and the surrounding background to the noise equivalent energy. The evaluation module compares each calculated energy multiplier with a multiplier threshold to generate an evaluation result of the fire detection performance of the spaceborne infrared instrument for the actual scenario to be evaluated.

[0051] The ground-based evaluation device for the fire detection performance of spaceborne infrared instruments provided in this disclosure can execute the ground-based evaluation method for the fire detection performance of any spaceborne infrared instrument provided in this disclosure, and has the corresponding functional modules and beneficial effects for executing the method. Content not described in detail in the device embodiments of this disclosure can be referred to the description in any method embodiment of this disclosure.

[0052] This disclosure also provides an electronic device including one or more processors and a memory. The processor may be a central processing unit (CPU) or other processing unit with data processing capabilities and / or instruction execution capabilities, and may control other components in the electronic device to perform desired functions. The memory may include one or more computer program products, which may include various forms of computer-readable storage media, such as volatile memory and / or non-volatile memory. Volatile memory may include, for example, random access memory (RAM) and / or cache memory. Non-volatile memory may include, for example, read-only memory (ROM), hard disk, flash memory, etc. One or more computer program instructions may be stored on the computer-readable storage medium, and the processor may execute the program instructions to implement the methods of the embodiments of this disclosure above and / or other desired functions. Various contents such as input signals, signal components, and noise components may also be stored in the computer-readable storage medium.

[0053] In one example, the electronic device may also include input and output devices, which are interconnected via a bus system and / or other forms of connection. Furthermore, the input device may include, for example, a keyboard, a mouse, etc. The output device can output various information to the outside, including determined distance information, direction information, etc. The output device may include, for example, a display, a speaker, a printer, and a communication network and its connected remote output devices, etc. In addition, depending on the specific application, the electronic device may include any other suitable components such as a bus, input / output interfaces, etc.

[0054] In addition to the methods and apparatus described above, embodiments of this disclosure may also be computer program products, including computer program instructions that, when executed by a processor, cause the processor to perform any of the methods provided in the embodiments of this disclosure.

[0055] Computer program products can be written in any combination of one or more programming languages ​​to perform the operations of embodiments of this disclosure. The programming languages ​​include object-oriented programming languages ​​such as Java and C++, as well as conventional procedural programming languages ​​such as C or similar languages. The program code can be executed entirely on a user's computing device, partially on a user's computing device, as a standalone software package, partially on a user's computing device and partially on a remote computing device, or entirely on a remote computing device or server.

[0056] Furthermore, embodiments of this disclosure may also be computer-readable storage media storing computer program instructions that, when executed by a processor, cause the processor to perform any method provided in the embodiments of this disclosure.

[0057] Computer-readable storage media may take the form of any combination of one or more readable media. A readable medium may be a readable signal medium or a readable storage medium. A readable storage medium may, for example, include, but is not limited to, electrical, magnetic, optical, electromagnetic, infrared, or semiconductor systems, apparatuses, or devices, or any combination thereof. More specific examples of readable storage media (a non-exhaustive list) include: electrical connections having one or more wires, portable disks, hard disks, random access memory (RAM), read-only memory (ROM), erasable programmable read-only memory (EPROM or flash memory), optical fibers, portable compact disk read-only memory (CD-ROM), optical storage devices, magnetic storage devices, or any suitable combination thereof.

[0058] It should be noted that, in this document, relational terms such as "first" and "second" are used merely to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element.

[0059] The above description is merely a specific embodiment of this disclosure, enabling those skilled in the art to understand or implement it. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of this disclosure. Therefore, this disclosure is not to be limited to the embodiments described herein, but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. A ground-based evaluation method for the fire detection performance of a spaceborne infrared instrument, characterized in that, The method includes: Obtain the scene parameters of the actual scenario to be evaluated; the scene parameters include the actual fire point size, the spatial resolution of the spaceborne infrared instrument, the orbital altitude, and the wave value; A radiative energy transfer model based on atmospheric attenuation is used to determine a first expression corresponding to the orbital altitude and the wave value; Solve the first expression with distance as the unknown to obtain the simulated detection range of the spaceborne infrared instrument; Based on the simulated detection distance, the spatial resolution of the spaceborne infrared instrument, and the actual fire point size, the simulated fire point size is determined to achieve the simulation evaluation scenario setting; Fire point detection is performed based on the simulated evaluation scenario, and multiple image output values ​​are acquired through the spaceborne infrared instrument. Obtain the pre-calibrated calibration parameters of the spaceborne infrared instrument; the calibration parameters include calibration coefficients and spaceborne infrared instrument noise. For each image output value, the radiation energy of each pixel of the spaceborne infrared instrument and the noise equivalent energy of the spaceborne infrared instrument are determined according to the image output value and the calibration parameters. The energy multiple is calculated by the ratio of the difference in radiation energy between each pixel of the spaceborne infrared instrument and the surrounding background to the noise equivalent energy. Each calculated energy multiplier is compared with a multiplier threshold to generate a fire detection performance evaluation result of the spaceborne infrared instrument for the actual scenario to be evaluated.

2. The method as described in claim 1, characterized in that, The step of employing a radiative energy transfer model based on atmospheric attenuation to determine a first expression corresponding to the orbital altitude and the wave value includes: Calculate the first atmospheric transmittance of the wave value based on the orbital altitude, and simultaneously calculate the first radiant energy of the fire point at the wave value for a given temperature and size. Substitute the first atmospheric transmittance and the first radiant energy into the radiant energy transfer model based on atmospheric attenuation to determine the first expression.

3. The method as described in claim 1, characterized in that, The implementation of the simulation evaluation scenario setting also includes: Based on the orbital linear velocity of the spaceborne infrared instrument, the simulated detection distance, the actual fire point size, and the simulated fire point size, the equivalent rotational speed of the three-dimensional rotating device is determined to achieve the simulation evaluation scenario setting; the equivalent rotational speed of the three-dimensional rotating device is used to simulate the speed of the spaceborne infrared instrument.

4. The method as described in claim 1, characterized in that, The calibration parameters also include NETD, and the method further includes: The multiple threshold is determined based on the NETD; Specifically, when NETD≤0.05K, the difference between the multiple threshold and 2 times is less than a preset value; When 0.05K < NETD ≤ 0.5K, the difference between the multiple threshold and 5 times is less than a preset value; When 0.5K < NETD, the multiple threshold is greater than 10 times.

5. The method as described in claim 4, characterized in that, The method further includes: In a laboratory calibration environment, the blackbody temperature was controlled at seven temperature points: 27℃, 37℃, 47℃, 57℃, 67℃, 77℃, and 97℃. The spaceborne infrared instrument was used to continuously image the seven temperature points. The NETD is calculated based on imaging at 77℃ and 97℃. The calibration coefficients were calculated based on imaging at 37°C, 47°C, and 67°C.

6. The method as described in claim 1, characterized in that, The step of comparing each calculated energy multiplier with a multiplier threshold to generate a fire detection performance evaluation result for the spaceborne infrared instrument in the actual scenario to be evaluated includes: If the energy multiplier is greater than the multiplier threshold, the count is incremented by one; Determine the number of images containing actual fire points among the multiple image output values; Based on the proportion of the count to the number of images, the performance evaluation result of the fire detection of the spaceborne infrared instrument for the actual scene to be evaluated is generated.

7. A ground testing system, characterized in that, The system for implementing the method of claim 1, wherein the system comprises: Blackbody calibration device, controllable fire source device, thermal imager, rangefinder, three-dimensional rotation device, temperature and humidity detection device, data acquisition and synchronization unit, radiation transfer model calculation unit and evaluation algorithm processing unit.

8. An electronic device, characterized in that, include: processor; Memory used to store the processor's executable instructions; The processor is configured to read the executable instructions from the memory and execute the instructions to implement the ground evaluation method for fire detection performance of the spaceborne infrared instrument according to any one of claims 1-6.

9. A computer-readable storage medium, characterized in that, The storage medium stores a computer program, which, when executed by a processor, implements the ground evaluation method for the fire detection performance of any of the spaceborne infrared instruments described in claims 1-6.

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