A lunar surface key exploration area radiance simulation method and device

Abstract

The application provides a method and device for simulating the brightness of a lunar surface key detection area, and relates to the technical field of lunar exploration. The method comprises the following steps: determining a simulation spectrum range according to load parameters; obtaining the lunar soil reflection characteristics, surface terrain parameters, solar incident angle and solar spectrum irradiance information of a target area; selecting a corresponding brightness calculation model; calculating the spectral brightness of the target area at the actual observation time of the detection load; calculating the signal-to-noise ratio of the target detection according to the target spectral brightness, load optical efficiency, detector parameters and system noise; and finally, through iterative calculation of the spectral brightness and detection signal-to-noise ratio of a specific target at different orbits, comparison and selection of a suitable detection orbit and detection time. The application can comprehensively consider the lunar surface terrain, illumination conditions, reflection characteristics and other factors, accurately simulate the change of the lunar surface spectral brightness, and provide accurate reference data for the motion compensation of a high-resolution imaging spectrometer.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of lunar exploration, and particularly relates to a lunar surface key exploration area radiance simulation method and device. BACKGROUND

[0002] With the rapid development of deep space exploration technology, lunar exploration has become an important strategic direction for each space power. In the lunar exploration mission, the high-resolution imaging spectrometer plays an important role in detecting the information of the lunar surface material composition, geological structure and the like. However, the existing lunar exploration data still has obvious deficiencies in spatial resolution, signal-to-noise ratio and polar coverage, and it is difficult to meet the actual needs of subsequent deep space exploration tasks such as lunar scientific station site selection and astronaut activity path planning.

[0003] At present, the high-resolution imaging spectrometer faces the following technical difficulties in the lunar exploration process: firstly, the lunar surface terrain is rugged, which makes it difficult to achieve efficient and comprehensive coverage of the target area; secondly, the orbit determination accuracy and speed-height ratio change of the lunar exploration satellite have obvious disadvantages compared with the earth remote sensing satellite, which seriously restricts the quality and efficiency of data acquisition; thirdly, the lunar surface target signal is weak, especially in the polar region where the light condition is not ideal, although the integration time can be prolonged to improve the signal-to-noise ratio, but this method will inevitably reduce the spatial scanning efficiency, forming a technical contradiction between coverage rate and signal-to-noise ratio.

[0004] Further, in the lunar high-resolution imaging spectral exploration, the sub-satellite point residence time is shorter than the required integration time of the detector, and the "advance-lag" motion compensation needs to be used to prolong the residence time and improve the detection signal-to-noise ratio. The cost of motion compensation to improve the signal-to-noise ratio is to shorten the coverage area of a single scan, which leads to the detection of key target areas no longer being continuous and full coverage, and combined with the influence of light and terrain and other factors, the appropriate orbit and detection time need to be selected from multiple detection orbits, therefore, the lunar surface key exploration area radiance simulation is essential.

[0005] In the prior art, although the motion compensation technology has been widely used in obtaining high-quality imaging spectral remote sensing data, due to the particularity of the lunar exploration environment, such as significant terrain fluctuation, high compensation ratio requirement, large speed-height ratio change, low orbit determination accuracy and the like, the motion compensation technology in the field of earth remote sensing is difficult to be directly transplanted to the lunar exploration scene.

[0006] In addition, the simulation research on the radiance of the lunar key exploration area is still in its infancy. The existing simulation method cannot effectively integrate the lunar surface terrain, lighting conditions, multi-dimensional factors such as lunar spectral reflectance characteristics, and it is difficult to accurately simulate the dynamic change rule of the lunar spectral radiance. This technical bottleneck directly affects the accuracy of the motion compensation of the high-resolution imaging spectrometer, and further restricts the quality and acquisition efficiency of the lunar exploration data. SUMMARY

[0007] The purpose of the present application is to provide a lunar key exploration area radiance simulation method to improve the quality and acquisition efficiency of lunar exploration data. This method should consider the lunar surface terrain, lighting conditions, and reflectance characteristics, accurately simulate the change of the lunar spectral radiance, and provide reliable reference data for the motion compensation of the high-resolution imaging spectrometer, thereby supporting the fine exploration and development of lunar scientific resources.

[0008] To achieve the above purpose, the present application realizes the following technical scheme:

[0009] A lunar key exploration area radiance simulation method, comprising the following steps:

[0010] S1: determining the simulation spectral range and spectral resolution according to the load parameters;

[0011] S2: obtaining the lunar soil reflectance characteristics, surface terrain parameters, solar incidence angle and solar spectral irradiance information of the target area;

[0012] S3: selecting the corresponding radiance calculation model according to the simulation spectral range;

[0013] S4: calculating the spectral radiance of the target area at the actual observation time of the detection load based on the radiance calculation model and the obtained information;

[0014] S5: calculating the signal-to-noise ratio of the target detection according to the target spectral radiance, load optical efficiency, detector parameters and system noise;

[0015] S6: iteratively calculating the spectral radiance and detection signal-to-noise ratio of the specific target under different orbits, and comparing and selecting the appropriate detection orbit and detection opportunity.

[0016] Further, in step S3, when the simulation spectral range is the visible short-wave infrared spectral range, a radiance calculation model that only considers the reflection of solar radiation by lunar soil is selected; the wavelength range of the visible short-wave infrared spectral range is 0.35-2.2 μm.

[0017] Further, the radiance calculation model that only considers the reflection of solar radiation by lunar soil is shown in the following formula:

[0018]

[0019] in:

[0020] L ref (λ,θ i ,θ r ,φ) is the spectral radiance of lunar soil reflectance at wavelength λ;

[0021] ρ(λ,θ i ,θ r ,φ) is the bidirectional reflectance distribution function at wavelength λ, which is determined by lunar soil characteristics and observation geometry;

[0022] E(λ,θ i Let be the point at wavelength λ, where the sun is at an incident angle θ. i Spectral irradiance under the following conditions;

[0023] θ i θ is the angle of incidence of sunlight. r φ is the reflection angle; φ is the phase angle between the reflected and incident light.

[0024] Further: In step S3, when the simulation spectrum is the mid-to-long-wave infrared spectrum, a radiance calculation model that simultaneously considers solar reflectance and lunar soil self-radiation is selected; the wavelength of the mid-to-long-wave infrared spectrum is greater than 2.2 μm.

[0025] Furthermore: the lunar surface spectral radiance calculation model that simultaneously considers solar radiation reflection and lunar soil self-radiation is characterized by calculating the lunar surface spectral radiance using the following formula:

[0026] L total (λ,θ i ,θ r ,φ)=L ref (λ,θ i ,θ r ,φ)+L emit (λ,T)

[0027] in:

[0028] L total (λ,θ i ,θ r ,φ) is the total spectral radiance at wavelength λ;

[0029] L ref (λ,θ i ,θ r φ) represents the spectral radiance of solar radiation reflected by the lunar soil;

[0030] L emit (λ,T) represents the spectral radiance of lunar regolith, calculated using the following formula:

[0031] L emit (λ, T) = ∈(λ) * B(λ, T)

[0032] wherein:

[0033] ∈(λ) is the lunar soil spectral emissivity at wavelength λ;

[0034] B(λ, T) is the blackbody radiation spectral brightness based on Planck's law, T is the lunar soil temperature in Kelvin, which can be calculated using one-dimensional heat conduction equation.

[0035] Further, in step S2, the lunar soil reflection characteristics are the bidirectional reflectance characteristics of the actual target lunar soil, the surface topography parameters are obtained from point cloud data of the target area, the solar incident angle is determined by parameters such as the target point payload transit time, target latitude and longitude, and the solar spectral irradiance is obtained by convolution according to the spectral resolution of the payload.

[0036] Further, in step S5, the signal-to-noise ratio of the target detection is calculated according to the following formula:

[0037] The solar radiation reflected by the lunar surface is detected by the detector, and the target radiation power P(λ) received by the detector is calculated according to the following formula:

[0038]

[0039] wherein E(λ, θ i ) is the solar radiation spectrum on the lunar surface, τ a is the lunar atmospheric transmittance, θ is the solar elevation angle, ρ is the lunar surface albedo, τ o is the optical efficiency, A d is the area of the photosensitive surface of the detector, and F# is the optical system parameter;

[0040] According to the target radiation power, the effective signal electron number N s (λ) generated by the target signal on the detector unit is calculated according to the following formula:

[0041]

[0042] wherein T int is the integration time of the detector, η(λ) is the quantum efficiency, and E ph (λ) is the single-photon energy;

[0043] According to the effective signal electron number, the signal-to-noise ratio SNR(λ) is calculated according to the following formula:

[0044]

[0045] wherein, n read N is the read noise of the detector, back N (λ) is the number of background electrons introduced by background radiation, dark N (λ) is the number of electrons introduced by the dark current of the detector, n N (λ) is the number of noise electrons calculated according to a typical noise electron model.

[0046] Further, in the step S6, the suitable detection orbit is selected, which represents the optimal orbit in the simulation results of the radiance of different orbits in the same target area and the signal-to-noise ratio, and the optimal orbit is the orbit with the highest value; the suitable detection time is selected, which corresponds to the detection time capable of meeting the coverage requirement of the target area under the same orbit considering the motion compensation along the orbit duty cycle, the detection time includes the start detection time and the end detection time, and the orbit spatial duty cycle is the ratio of the detection area to the flight area; the motion compensation parameters of the high-resolution imaging spectrometer are determined according to the calculated spectral radiance and signal-to-noise ratio; the motion compensation parameters include the pointing mirror rotation angle sequence and the integration time.

[0047] The application further provides a lunar surface key detection area radiance simulation device applying the above method, and the device comprises:

[0048] A determination unit is configured to determine a simulation spectrum range according to the load parameters.

[0049] An acquisition unit is configured to acquire the lunar soil reflection characteristics, the surface terrain parameters, the solar incident angle and the solar spectrum irradiance information of the target area.

[0050] A selection unit is configured to select a corresponding radiance calculation model according to the simulation spectrum range.

[0051] A first calculation unit is configured to calculate the spectral radiance of the target area at an actual observation moment of the detection load based on the radiance calculation model and the acquired information.

[0052] A second calculation unit is configured to calculate the signal-to-noise ratio of the target detection in combination with the load optical efficiency, the detector parameters and the system noise.

[0053] A third calculation unit is configured to calculate the temperature of the lunar surface target area by using a one-dimensional heat conduction equation.

[0054] The first calculation unit is further configured to substitute the temperature into the radiance calculation model to calculate the lunar soil self-radiation.

[0055] Compared with the prior art, the application has the following beneficial effects:

[0056] I. Improve data quality: By considering various factors such as lunar surface topography, lighting conditions, and reflection characteristics, the method accurately simulates the variation of lunar spectral radiance, providing reliable data support for the motion compensation of the high-resolution imaging spectrometer, and significantly improving the quality of lunar exploration data.

[0057] II. Enhance acquisition efficiency: Using the method, the spectral radiance of the target area at a specific time can be calculated more accurately, and the signal-to-noise ratio of the target detection can be calculated accordingly, guiding the setting of the motion compensation parameters of the high-resolution imaging spectrometer, so that the spatial scanning efficiency is improved while maintaining a high signal-to-noise ratio, enhancing the efficiency of data acquisition.

[0058] III. Adapt to complex conditions: The method can adapt to complex conditions such as significant terrain undulations, high compensation ratio requirements, and large speed-altitude ratio changes, providing effective solutions to the problem that existing technologies cannot be directly applied to lunar exploration.

[0059] IV. Flexible response to different spectral bands: The method can flexibly respond to different spectral bands. For the visible short-wave infrared spectral band, the radiance calculation model considering the reflection of solar radiation by lunar soil is selected; while for the medium-long wave infrared spectral band, both the amount of solar reflection and the self-radiation of lunar soil are considered, ensuring the accuracy of radiance calculation in different wavelength ranges.

[0060] V. Support fine exploration: By accurately calculating the spectral radiance and signal-to-noise ratio of the target area, the method provides a basis for setting the motion compensation parameters of the high-resolution imaging spectrometer, and further supports the fine exploration and development of lunar scientific resources, providing strong data support for subsequent lunar scientific station site selection and astronaut activity path planning tasks. BRIEF DESCRIPTION OF DRAWINGS

[0061] Figure 1 A flowchart of the lunar key exploration area radiance simulation method of the present application in one embodiment is shown in the figure; DETAILED DESCRIPTION

[0062] The technical solutions of the present application will be described in detail below with reference to the accompanying drawings. Obviously, the described embodiments are part of the embodiments of the present application, not all embodiments. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative labor are within the scope of protection of the present application.

[0063] In the description of the present application, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer" and the like indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, and therefore cannot be understood as indicating or implying that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as limiting the present application. In addition, the terms "first", "second", "third" are only for descriptive purposes and cannot be understood as indicating or implying relative importance.

[0064] The present application provides a method for simulating the brightness of a lunar key detection area, comprising the following steps: determining a simulation spectral range according to load parameters; obtaining the lunar soil reflection characteristics, surface topography parameters, solar incidence angle and solar spectrum irradiance information of the target area; selecting a corresponding brightness calculation model according to the simulation spectral range; calculating the spectral brightness of the target area at the actual observation time of the detection load based on the brightness calculation model and the obtained information; and calculating the signal-to-noise ratio of the target detection according to the target spectral brightness, load optical efficiency, detector parameters and system noise.

[0065] In the implementation of the present application, first, the spectral range required for simulation is determined according to the load parameters of the imaging spectrometer. For the visible short-wave infrared spectral range (0.35 μm to 2.2 μm), a brightness calculation model considering the reflection of solar radiation by lunar soil is selected. For the medium-long-wave infrared spectral range (wavelength greater than 2.2 μm), a brightness calculation model considering both the amount of solar reflection and the lunar soil's own radiation is selected. Through such selection, the spectral brightness characteristics under different wavebands can be more accurately reflected.

[0066] Next, the relevant information of the target area is obtained, including lunar soil reflection characteristics, surface topography parameters, solar incidence angle, and solar spectrum irradiance, etc. These information can be obtained through existing databases or ground experiments. After obtaining these information, based on the selected brightness calculation model, the spectral brightness of the target area at the actual observation time of the detection load is calculated using these parameters of the target area. For the medium-long-wave infrared spectral range, a one-dimensional heat conduction equation is also used to calculate the temperature of the lunar surface target area, and the temperature is substituted into the brightness calculation model to calculate the amount of lunar soil's own radiation.

[0067] After the spectral brightness of the target area is calculated, the signal-to-noise ratio of the target detection is calculated according to a specific formula, combining the optical efficiency of the imaging spectrometer, the parameters of the detector, and the noise level of the system. This formula reflects the influence of system performance on the signal-to-noise ratio, and through this way, a reference basis can be provided for the motion compensation of the imaging spectrometer.

[0068] Finally, according to the calculated spectral radiance and signal-to-noise ratio, the motion compensation parameters of the high-resolution imaging spectrometer are determined, mainly including the pointing mirror rotation angle sequence and the integration time. These parameters can be uploaded to the load through instructions to ensure that the best detection effect can be achieved in a specific detection task.

[0069] Through the above steps, the moon surface terrain, illumination conditions, reflection characteristics and other factors are comprehensively considered, the change of the lunar surface spectral radiance is accurately simulated, accurate reference data for the motion compensation of the high-resolution imaging spectrometer is provided, and the fine exploration and development of the lunar scientific resources are supported.

[0070] The above description is intended to enable a person skilled in the art to quickly understand the technical solution points of the present application, and the technical solution of the present application will be described in detail through specific embodiments.

[0071] A lunar surface key detection area radiance simulation method, comprising the following steps:

[0072] S1: determining the simulation spectral range and spectral resolution according to the load parameters;

[0073] S2: obtaining the lunar soil reflection characteristics, surface terrain parameters, solar incident angle and solar spectral irradiance information of the target area;

[0074] In an embodiment, the lunar soil reflection characteristics are the bidirectional reflectance characteristics of the actual target lunar soil; the surface terrain parameters are obtained through the point cloud data of the target area; the solar incident angle is confirmed through the target point load transit time, target latitude and longitude and other parameters; the solar spectral irradiance is obtained by convolution according to the spectral resolution of the load, and the solar spectral irradiance is derived from the atmospheric layer outside solar spectral irradiance information provided by (Gueymard, 2018).

[0075] S3: selecting a corresponding radiance calculation model according to the simulation spectral range;

[0076] In other embodiments, in the step S3, when the simulation spectral range is the visible short-wave infrared spectral range, a radiance calculation model considering only the reflection of solar radiation by lunar soil is selected; the wavelength range of the visible short-wave infrared spectral range is 0.35-2.2 μm; when the simulation spectral range is the medium-long-wave infrared spectral range, a radiance calculation model considering both the reflection of solar radiation and the self-radiation of lunar soil is selected; the wavelength of the medium-long-wave infrared spectral range is greater than 2.2 μm.

[0077] The radiance calculation model considering only the reflection of solar radiation by lunar soil is shown in the following formula:

[0078]

[0079] Wherein:

[0080] L ref (λ, θ i , θ r , φ) is the lunar soil reflectance spectrum radiance at wavelength λ;

[0081] ρ(λ, θ i , θ r , φ) is the bidirectional reflectance distribution function at wavelength λ, determined by the lunar soil properties and observation geometry;

[0082] E(λ, θ i ) is the spectral irradiance at wavelength λ, with the sun at incident angle θ i

[0083] θ i is the solar light incident angle; θ r is the reflection angle; φ is the phase angle of the reflected and incident light.

[0084] The lunar surface spectrum radiance calculation model considering both the solar radiation reflection amount and the lunar soil self-radiation, characterized in that the lunar surface spectrum radiance is calculated by the following formula:

[0085] L total (λ, θ i , θ r , φ) = L ref (λ, θ i , θ r , φ) + L emit (λ, T)

[0086] Wherein:

[0087] L total (λ, θ i , θ r , φ) is the total spectrum radiance at wavelength λ;

[0088] L ref (λ, θ i , θ r , φ) is the spectrum radiance of the lunar soil reflecting solar radiation;

[0089] L emit (λ, T) is the spectrum radiance of the lunar soil self-radiation, calculated by the following formula:

[0090] L emit (λ, T) = ∈(λ)·B(λ, T)

[0091] Wherein:

[0092] ∈(λ) is the spectrum emissivity of the lunar soil at wavelength λ; ​

[0093] B(λ, T) is the blackbody radiation spectral radiance based on Planck's law, expressed as:

[0094]

[0095] where h is Planck's constant; c is the speed of light; k B is the Boltzmann constant; T is the lunar soil temperature in Kelvin, which can be calculated using a one-dimensional heat conduction equation.

[0096] S4: Based on the radiance calculation model and the acquired information, the spectral radiance of the target region at the actual observation time of the payload is calculated;

[0097] S5: The signal-to-noise ratio of the target detection is calculated according to the target spectral radiance, the payload optical efficiency, the detector parameters, and the system noise.

[0098] In other embodiments, the signal-to-noise ratio of the target detection is calculated according to the following formula:

[0099] The detector detects the solar radiation reflected by the lunar surface, and the target radiation power P(λ) received by the detector is calculated according to the following formula:

[0100]

[0101] where E(λ, θ i ) is the solar radiation spectrum on the lunar surface, τ a is the lunar atmospheric transmittance, θ is the solar elevation angle, ρ is the lunar surface albedo, τ o is the optical efficiency, A d is the detector photosensitive area, and F# is the optical system parameter.

[0102] According to the target radiation power, the effective signal electron number Ns(λ) generated by the target signal on the detector unit is calculated according to the following formula:

[0103]

[0104] where T int is the integration time of the detector, η(λ) is the quantum efficiency, and Eph(λ) is the single-photon energy.

[0105] According to the effective signal electron number, the signal-to-noise ratio SNR(λ) is calculated according to the following formula:

[0106]

[0107] where n read is the readout noise of the detector, N back (λ) is the background electron number introduced by the background radiation, and Ndark (λ) is the number of electrons introduced by the detector dark current, N n (λ) is the number of noise electrons calculated according to a typical noise electron model.

[0108] S6: iteratively calculating the spectral radiance of the specific target in different orbits, the detection signal-to-noise ratio, and comparing and selecting a suitable detection orbit and detection time.

[0109] In some embodiments, in step S6, the suitable detection orbit is selected as the optimal orbit in the simulation results of the radiance and signal-to-noise ratio of different orbits of the same target region, and the optimal orbit is the orbit with the highest value; the suitable detection time corresponds to the detection time that can achieve the coverage requirement of the target region in the same orbit, considering the motion compensation along the orbit duty cycle, and the detection time includes the start detection time and the end detection time; the orbit spatial duty cycle is the ratio of the detection region to the flight region; the spectral radiance and the signal-to-noise ratio calculated are used to determine the motion compensation parameters of the high-resolution imaging spectrometer; the motion compensation parameters include the pointing mirror rotation angle sequence and the integration time.

[0110] The above embodiments are only for illustrating the technical concept and characteristics of the present application, and the purpose is to enable those skilled in the art to understand the content of the present application and implement it, and cannot limit the protection scope of the present application. Any equivalent transformation or modification made according to the spirit and essence of the present application should be covered within the protection scope of the present application.

Claims

1. A method for simulating the radiance of a lunar key exploration area, characterized in that, The method comprises the following steps: S1: determining a simulation spectrum range and a spectral resolution according to a load parameter; S2: obtaining lunar soil reflectance characteristics, surface terrain parameters, a solar incidence angle, and solar spectral irradiance information of a target region; S3: selecting a corresponding radiance calculation model according to the simulation spectrum range; S4: calculating spectral radiance of the target region at an actual observation time of the detection load based on the radiance calculation model and the obtained information; S5: calculating a signal-to-noise ratio of target detection according to target spectral radiance, load optical efficiency, detector parameters, and system noise; S6: iteratively calculating spectral radiance and detection signal-to-noise ratio of the same target under different orbits, comparing them, and selecting a suitable detection orbit and detection time.

2. The method according to claim 1, wherein, In the step S3, when the simulation spectrum range is a visible short-wave infrared spectrum range, a radiance calculation model that only considers lunar soil reflection of solar radiation is selected; the wavelength range of the visible short-wave infrared spectrum range is 0.35 μm to 2.2 μm.

3. The method according to claim 2, wherein, The radiance calculation model that only considers lunar soil reflection of solar radiation is shown in the following formula: In the step S3, when the simulation spectrum range is a medium-long-wave infrared spectrum range, a radiance calculation model that considers both solar radiation reflection and lunar soil self-radiation is selected; the wavelength of the medium-long-wave infrared spectrum range is greater than 2.2 μm. For example, the wavelength of the reflected light can be 550 nm. The reflected light spectrum radiance of the lunar soil at the location; For example, the wavelength is The bidirectional reflectance distribution function at the point is determined by the lunar soil properties and the observation geometry. For, wavelength is At the angle of incidence of the sun Spectral irradiance under the following conditions; is the angle of incidence of the sunlight; is the angle of reflection; is the phase angle of the reflected and incident light.

4. The method according to claim 3, wherein, The lunar surface spectral radiance calculation model that considers both solar radiation reflection and lunar soil self-radiation is characterized by calculating the lunar surface spectral radiance through the following formula:

5. The method according to claim 4, wherein, In the step S2, the lunar soil reflectance characteristics are bidirectional reflectance characteristics of actual target lunar soil; the surface terrain parameters are obtained through point cloud data of the target region; the solar incidence angle is determined through target point load transit time, target latitude and longitude, and other parameters; and the solar spectral irradiance is obtained through convolution according to the spectral resolution of the load. In the step S5, the signal-to-noise ratio of target detection is calculated according to the following formula: For example, the total spectral radiance at the wavelength of 550 nm is the total spectral radiance at the wavelength of 550 nm is B is the spectral radiance of the lunar soil reflecting solar radiation; The spectral radiance of the lunar soil's own radiation is calculated from the following equation: τ For, wavelength is Spectral emissivity of lunar soil at that location; B is the blackbody spectral radiance based on Planck's law, T T is the lunar soil temperature in Kelvin, calculated using a one-dimensional heat conduction equation.

6. The method according to claim 1, wherein, θ 7. The method according to claim 1, wherein, ρ The target radiation power received by the detector is calculated from the detected solar radiation reflected from the lunar surface according to the formula : wherein, is the solar irradiance spectrum at the lunar surface, τ a is the lunar atmospheric transmittance, λ is the solar elevation angle, η is the lunar surface albedo, λ o is the optical efficiency, A d is the detector photosurface area, F# is the optical system parameter; According to the target radiation power, the effective number of signal electrons generated by the target signal on the detector unit is calculated as N s ( λ ): wherein T int is the integration time of the detector, λ SNR is the quantum efficiency, E ph λ is the energy of a single photon;​​ According to the effective signal electrons, the signal-to-noise ratio is calculated as follows λ ( λ ): in, n read This refers to the readout noise of the detector. N back ( Nn () represents the number of background electrons introduced by background radiation. N dark ( λ () represents the number of electrons introduced by the detector's dark current. In the step S6, the selected suitable detection orbit represents an optimal orbit in the simulation results of radiance and signal-to-noise ratio of the same target region under different orbits, and the optimal orbit is the orbit with the highest value; the selected suitable detection time corresponds to a detection time that can meet the target region coverage requirement under the same orbit considering motion compensation along the orbit duty cycle, and the detection time includes a start detection time and an end detection time; and the orbit spatial duty cycle is a ratio of a detection region to a flight region. ( The calculated spectral radiance and signal-to-noise ratio are used to determine a motion compensation parameter of a high-resolution imaging spectrometer; the motion compensation parameter includes a pointing mirror rotation angle sequence and an integration time. The number of noise electrons is calculated based on a typical noise electron model.

8. The method according to claim 1, wherein, The method comprises the following steps: A determination unit is configured to determine a simulation spectrum range according to a load parameter; 9. A device for applying the method of simulating the brightness of a lunar key area according to any one of claims 1 to 8, characterized in that, An acquisition unit is configured to obtain lunar soil reflectance characteristics, surface terrain parameters, a solar incidence angle, and solar spectral irradiance information of a target region; A selection unit is configured to select a corresponding radiance calculation model according to the simulation spectrum range; and ​ ​ The first computing unit is configured to calculate the spectral radiance of the target region at an actual observation time of the detection load based on the radiance calculation model and the obtained information. The second computing unit is configured to calculate the signal-to-noise ratio of the target detection in combination with the load optical efficiency, the detector parameter and the system noise. The third computing unit is configured to calculate the temperature of the lunar surface target region by using a one-dimensional heat conduction equation. The first computing unit is further configured to substitute the temperature into the radiance calculation model to calculate the lunar soil self-radiation.

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