Automatic planning device for on-orbit observation mode of solar reflection band hyperspectral imager

Abstract

The invention provides an automatic planning device for an on-orbit observation mode of a solar reflection band hyperspectral imager, and relates to the technical field of satellite remote sensing, and the device comprises a track forecast analysis module, an observation mode priority ranking module, an observation target combination module, a control instruction generation module and an instruction verification and uploading module. The method comprises the following steps: reading and analyzing a satellite orbit forecasting file to obtain orbit forecasting information of a satellite under a geocentric inertial system, and calculating a view field angle and a position parameter of an observation target in combination with an instrument installation coordinate; dynamically adjusting the priority of an observation task according to the function composition of a preset earth-moon observation mode and a self-calibration mode, an observation period and a satellite sudden interruption event; and calling a preset observation target combination rule, generating an instrument maneuvering control instruction and an observation duration control instruction, performing integrity verification on an instruction sequence, and injecting the verified instruction into an instrument execution controller through an instruction upper injector, so that automatic arrangement and generation of the instruction sequence can be realized.

Description

Technical Field

[0001] The present invention relates to the field of satellite remote sensing technology, and in particular to an automatic planning device for an on-orbit observation mode of a solar reflection band hyperspectral imager. Background Art

[0002] To measure the reflected flux of sunlight incident on Earth, cloud and aerosol properties, surface reflectivity, and other information crucial to climate intensity, response, and feedback, a remote sensing satellite must carry a hyperspectral imager capable of measuring Earth-reflected solar radiation with an accuracy of 0.3% (k = 2). This hyperspectral imager calculates Earth reflectivity by measuring the Earth's radiance spectrum and the solar irradiance spectrum. The Sun is used as an on-orbit radiation calibration source for reflectivity measurements, and the reflectivity is traced back to the International System of Units (SI) unit of power, the watt, using the solar irradiance spectrum measured by a solar total irradiance reference spectrometer. Because sunlight intensity in space is too high, instruments generally cannot observe the Sun directly. Instead, sunlight must be attenuated by an attenuator (aperture or filter) before being directed into the instrument. To calibrate the instrument's linear responsivity on-orbit, the attenuator must be configured with different attenuation levels. Therefore, the attenuator is typically a wheel-like structure equipped with a through hole (no attenuation) and attenuation plates with different attenuation coefficients. The attenuation plate wheel rotates to move the attenuation plates of different levels into and out of the imager's aperture. Furthermore, as a high-precision imager, its primary function is to transfer its own radiometric calibration accuracy to other satellite remote sensing instruments operating in the solar reflectance band, using pseudo-invariant surrogate calibration sources such as stable Earth targets and the Moon as intermediaries, through inter-satellite sub-satellite cross-calibration. Finally, to perform high-precision radiometric calibration on raw measurement data from in-orbit observations of targets such as the Earth, Sun, and Moon, it is necessary to immediately observe deep, cold space (referred to as "cold space") to obtain the instrument's dark background level after completing observations of various targets.

[0003] Since remote sensing instruments that observe global cloud and aerosol properties and surface reflectance are typically deployed in sun-synchronous orbits (such as Aqua / MODIS, Landsat / OLI, and Sentinel-2 / MSI), deploying a hyperspectral imager on an inclined orbit greatly increases the chances of cross-calibration with the sub-satellite points of these remote sensing instruments, which are used for radiometric calibration. However, satellites operating on inclined orbits are subject to a variety of complex factors, causing their orbital characteristics to change. Firstly, the satellite's orbital altitude gradually decreases due to factors such as atmospheric drag and Earth's gravitational perturbations. To ensure long-term stable operation, regular orbit adjustments (such as raising the orbital altitude) are necessary. Secondly, remote sensing satellites need to maintain internal thermal stability, and heat dissipation surfaces are typically installed on one side of the satellite. However, in inclined orbits, the solar illumination angle is not fixed on the same side of the orbital plane, but rather appears on both sides of the satellite over time. When the illumination angle changes and the sun hits the heat dissipation surface, it affects the satellite's heat dissipation and thermal stability. Therefore, the satellite must maneuver according to the changing solar azimuth angle (β angle) to avoid this situation.

[0004] In summary, due to the diverse observation targets and complex observation modes of hyperspectral imagers, as well as the harsh operating conditions of inclined orbits, it is necessary to configure and install an on-orbit automatic observation mode planning device that combines the observation function requirements of satellite instruments with the constraints of orbital environmental conditions. This device is primarily responsible for formulating and generating multi-target, multi-mode observation instructions, and rationally scheduling tasks based on observation task priorities and the collaborative relationships between observation targets to maximize observation efficiency.

[0005] Traditional satellite command operation relies primarily on manual command injection as the satellite passes over ground tracking and control stations. Since sun-synchronous satellites typically have relatively simple observation modes and highly regular instrument movements, manual command generation and injection are sufficient for scenarios with simple observation modes and low injection frequency. However, this manual approach presents significant limitations when faced with multi-target, multi-mode observation missions for hyperspectral imagers. Constrained by satellite orbital conditions, a single instrument observation mode may consist of multiple target observations, often with complex collaborative relationships between these targets. For example, cold-sky observation data is the basis for radiometric calibration or analysis of Earth-Moon target observation data. This requires timely switching of attenuator filters to observe cold-sky data before and after Earth-Moon observation missions. This requires an observation mode planning device to intelligently generate command sequences to control instrument operations based on task priorities and the inherent logical relationships between target collaborations. However, manual command injection is not only prone to human error when handling such highly complex and dynamically changing task scheduling requirements, but is also inefficient when processing large numbers of commands and complex task logic.

[0006] Existing satellite observation missions typically rely on manual planning and command generation. This approach is inefficient, error-prone, and lacks flexibility when handling multi-target, multi-mode observation missions. In particular, the diversity of targets and complexity of observation modes in hyperspectral imager observation missions make manual planning difficult to meet real-time and accuracy requirements. Therefore, a device that can automatically plan observation modes and generate observation commands is urgently needed to improve observation efficiency and system reliability. Summary of the Invention

[0007] In view of this, the purpose of the present invention is to propose an automatic planning device for on-orbit observation modes of a solar reflection band hyperspectral imager ("hyperspectral imager" for short), so as to realize the automatic arrangement and generation of instruction sequences under the conditions of multiple observation modes and multiple observation target combinations of the instrument. The device of the present invention can calculate the observation angles and observation positions of different targets within the instrument's field of view through orbit prediction combined with the installation coordinates of the instrument on the satellite, and determine the observation mode and the corresponding observation target combination according to the instrument's mission requirements. The device is automatically timed and started every day by a computer controller. Since satellites in low-orbit inclined orbits are subject to greater atmospheric resistance, there are large errors in the satellite orbit position forecast. Therefore, the frequency of orbit forecast updates needs to be increased, and the corresponding mode automatic planning device also needs to calculate and generate instruction sequences according to a recursive strategy every day.

[0008] To achieve the above object, the present invention provides the following technical solutions:

[0009] Based on the above objectives, in a first aspect, the present invention provides an automatic planning device for on-orbit observation mode of a solar reflection band hyperspectral imager, comprising the following modules:

[0010] Orbit prediction and analysis module: used to regularly read and analyze satellite orbit prediction files, obtain orbit prediction information of satellite position, speed, time and maneuvering status in the geocentric inertial system, and calculate the field of view angle and position parameters of the observed target based on the instrument installation coordinates;

[0011] Observation mode priority sorting module: built-in priority rules for Earth-Moon observation mode and self-calibration mode, dynamically adjusts the observation task priority according to the functional composition, observation cycle and sudden satellite interruption events of the preset Earth-Moon observation mode (A-1 to A-4) and self-calibration mode (B-1 to B-4);

[0012] Observation target combination module: used to call preset observation target combination rules according to different observation modes;

[0013] Control command generation module: Calculates the observation time window, turntable azimuth and pitch angle parameters based on the orbit geometry model, and generates instrument maneuver control commands and observation duration control commands;

[0014] Instruction verification and injection module: uses cyclic redundancy check (CRC) to verify the integrity of the instruction sequence, and injects the verified instructions into the instrument execution controller through the instruction injector.

[0015] As a further solution of the present invention, in the observation mode priority sorting module:

[0016] The priority rule for Earth-Moon observation modes is: pseudo-invariant target observation mode (A-1) > intersatellite cross calibration mode (A-2) > solar spectrum irradiance observation and on-orbit tracing mode (A-3) > Earth patrol mode (A-4);

[0017] The priority of the self-calibration modes is: attenuator attenuation coefficient self-test mode (B-1) > instrument linear response test mode (B-2) > instrument field of view homogenization mode (B-3) > spectrum center wavelength test mode (B-4);

[0018] When the self-calibration mode is triggered, it takes priority over all Earth-Moon observation modes.

[0019] As a further solution of the present invention, the Earth-Moon observation modes are arranged in descending order of priority as follows: pseudo-invariant target observation mode, intersatellite cross-calibration mode, solar spectrum irradiance observation and on-orbit tracing mode, and ground patrol mode.

[0020] As a further solution of the present invention, the observation target combination rule includes:

[0021] In the pseudo-invariant target observation mode, site tracking observation, solar spectrum irradiance observation and instrument dark background observation are combined;

[0022] In the self-calibration mode, the solar spectrum data is observed by the dual rotating attenuation wheel combination to generate attenuation coefficient and response linearity test instructions.

[0023] As a further solution of the present invention, the self-calibration modes are arranged in descending order of priority as follows: attenuator attenuation coefficient self-test mode, instrument linear response test mode, instrument field of view homogenization mode, and spectrum center wavelength test mode.

[0024] As a further solution of the present invention, the pseudo-invariant target observation mode in the observation target combination module includes:

[0025] Site replacement calibration mode: Select a stable area such as the Dunhuang radiation calibration site or the Libyan desert to conduct earth observations in that area, and combine solar spectral irradiance observations with dark background data to complete the ground data radiation calibration and emissivity calculation, and generate a reference dataset for radiation calibration transfer;

[0026] Lunar observation mode: During a specific lunar phase, lunar spectral irradiance observations are combined with solar spectral irradiance observations to calculate the lunar albedo and use it as a lunar reference dataset for radiometric calibration.

[0027] Intersatellite cross calibration mode: Based on the orbital parameters of the satellite where the hyperspectral imager is located and the satellite to be compared, the temporal and spatial parameters of the sub-satellite point crossing event of the two satellites are predicted and the satellite where the imager is located is guided to conduct maneuverable observation of the ground.

[0028] As a further solution of the present invention, in the control instruction generation module, the sun / moon observation instruction parameters include the turntable azimuth and pitch angle; the earth observation instruction parameters include restrictions including the sub-satellite point position, observation time window and field of view coverage.

[0029] As a further solution of the present invention, in the instruction verification and injection module, sequential logic is used to verify the physical feasibility of the observation instruction, including the matching of the turntable maneuvering time and the observation duration.

[0030] As a further solution of the present invention, the automatic planning device for on-orbit observation mode of the solar reflection band hyperspectral imager further includes:

[0031] Self-calibration mode trigger mechanism: Dynamically generates self-calibration task trigger instructions based on periodic observation rules of self-calibration parameters such as instrument attenuation characteristics and detector response uniformity;

[0032] Emergency interrupt response module: When the satellite performs maneuvers, it terminates the current observation mission and replans the remaining command sequences.

[0033] As a further solution of the present invention, the automatic planning device for the on-orbit observation mode of the solar reflection band hyperspectral imager updates the orbit forecast data daily through a recursive strategy, with an update frequency of not less than once every 6 hours, to ensure the calculation accuracy of the observation angle under the inclined orbit.

[0034] As a further solution of the present invention, the observation target combination module supports various target observations and complex observation combinations included in the two major observation modes of hyperspectral imager instrument self-calibration and Earth-Moon observation.

[0035] Compared with the prior art, the automatic planning device for on-orbit observation mode of a solar reflection band hyperspectral imager proposed in the present invention has the following beneficial effects:

[0036] 1. The present invention uses an orbit prediction analysis module to calculate satellite positions and target field of view angles in real time, and combines this with a dynamic priority sorting mechanism to achieve automated scheduling of multi-mode observation tasks, effectively solving the problems of low efficiency and poor flexibility in manual instruction generation.

[0037] 2. The present invention also integrates a self-calibration mode trigger mechanism, which observes solar spectrum data through a dual-rotating attenuation wheel combination, dynamically monitors the instrument's attenuation characteristics and response linearity, ensures the stability of the instrument's attenuator characteristics and radiation calibration performance, and supports the SI traceability of solar spectrum irradiance and the transfer of Earth observation radiation calibration.

[0038] 3. The present invention targets multiple target observations and complex combinations of multiple targets involved in two major observation modes: hyperspectral imager instrument self-calibration and Earth-Moon observations. It combines the orbital constraints of multiple target observation combinations, dynamically plans the optimal observation time window, avoids waste of energy and storage resources, and optimizes the multi-target collaborative observation capability.

[0039] 4. The present invention's built-in command verification module uses cyclic redundancy checks (CRCs) and sequential logic verification to ensure functional compatibility of turntable maneuver time and observation duration, effectively reducing command conflict rates. When a satellite platform maneuver occurs, the emergency interrupt response module aborts the current mission and replans the remaining command sequence, maximizing the safety of the instrument's on-orbit operation. Regularly updating orbital prediction data based on a recursive strategy ensures the accuracy of the instrument's observation targets and the long-term stability of the observation data in inclined orbits, providing a reliable dataset for high-precision SI traceability and radiation calibration transfer of solar reflected radiation.

[0040] In summary, the automatic planning device for the on-orbit observation mode of the solar reflection band hyperspectral imager of the present invention significantly improves the accuracy and execution efficiency of the imager's on-orbit observation task planning through core technologies such as automated observation planning, multi-target collaborative observation, and high robustness verification.

[0041] These and other aspects of the present application will be more clearly understood in the following description of the embodiments. It should be understood that the above general description and the following detailed description are merely exemplary and explanatory and cannot limit the present application. BRIEF DESCRIPTION OF THE DRAWINGS

[0042] In order to more clearly illustrate the technical solutions in the embodiments of the present invention or related technologies, the following briefly introduces the drawings required for the exemplary embodiments or related technical descriptions. The drawings are used to provide a further understanding of the present invention and constitute part of the specification. Together with the embodiments of the present invention, they are used to explain the present invention and do not constitute a limitation of the present invention. In the drawings:

[0043] Figure 1 This is a workflow diagram of an automatic planning device for an on-orbit observation mode of a solar reflection band hyperspectral imager according to an embodiment of the present invention.

[0044] Figure 2The present invention is a schematic diagram of an on-orbit working mode of a solar reflection band hyperspectral imager in an automatic on-orbit observation mode planning device for a solar reflection band hyperspectral imager according to an embodiment of the present invention.

[0045] Figure 3 This is a schematic diagram of the observation target combination included in the site replacement calibration mode in the automatic planning device for on-orbit observation mode of a solar reflection band hyperspectral imager according to an embodiment of the present invention.

[0046] Figure 4 This is a schematic diagram of the combination of observation targets included in the lunar observation mode in an automatic planning device for on-orbit observation modes of a solar reflection band hyperspectral imager according to an embodiment of the present invention.

[0047] Figure 5 This is a schematic diagram of the observation target combination included in the intersatellite cross-calibration mode in an automatic planning device for on-orbit observation mode of a solar reflection band hyperspectral imager according to an embodiment of the present invention.

[0048] Figure 6 This is a schematic diagram of the combination of solar spectral irradiance observation and observation targets included in the on-orbit tracing mode in an automatic planning device for on-orbit observation mode of a solar reflection band hyperspectral imager in an embodiment of the present invention.

[0049] Figure 7 This is a schematic diagram of the combination of observation targets included in the ground inspection observation mode in an automatic planning device for on-orbit observation modes of a solar reflection band hyperspectral imager according to an embodiment of the present invention.

[0050] Figure 8 This is a schematic diagram of an observation target combination included in an attenuator attenuation coefficient self-check mode in an automatic planning device for an on-orbit observation mode of a solar reflection band hyperspectral imager according to an embodiment of the present invention.

[0051] Figure 9 This is a schematic diagram of an observation target combination included in an instrument response linearity self-check mode in an automatic planning device for an on-orbit observation mode of a solar reflection band hyperspectral imager according to an embodiment of the present invention.

[0052] Figure 10 This is a schematic diagram of the observation target combination included in the instrument field of view homogenization mode in an automatic planning device for on-orbit observation mode of a solar reflection band hyperspectral imager in an embodiment of the present invention.

[0053] Figure 11 This is a schematic diagram of the observation target combination included in the spectral center wavelength self-check mode in an automatic planning device for on-orbit observation mode of a solar reflection band hyperspectral imager according to an embodiment of the present invention.

[0054] Figure 12This is a schematic diagram of a template for generating instrument maneuver control instructions in an automatic planning device for an on-orbit observation mode of a solar reflection band hyperspectral imager according to an embodiment of the present invention.

[0055] Figure 13 This is a schematic diagram of a template for generating instrument observation duration control instructions in an automatic planning device for an on-orbit observation mode of a solar reflection band hyperspectral imager according to an embodiment of the present invention.

[0056] Figure 14 This is a flowchart for generating instructions for timing execution in an automatic planning device for an on-orbit observation mode of a solar reflection band hyperspectral imager according to an embodiment of the present invention.

[0057] Figure 15 This is a flowchart of generating schedule execution instructions in an automatic planning device for an on-orbit observation mode of a solar reflection band hyperspectral imager according to an embodiment of the present invention.

[0058] Figure 16 This is a schematic diagram of an instruction template in an automatic planning device for an on-orbit observation mode of a solar reflection band hyperspectral imager according to an embodiment of the present invention.

[0059] Figure 17 This is a structural block diagram of an automatic planning device for an on-orbit observation mode of a solar reflection band hyperspectral imager according to an embodiment of the present invention. DETAILED DESCRIPTION

[0060] Below, the present application is further described in conjunction with the accompanying drawings and specific implementation methods. It should be noted that, under the premise of no conflict, the various embodiments or technical features described below can be arbitrarily combined to form new embodiments.

[0061] To make the purpose, technical solutions and advantages of the present invention more clearly understood, the following is a further detailed description of the embodiments of the present invention in conjunction with specific embodiments and with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are only used to explain the present application and are not intended to limit the present application.

[0062] It should be noted that all expressions using "first" and "second" in the embodiments of the present invention are intended to distinguish two non-identical entities or non-identical parameters with the same name. Therefore, "first" and "second" are used for convenience of expression only and should not be understood as limitations on the embodiments of the present invention. In addition, the terms "including" and "having" and any variations thereof are intended to cover non-exclusive inclusions, for example, other steps or units inherent to a process, method, system, product, or device that includes a series of steps or units.

[0063] The following will be combined with the drawings in the embodiments of this application to clearly and completely describe the technical solutions in the embodiments of this application. Obviously, the embodiments described are part of the embodiments of this application, not all of them. Based on the embodiments in this application, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of this application.

[0064] The flowcharts shown in the accompanying drawings are for illustrative purposes only and do not necessarily include all contents and operations / steps, nor must they be executed in the order described. For example, some operations / steps may be decomposed, combined, or partially merged, so the actual execution order may vary depending on the actual situation.

[0065] The following describes some embodiments of the present application in detail with reference to the accompanying drawings. In the absence of conflict, the following embodiments and features therein may be combined with each other.

[0066] The existing method of manually compiling and uploading satellite observation instructions suffers from inefficiency, error-proneness, and lack of flexibility when handling multi-target, multi-mode observation missions for hyperspectral imagers. This invention proposes an automatic on-orbit observation mode planning device for a solar reflection band hyperspectral imager. Based on the priority of the observation mission, the observation targets to be combined with the observation mode, and the timing logic for the coordinated observation targets, the device automatically compiles and generates observation instruction sequences for the imager, subject to orbital environmental conditions and satellite maneuvering state instructions. After a correctness self-check, the device injects these into the instrument execution controller. The device of the present invention is capable of automatically compiling and generating instruction sequences for the instrument's multiple observation modes and multiple observation target combinations. The device calculates the observation angles and positions of different targets within the instrument's field of view using orbital predictions combined with the instrument's installation coordinates on the satellite, determining the observation mode and corresponding observation target combination based on the instrument's mission requirements. The device of the present invention is automatically timed and activated daily by a computer controller. Because satellite orbit position forecasts in inclined orbits have significant errors, the forecast update frequency needs to be increased (e.g., every six hours). Therefore, the automatic mode planning device also needs to calculate and generate instruction sequences daily using a recursive strategy.

[0067] See also Figures 1 to 17 As shown, an embodiment of the present invention provides an automatic planning device for on-orbit observation mode of a solar reflection band hyperspectral imager, comprising the following modules:

[0068] Orbit prediction and analysis module: used to regularly read and analyze satellite orbit prediction files, obtain orbit prediction information of satellite position, speed, time and maneuvering status in the geocentric inertial system, and calculate the field of view angle and position parameters of the observed target based on the instrument installation coordinates;

[0069] Observation mode priority sorting module: built-in priority rules for Earth-Moon observation mode and self-calibration mode, dynamically adjusts the observation task priority according to the functional composition, observation cycle and sudden satellite interruption events of the preset Earth-Moon observation mode (A-1 to A-4) and self-calibration mode (B-1 to B-4);

[0070] Observation target combination module: used to call preset observation target combination rules according to different observation modes;

[0071] Control command generation module: Calculates the observation time window, turntable azimuth and pitch angle parameters based on the orbit geometry model, and generates instrument maneuver control commands and observation duration control commands;

[0072] Instruction verification and injection module: uses cyclic redundancy check (CRC) to verify the integrity of the instruction sequence, and injects the verified instructions into the instrument execution controller through the instruction injector.

[0073] See also Figure 1 As shown, the overall workflow of the automatic planning device for on-orbit observation mode of the solar reflection band hyperspectral imager of the present invention is as follows:

[0074] The orbit predictor periodically reads and parses the orbit prediction file, inputs the orbit prediction file (the read satellite position, speed, and time), the observation mode priority sorting (executed according to the priority sorting rules), and the observation mode target combination. Based on the input of the above orbit prediction file, it will predict that the instrument will turn to a specific angle at a specific time to observe the specified target. Based on this, the instrument's maneuvering control instructions and instrument observation time control instructions are generated. The instructions are combined and merged and then verified to generate an instruction list. The instructions are injected through the instruction injector, and the instrument performs observations according to the instructions.

[0075] In this embodiment, in the observation mode priority sorting module:

[0076] The priority rule for Earth-Moon observation modes is: pseudo-invariant target observation mode (A-1) > intersatellite cross calibration mode (A-2) > solar spectrum irradiance observation and on-orbit tracing mode (A-3) > Earth patrol mode (A-4);

[0077] The priority of the self-calibration modes is: attenuator attenuation coefficient self-test mode (B-1) > instrument linear response test mode (B-2) > instrument field of view homogenization mode (B-3) > spectrum center wavelength test mode (B-4);

[0078] When the self-calibration mode is triggered, it takes priority over all Earth-Moon observation modes.

[0079] Specifically, when reading and parsing orbit prediction files, the computer of the observation mode automatic planning device generates instructions for a permanent background process to periodically read and parse the orbit prediction files. The orbit prediction information primarily includes the satellite's position, velocity, time, and satellite maneuver status indicator in the Earth-centered inertial system. When prioritizing observation modes, a hyperspectral imager is not a conventional Earth observation remote sensing instrument. Its primary function is to self-verify its own radiometric calibration accuracy on-orbit and trace the Earth's reflectivity to the International System of Units (SI) power unit, Watt, using the solar reference spectral irradiance. Secondly, the imager's radiometric calibration accuracy is transferred to other remote sensing instruments that lack SI-traceability through inter-satellite cross-calibration techniques or pseudo-invariant target-based alternative calibration techniques. Furthermore, the hyperspectral imager's inherent characteristics related to the instrument's radiometric calibration accuracy and SI traceability uncertainty, such as the attenuator attenuation characteristics, detector response linearity, detector response uniformity, and spectral calibration stability, also require regular on-orbit self-verification and self-calibration. Therefore, the observation mode of the imager is divided into Earth-Moon observation mode and self-calibration mode according to its functional composition and observation period. Figure 2 Among them, the Earth-Moon observation mode is daily observation, and the priority is sorted from high to low as follows:

[0080] A-1. Pseudo-invariant target observation mode (including the site replacement calibration mode based on the Earth-stable target and the lunar observation mode);

[0081] A-2. Intersatellite cross calibration mode;

[0082] A-3. Solar spectral irradiance observation and on-orbit tracing mode;

[0083] A-4. Ground patrol mode;

[0084] The instrument self-calibration mode is a periodic observation (e.g. once a month), and the priority is ranked from high to low as follows:

[0085] B-1. Attenuator attenuation coefficient self-test mode;

[0086] B-2. Instrument linear response test mode;

[0087] B-3. Instrument field of view homogenization mode;

[0088] B-4. Spectral center wavelength test mode.

[0089] In addition, since the self-calibration of the instrument's inherent characteristics is the basis for maintaining the imager's radiation calibration accuracy and calibration stability, when the opportunity arises to carry out self-calibration, the self-calibration mode has a higher priority than the Earth-Moon observation mode.

[0090] Therefore, the observation mode automatic planning device needs to have the above-mentioned observation modes and their priority codes built in, and then plan and sort the priorities of the observation modes actually executed every day in combination with the satellite orbit forecast information and the observation target observation timing constraints.

[0091] In this embodiment, the Earth-Moon observation modes are arranged in descending order of priority as follows: pseudo-invariant target observation mode, intersatellite cross calibration mode, solar spectrum irradiance observation and on-orbit tracing mode, and ground patrol mode.

[0092] Among them, the observation target combination rules include:

[0093] In the pseudo-invariant target observation mode, site tracking observation, solar spectrum irradiance observation and instrument dark background observation are combined;

[0094] In the self-calibration mode, the solar spectrum data is observed by the dual rotating attenuation wheel combination to generate attenuation coefficient and response linearity test instructions.

[0095] In this embodiment, the self-calibration modes are arranged in descending order of priority as follows: attenuator attenuation coefficient self-test mode, instrument linear response test mode, instrument field of view homogenization mode, and spectrum center wavelength test mode.

[0096] In this embodiment, the pseudo-invariant target observation mode in the observation target combination module includes:

[0097] Site replacement calibration mode: Select a stable area such as the Dunhuang radiation calibration site or the Libyan desert to conduct earth observations in that area, and combine solar spectral irradiance observations with dark background data to complete the ground data radiation calibration and emissivity calculation, and generate a reference dataset for radiation calibration transfer;

[0098] Lunar observation mode: During a specific lunar phase, lunar spectral irradiance observations are combined with solar spectral irradiance observations to calculate the lunar albedo and use it as a lunar reference dataset for radiometric calibration.

[0099] Intersatellite cross calibration mode: Based on the orbital parameters of the satellite where the hyperspectral imager is located and the satellite to be compared, the temporal and spatial parameters of the sub-satellite point crossing event of the two satellites are predicted and the satellite where the imager is located is guided to conduct maneuverable observation of the ground.

[0100] In this embodiment, when the observation mode targets are combined, each observation mode is composed of multiple observation targets. Therefore, the observation mode automatic planning device performs different observation target combinations according to different observation modes, and then calls the orbit geometry model to calculate the observation angles and observation positions of different observation targets, and generates instrument maneuvering control instructions and observation time control instructions.

[0101] In this embodiment, in the control instruction generation module, the sun / moon observation instruction parameters include the turntable azimuth and pitch angle; the earth observation instruction parameters include restrictions including the sub-satellite point position, observation time window and field of view coverage.

[0102] In this embodiment, in the instruction verification and injection module, sequential logic is used to verify the physical feasibility of the observation instruction, including the matching of the turntable maneuvering time and the observation duration.

[0103] In this embodiment, the observation target combinations corresponding to various observation modes are described as follows:

[0104] A-1 Pseudo-invariant target observation mode:

[0105] (1) Site replacement calibration model.

[0106] The site-bypass calibration model selects several regions on Earth with stable surface properties (such as the Dunhuang Radiation Calibration Field in China and the Libyan Desert) as radiometric calibration transfer media. Using the imager's high radiometric calibration accuracy as a reference and field measurement data with known / measurable radiometric information as an intermediary, the field observation data of the imager and the instrument under test are compared with the intermediary data, thereby achieving a mutual comparison between the radiometric calibration accuracy of the instrument under test and that of the imager. Because the imager's radiometric calibration accuracy is self-verified and traceable to the SI reference, a radiometric calibration transfer relationship is indirectly established from the SI reference source to the instrument under test (i.e., the deviation and uncertainty between the instrument's radiometric calibration value and the true measurement value are obtained). Compared to sub-satellite cross-calibration, site-bypass calibration has lower requirements on the spatiotemporal geometry of the imager and instrument under test observing the same site. Compared to sub-satellite cross-calibration, site-bypass calibration has more relaxed requirements on observation time difference, pointing error, and projection footprint matching error. However, the use of field measurement data as intermediary data increases the length of the radiometric calibration transfer link and may introduce new uncertainties.

[0107] Since the site replacement calibration uses the earth reflectivity after the imager radiometric calibration as the reference source, and the site observation area is relatively limited (such as the Dunhuang radiation calibration field), the imager's two-dimensional pointing mechanism is required to track and observe the site target to accumulate observation samples. The radiometric calibration and calculation of the earth reflectivity of the site observation data require the observation of the instrument dark background and solar spectral irradiance. Therefore, the observation mode automatic planning device needs to combine the three observation targets of site tracking observation, solar spectral irradiance observation and instrument dark background observation for this mode, such as Figure 3As shown, the system generates control instructions for the two-dimensional pointing mechanism to point toward each target. For field tracking observations, the satellite's start and end times and effective tracking angles for passing over the stable target are calculated using orbit prediction files and the designated Earth stable target region. For solar spectrum irradiance observations, a diffuse transmission plate of the attenuator is inserted into the imager's aperture to prevent direct sunlight from damaging the instrument's optical components or detectors. For instrument dark background observations, the attenuator's maximum level of attenuation is inserted, and the instrument's aperture is pointed toward cold sky.

[0108] Among them, the reference earth stable target area delineated by the hyperspectral imager in the field alternative calibration mode observation is shown in Table 1. The relevant information is stored in the observation mode automatic planning device in the form of a pre-made list static template for command arrangement and use.

[0109] Table 1. Scope of the Earth Stability Target Point Area

[0110]

[0111] (2) Lunar observation mode.

[0112] Similar to the field replacement calibration mode, the lunar observation mode uses the Moon as a long-term, stable, on-orbit calibration source for remote sensing instruments operating in the solar reflectance band. During the hyperspectral imager radiometric calibration transfer process, the Moon serves as the radiometric calibration transfer medium, the imager's high radiometric calibration accuracy serves as a reference, and lunar irradiance model data simulating lunar phase observations serves as an intermediary. Lunar observation data from the imager and the instrument under test (DUT) at the same lunar phase are compared with the intermediary data. This allows for a mutual comparison of the DUT's radiometric calibration accuracy with the imager's, indirectly establishing a transfer relationship between the SI reference source based on lunar observations and the DUT. Because the Moon is the brightest and largest natural light source observable by humans besides the Sun, and observations of the Moon from space are unaffected by atmospheric absorption and scattering, using the Moon as a radiometric calibration transfer medium offers unique advantages compared to a stable Earth target. However, this requires the construction of a high-precision lunar irradiance model.

[0113] The lunar observation data needs to be calibrated for radiation and the lunar albedo needs to be calculated. Therefore, the observation mode automatic planning device needs to combine three observation targets for this mode: lunar spectrum irradiance observation, solar spectrum irradiance observation and instrument dark background observation, such as Figure 4 As shown, the system generates control instructions for the two-dimensional pointing mechanism to point to each target. In order to implement lunar observation, the orbit prediction file needs to include the calculation data of parameters such as the time, position and speed of the lunar observation in the geocentric ground coordinate system.

[0114] A-2. Intersatellite cross calibration mode.

[0115] Conducting inter-satellite sub-satellite cross-calibration is an important means of transferring the radiometric calibration accuracy of hyperspectral imagers to the instrument under test. When an imager and the instrument under test observe the same Earth scene through the same atmospheric path for a short period of time (e.g., 300 seconds), it is assumed that the atmospheric state and ground surface characteristics will not change significantly over such a short period. Theoretically, the observational data from both instruments will be consistent. Therefore, by directly comparing the Earth reflectance data from both instruments, the radiometric calibration accuracy of the instrument under test relative to the imager can be assessed. Similarly, because the radiometric calibration accuracy of the imager is self-checked and traceable to the SI reference source, a radiometric calibration transfer relationship from the SI reference source to the instrument under test is indirectly established.

[0116] The automatic planning device of observation mode needs to combine three observation targets: earth cross target observation, solar spectrum irradiance observation and instrument dark background observation for intersatellite cross calibration mode, such as Figure 5 As shown, the system generates control instructions for the two-dimensional pointing mechanism to point to each target. To observe targets that intersect the Earth, the orbit prediction file must include calculated data for the time, position, and angle of intersection between the instrument's satellite orbit and the imager's orbit. The file also controls the imager's two-dimensional pointing mechanism to point to the observation area on time.

[0117] A-3. Solar spectral irradiance observation and on-orbit tracing mode.

[0118] The hyperspectral imager conducts solar irradiance spectrum observation on orbit mainly to use the stable solar irradiance as a reference to verify the absolute accuracy and stability of its own radiation calibration. If the imager is equipped with an Electrical Substitution Radiometer (ESR), the absolute true value of the solar spectral irradiance can be measured independently by the thermoelectric power method. At this time, the observation mode automatic planning device only needs to control the imager and the electrical substitution radiometer to synchronously observe the sun to realize the solar spectral irradiance observation and on-orbit traceability; if the imager is not equipped with an electrical substitution radiometer, it cannot independently measure the absolute true value of the solar spectral irradiance. At this time, the observation mode automatic planning device needs to control the imager and the solar spectral irradiance reference instrument (such as TSIS / SIM) based on the orbital prediction information to carry out on-orbit solar synchronous observation activities, and trace its solar spectral irradiance observation data to the reference instrument. Therefore, the solar spectral irradiance observation and on-orbit traceability mode include two observation targets: solar spectrum collaborative observation and instrument dark background observation. Figure 6 shown.

[0119] A-4. Ground patrol observation mode.

[0120] During Earth-Moon observation activities, when there is no plan or opportunity to carry out observations such as radiation calibration transfer or solar spectrum irradiance tracing, the hyperspectral imager mainly conducts ground patrol observations of sub-satellite points. At this time, the observation mode automatic planning device controls the imager's two-dimensional pointing mechanism to point to the sub-satellite point to observe the Earth (it is also a protection mode to avoid the sun), and before the Earth observation starts to exit the Earth's shadow area or after the observation ends to enter the Earth's shadow area (depending on the imager's maneuverability), the solar spectrum irradiance and instrument dark background are observed in real time for radiation calibration and reflectivity calculation of Earth observation data. Therefore, the ground patrol observation mode includes observation targets such as Figure 7 shown.

[0121] In order to monitor and maintain the stability of the on-orbit performance of the hyperspectral imager and ensure the integrity of the on-orbit traceability link, the instrument needs to carry out self-calibration activities regularly during on-orbit operation to ensure the stability of the attenuation coefficient of each attenuator plate, the stability of the instrument response linearity, the relative uniformity of the detector spatial response, and the stability of the spectrometer dispersion characteristics. Among them, the attenuation coefficient of the attenuator plate is the most critical parameter to ensure the accuracy of solar spectrum irradiance measurement and the integrity of the traceability link. The present invention arranges the observation target combinations involved in the self-calibration mode instruction sequence of the observation mode automatic planning device as follows:

[0122] B-1. Attenuator attenuation coefficient self-test mode.

[0123] The accuracy of the attenuator's attenuation coefficients directly impacts the accuracy of on-orbit measurements of solar spectral irradiance. Therefore, pre-launch laboratory measurements require accurate measurement of the spectral attenuation coefficients of each attenuator in the solar reflection band. After the imager launches, the attenuation characteristics of the attenuators should theoretically remain consistent with pre-launch measurements. However, these characteristics may change due to changes in the space operating environment and the influence of cosmic rays. Therefore, the imager's on-orbit self-calibration begins with measuring the attenuation coefficients of the attenuators and comparing them with pre-launch measurements.

[0124] The on-orbit measurement of the attenuation coefficient of the attenuation plate adopts the observation data ratio method, that is, by rotating the wheel hole, the aperture with the attenuation plate installed and the through hole without the attenuation plate are respectively observed for the same radiation source, and then the spectral ratio is calculated to obtain the spectral attenuation coefficient of the attenuation plate.

[0125] To ensure that each attenuator aperture effectively observes the same radiation source, one approach is to install an artificial light source (such as a calibration lamp and integrating sphere) in orbit. However, due to the limited lifespan of calibration lamps and the difficulty in aligning their light spectrum with the solar spectrum, another approach is to use a dual-rotating attenuation disc wheel for solar observation. This involves installing two coaxially rotating discs and observing the sun through different combinations of attenuation disc apertures. In the attenuator's attenuation coefficient self-test mode, the outer disc of the dual-rotating attenuation disc wheel primarily performs dynamic radiation adjustment, setting the appropriate attenuation energy level to ensure that the first attenuated sunlight is effectively responded to after passing through both the inner disc aperture and the maximum attenuation disc aperture. Naturally, the attenuation discs in each of the inner disc apertures are the components whose attenuation coefficients require precise measurement.

[0126] According to the above principle, the observation mode automatic planning device calculates the accurate solar observation time according to the self-calibration mode plan schedule and orbit prediction file, drives the imager's two-dimensional pointing mechanism to stably point to the sun, and controls the inner and outer wheel holes of the attenuation plate wheel to observe the sun one by one, and calculates the attenuation coefficient of the attenuation plate based on the measurement data of each wheel hole. The observation target combination is as follows: Figure 8 shown.

[0127] B-2. Instrument response linearity self-test mode.

[0128] Ideally, a hyperspectral imager should be a linear response system, but actual instruments always exhibit more or less nonlinear response characteristics. Regular on-orbit testing of the stability of the instrument's response linearity is an important measure to ensure the accuracy and stability of radiometric calibration. The nonlinear response of the instrument is mainly manifested in:

[0129] ① The nonlinearity of the detector's response to different radiation energy levels at the same integration time;

[0130] ② The nonlinearity of the detector output for signals with different integration times at the same radiation energy level.

[0131] For the first type of nonlinear response, similar to the attenuation coefficient self-test mode, solar attenuation data can be measured using different attenuation plate combinations at a fixed integration time. For the second type of nonlinear response, a fixed attenuation plate level can be used to measure solar attenuation data at different integration times. Based on the combination of these two measurement methods, the linearity of the imager's instrument response during on-orbit operation can be analyzed and evaluated.

[0132] According to the above principle, the observation mode automatic planning device calculates the accurate solar observation time according to the self-calibration mode plan schedule and orbit prediction file, drives the imager's two-dimensional pointing mechanism to stably point to the sun, and controls the combination of the inner and outer wheel holes of the attenuation wheel and the detector integration time to observe the sun one by one. The observation target combination is as follows: Figure 9 shown.

[0133] B-3. Instrument field of view homogenization mode.

[0134] A hyperspectral imager is essentially an imaging spectrometer. Using a slit aperture, dispersive optics, and an array detector, it images the beam of light instantaneously focused on the slit onto an array detector. Therefore, the instantaneous field-of-view image reflects the spatial distribution of the scene in one dimension of the rectangular detector array (called the "spatial dimension"), while the spectral distribution of the scene in the other dimension (called the "spectral dimension"). The relative consistency of the instrument's radiometric calibration in these two detector dimensions is a key factor affecting data measurement accuracy and calibration stability.

[0135] In order to ensure the relative consistency of radiation calibration in the spatial and spectral dimensions, the imager needs to conduct regular field of view homogenization tests on the instrument while in orbit. The basic principle is to install a solar attenuation screen in front of the instrument (such as installing a solar diffuse transmission plate on the base of the instrument), and the observation mode automatic planning device drives the two-dimensional pointing mechanism to scan the attenuation screen at a uniform speed along the long side of the slit, so as to ensure that each detector in the spatial dimension can observe the same brightness area on the screen. Based on the short-term stability of the radiance of the same area of the attenuation screen during the scanning time, the relative calibration consistency of the instrument in the two dimensions (i.e., field of view homogenization) can be evaluated and corrected. The observation target combination is as follows: Figure 10 shown.

[0136] B-4. Spectral center wavelength self-test mode.

[0137] Spectral calibration accuracy is an important factor that characterizes the working performance of hyperspectral imagers and affects the accuracy of radiation calibration. Generally, the measurement and evaluation of the dispersion characteristics of the spectrometer are completed in a laboratory environment before launch through tunable laser frequency scanning. Due to satellite resource conditions such as volume, weight, and power consumption, it is usually impossible to configure an on-board laser frequency scanning device for the imager, and it is simplified to a small number of discrete lasers with monochromatic wavelengths. The imager indirectly evaluates the stability of the imager's spectral calibration by regularly observing the on-board laser and monitoring the changes in the central wavelength of the laser spectral image at each discrete wavelength. Therefore, the observation mode automatic planning device drives the two-dimensional pointing mechanism to point to the laser target, and controls the laser to open and close one by one to implement monochromatic laser observation. The observation target combination is as follows: Figure 11 shown.

[0138] In this embodiment, the automatic planning device for the on-orbit observation mode of the solar reflection band hyperspectral imager further includes:

[0139] Self-calibration mode trigger mechanism: Dynamically generates self-calibration task trigger instructions based on periodic observation rules of self-calibration parameters such as instrument attenuation characteristics and detector response uniformity;

[0140] Emergency interrupt response module: When the satellite performs maneuvers, it terminates the current observation mission and replans the remaining command sequences.

[0141] In this embodiment, after completing the observation mode priority sorting and observation target combination, the observation mode automatic planning device calculates the control information parameters such as the observation time and observation angle of each target according to the orbit prediction file. The information parameters are calculated as follows:

[0142] (1) Calculate the azimuth and elevation angles of the turntable of the solar / moon observation instrument of the solar reflection band hyperspectral imager.

[0143] Based on the orbit prediction file and the sun / moon vector broadcast by the satellite, the sun / moon vector position at the future time is calculated and converted into pitch angle and azimuth angle to control the turntable to point to the position. The specific calculation method is as follows:

[0144] The vector from the Earth to the Sun / Moon in the geocentric inertial coordinate system is known. After matrix transformation, the vector in the optical axis coordinate system can be obtained:

[0145]

[0146] Among them, the subscript optics is the optical axis coordinate axis, eci is the Earth-centered inertial coordinate system, orb is the orbit coordinate system, body is the satellite body coordinate system, inst is the instrument coordinate system, prism is the instrument prism coordinate system, and optics is the optical axis coordinate system; is the vector in the optical axis coordinate system, T eci2orb is the transformation matrix from the Earth-centered inertial coordinate system to the orbital coordinate system, T orb2body is the transformation matrix from the orbital coordinate system to the satellite body coordinate system, T body2inst is the transformation matrix from the satellite body coordinate system to the instrument coordinate system, T inst2prism is the transformation matrix from the instrument coordinate system to the instrument prism coordinate system, T prism2optics is the transformation matrix from the instrument prism coordinate system to the optical axis coordinate system.

[0147] The automatic observation mode planning device will determine whether the sun / moon enters the XOY plane of the optical axis coordinate system according to the observation mode and establish the recognition conditions:

[0148] α=arctan(r z / r x )<ε (2)

[0149] Among them, α is the pitch angle, and ε is the set threshold.

[0150] Calculate the azimuth angle β corresponding to the observation mode:

[0151] β=arctan(r y / r x ) (3)

[0152] Calculate observation time: When the pitch angle meets the set threshold conditions, the start time and end time that meet the conditions will be recorded as the target observation time in this observation mode.

[0153] (2) Calculate the azimuth and elevation angles of the turntable of the solar reflection band hyperspectral imager for earth observation.

[0154] According to the orbit prediction file, the position of the satellite passing through the Earth's stable target area in the future is calculated and converted into pitch angle and azimuth angle to control the turntable to point to the position. The specific calculation method is as follows:

[0155] The coordinate vector of the known earth-stabilized target in the Earth-centered Earth-fixed system Coordinate vector of the satellite in the Earth-centered Earth-fixed system Then the vector pointing from the satellite to the stable target on Earth can be expressed as:

[0156]

[0157] After matrix transformation, the vector in the instrument coordinate system can be obtained:

[0158]

[0159] Wherein, the subscript ecr is the Earth-centered Earth-fixed coordinate system, eci is the Earth-centered inertial coordinate system, orb is the orbit coordinate system, body is the satellite body coordinate system, inst is the instrument coordinate system, and cube is the instrument focal plane coordinate system; T ecr2eci is the transformation matrix from the Earth-centered Earth-fixed coordinate system to the Earth-centered inertial coordinate system, T eci2orb is the transformation matrix from the Earth-centered Earth-fixed coordinate system to the orbital coordinate system, T orb2body is the transformation matrix from the orbital coordinate system to the satellite body coordinate system, T body2inst is the transformation matrix from the satellite body coordinate system to the instrument coordinate system, T inst2cube is the transformation matrix from the instrument coordinate system to the instrument focal plane coordinate system.

[0160] The azimuth angle calculation formula is:

[0161]

[0162] The formula for calculating the pitch angle is:

[0163]

[0164] Observation time determination:

[0165] The coordinate vector of the known earth-stabilized target in the Earth-centered Earth-fixed system Then the longitude and latitude of the Earth's stable target can be expressed as

[0166]

[0167] Among them, the subscript lon is longitude, lat is latitude, r x is the x component of the Earth-centered Earth-fixed system, r y The y component of the Earth-centered Earth-fixed system, r z is the z component of the Earth-fixed system, e is the eccentricity, and a is the radius of the Earth.

[0168] The latitude and longitude range is filtered according to the threshold range of the earth stable target point, and the start time and end time that meet the filtering conditions are recorded as the observation time of the earth stable target point.

[0169] In this embodiment, when the instrument control instruction is generated, the steps for generating the instrument maneuver control instruction are as follows:

[0170] Step 1: Follow Figure 12 The instrument maneuver control instruction generation template shown;

[0171] Step 2: Set the instrument maneuver control command parameters and set the necessary command parameters in the specified template;

[0172] Step 3: Agree on the satellite-to-ground communication format. The ground user and the onboard computer agree on the communication format for data upload to ensure correct data transmission and analysis.

[0173] Step 4: Prepare the annotation data. According to the agreed communication format, prepare the instruction annotation data including instruction template, instruction parameters and other information.

[0174] Among them, when the instrument observes the duration control instruction, the steps are as follows:

[0175] Step 1: Follow Figure 13 The instrument observation duration control instruction generation template shown;

[0176] Step 2: Set the instrument observation time control instruction parameters and set the necessary instruction parameters in the specified template;

[0177] Step 3: Calculate the time interval from the start time to the end time of the observation, accumulate all generated instructions, and determine whether it exceeds the total instrument observation time based on the accumulated value.

[0178] In this embodiment, when the instruction is verified, the generated observation instructions are verified and merged. The verification method is Cyclic Redundancy Check (CRC) to ensure the correctness and integrity of the instruction. When the CRC is verified, a suitable divisor (i.e., a generating polynomial) is selected, and the data to be verified is regarded as the dividend. Then, modulo 2 division (i.e., binary division without considering the carry) is performed, and the remainder obtained is the CRC check value. When the receiver receives the data, it can verify the integrity of the data through the same operation. If the remainder is zero, it means that there is no error in the data; otherwise, an error occurred in the data during transmission. The specific steps of CRC verification are:

[0179] A. Select a generating polynomial: First, you need to select a generating polynomial, which is usually a fixed binary number used for CRC check calculation.

[0180] B. Append zero bits: A certain number of zero bits are appended to the data to be checked (usually also a binary number). The number of these zero bits is usually equal to the order of the generating polynomial (that is, the number of bits minus 1).

[0181] C. Perform modulo-2 division: Treat the data with the appended zero bits as the dividend and the generator polynomial as the divisor, performing modulo-2 division. Each division result is derived using an exclusive-OR operation.

[0182] D. Obtaining the CRC checksum: The remainder obtained after the modulo-2 division operation is the CRC checksum. This checksum will be appended to the end of the original data to form a complete data frame.

[0183] In this embodiment, the automatic planning device for the on-orbit observation mode of the solar reflection band hyperspectral imager is further provided with a fault-tolerant mechanism for instructions, which includes:

[0184] 1. Operation monitoring: If abnormal conditions such as resource exhaustion and instruction execution timeout are detected, the program will immediately trigger the error handling mechanism.

[0185] 2. Exception capture and handling: The program uses a try-catch block to capture possible exceptions. In the catch block, the program executes appropriate error handling logic based on the exception type, such as logging and releasing resources.

[0186] 3. Automatic Retry: In the event of network delays or temporary resource unavailability, the program will automatically retry failed commands. The retry mechanism can be configured with parameters such as the number of retries and the retry interval to balance performance and reliability.

[0187] In this embodiment, the automatic planning device for the on-orbit observation mode of the solar reflection band hyperspectral imager updates the orbit forecast data daily through a recursive strategy, with an update frequency of not less than once every 6 hours to ensure the calculation accuracy of the observation angle under the inclined orbit.

[0188] In this embodiment, the observation target combination module supports various target observations and complex observation combinations included in the two major observation modes of hyperspectral imager instrument self-calibration and Earth-Moon observation.

[0189] In this embodiment, the timing execution instruction generation process of the on-orbit observation mode automatic planning device of the solar reflection band hyperspectral imager is shown in Figure 14 As shown, take the daily instruction generation process as an example, see Figure 15 As shown in the figure, the command is generated every day, and two files are generated: one is a pure command file, and the other is a command description file. The command template of the automatic planning device of the on-orbit observation mode of the solar reflection band hyperspectral imager is as follows: Figure 16 The present invention's automatic planning device for on-orbit observation mode for a solar reflection band hyperspectral imager can read and parse orbit prediction files in real time, rapidly calculating the position and angle of the observed target, significantly reducing the time required to plan observation missions. Through intelligent sorting and planning, the device prioritizes high-priority observation tasks, ensuring timely observation of important scientific research targets and improving overall observation efficiency.

[0190] The automatic planning device for the on-orbit observation mode of the solar reflection band hyperspectral imager of the present invention can reasonably plan the observation time according to the satellite orbit characteristics and the instrument working capabilities, thereby avoiding the waste of observation resources; by setting the upper limit of the number of instructions and the observation time limit, the efficient execution of the observation task is ensured, while the demand for caching and maneuverability on the satellite is reduced; the automated instruction generation and verification mechanism ensures the correctness and completeness of the observation instructions, reducing the risk of human error; the device adopts a modular design, and each module is independent of each other, which is convenient for maintenance and upgrading, and enhances the stability and reliability of the system.

[0191] It should be noted that the observation mode priority ranking and observation targets of each mode designed in the present invention adopt the principle that instrument traceability has the highest priority and radiation calibration transfer has the second priority. Any other scheme that does not add new modes or new observation targets but only changes the priority of the observation mode is considered to be in conflict with the present invention and should not be protected.

[0192] The present invention's test method and observation target in the attenuator attenuation coefficient self-test mode are aimed at a scheme for observing the sun using a dual-rotating attenuation wheel combination. Other schemes that only change the attenuation wheel structure and the observation light source without changing the measurement method are considered to be in conflict with the present invention and should not be protected.

[0193] In the timed execution instruction generation process, the present invention designs weekend judgment conditions to realize unmanned observation mode automatic planning device. Other instruction generation process schemes that have no essential changes and only make changes in holiday judgment are considered to be in conflict with the present invention and should not be protected.

[0194] The above are exemplary embodiments disclosed in the present invention, but it should be noted that various changes and modifications may be made without departing from the scope of the embodiments disclosed in the claims. The functions, steps and / or actions of the method claims according to the disclosed embodiments described herein do not need to be performed in any particular order. In addition, although the elements disclosed in the embodiments of the present invention may be described or required in individual form, they may also be understood as multiple unless expressly limited to the singular.

[0195] It should be understood that, as used herein, the singular form "a" or "an" is intended to include the plural form, unless the context clearly supports an exception. It should also be understood that, as used herein, "and / or" refers to any and all possible combinations of one or more of the items listed in association. The serial numbers of the embodiments disclosed in the above embodiments of the present invention are for descriptive purposes only and do not represent the superiority or inferiority of the embodiments.

[0196] Those skilled in the art should understand that the discussion of any of the above embodiments is merely illustrative and is not intended to imply that the scope of the disclosure of the embodiments of the present invention (including the claims) is limited to these examples. Within the spirit of the embodiments of the present invention, the technical features of the above embodiments or different embodiments may be combined, and there are many other variations of different aspects of the above embodiments of the present invention, which are not provided in detail for the sake of simplicity. Therefore, any omissions, modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the embodiments of the present invention should be included in the scope of protection of the embodiments of the present invention.

Claims

1. An automatic planning device for on-orbit observation mode of a solar reflection band hyperspectral imager, characterized in that: Includes the following modules: Orbit prediction and analysis module: used to regularly read and analyze satellite orbit prediction files, obtain orbit prediction information of satellite position, speed, time and maneuvering status in the geocentric inertial system, and calculate the field of view angle and position parameters of the observed target based on the instrument installation coordinates; Observation mode priority sorting module: built-in priority rules for Earth-Moon observation mode and self-calibration mode, dynamically adjusts the observation task priority according to the preset Earth-Moon observation mode and self-calibration mode functional structure, observation cycle and satellite sudden interruption events; Observation target combination module: used to call preset observation target combination rules according to different observation modes; Control command generation module: Calculates the observation time window, turntable azimuth and pitch angle parameters based on the orbit geometry model, and generates instrument maneuver control commands and observation duration control commands; Instruction verification and injection module: uses cyclic redundancy check to verify the integrity of the instruction sequence, and injects the verified instructions into the instrument execution controller through the instruction injector.

2. The automatic planning device for on-orbit observation mode of a solar reflection band hyperspectral imager according to claim 1, characterized in that: In the observation mode prioritization module: The priority rule for Earth-Moon observation modes is: pseudo-invariant target observation mode > intersatellite cross calibration mode > solar spectrum irradiance observation and on-orbit tracing mode > Earth patrol mode; The priority rule of self-calibration mode is: attenuator attenuation coefficient self-test mode > instrument linear response test mode > instrument field of view homogenization mode > spectrum center wavelength test mode; When the self-calibration mode is triggered, it takes priority over all Earth-Moon observation modes.

3. The automatic planning device for on-orbit observation mode of a solar reflection band hyperspectral imager according to claim 2, characterized in that: The Earth-Moon observation modes are arranged in descending order of priority as follows: pseudo-invariant target observation mode, intersatellite cross calibration mode, solar spectrum irradiance observation and on-orbit tracing mode, and Earth patrol mode.

4. The automatic planning device for on-orbit observation mode of a solar reflection band hyperspectral imager according to claim 3, characterized in that: The observation target combination rules include: In the pseudo-invariant target observation mode, site tracking observation, solar spectrum irradiance observation and instrument dark background observation are combined; In the self-calibration mode, the solar spectrum data is observed by the dual rotating attenuation wheel combination to generate attenuation coefficient and response linearity test instructions.

5. The automatic planning device for on-orbit observation mode of a solar reflection band hyperspectral imager according to claim 4, characterized in that: The self-calibration modes are arranged in descending order of priority as follows: attenuator attenuation coefficient self-test mode, instrument linear response test mode, instrument field of view homogenization mode, and spectrum center wavelength test mode.

6. The automatic planning device for on-orbit observation mode of a solar reflection band hyperspectral imager according to claim 1, characterized in that: The pseudo-invariant target observation mode in the observation target combination module includes: Site replacement calibration mode: Select a stable area such as the Dunhuang radiation calibration site or the Libyan desert to conduct earth observations in that area, and combine solar spectral irradiance observations with dark background data to complete the ground data radiation calibration and emissivity calculation, and generate a reference dataset for radiation calibration transfer; Lunar observation mode: During a specific lunar phase, lunar spectral irradiance observations are combined with solar spectral irradiance observations to calculate the lunar albedo and use it as a lunar reference dataset for radiometric calibration. Intersatellite cross calibration mode: Based on the orbital parameters of the satellite where the hyperspectral imager is located and the satellite to be compared, the temporal and spatial parameters of the sub-satellite point crossing event of the two satellites are predicted and the satellite where the imager is located is guided to conduct maneuverable observation of the ground.

7. The automatic planning device for on-orbit observation mode of a solar reflection band hyperspectral imager according to claim 6, characterized in that: In the control instruction generation module, the sun / moon observation instruction parameters include the turntable azimuth and pitch angle; the earth observation instruction parameters include restrictions including the sub-satellite point position, observation time window and field of view coverage.

8. The automatic planning device for on-orbit observation mode of a solar reflection band hyperspectral imager according to claim 1, characterized in that: In the instruction verification and injection module, sequential logic is used to verify the physical feasibility of the observation instruction, including the matching of the turntable maneuvering time and the observation duration.

9. The automatic planning device for on-orbit observation mode of a solar reflection band hyperspectral imager according to claim 8, characterized in that: The automatic planning device for the on-orbit observation mode of the solar reflection band hyperspectral imager further includes: Self-calibration mode trigger mechanism: Dynamically generates self-calibration task trigger instructions based on periodic observation rules of self-calibration parameters such as instrument attenuation characteristics and detector response uniformity; Emergency interrupt response module: When the satellite performs maneuvers, it terminates the current observation mission and replans the remaining command sequences.

10. The automatic planning device for on-orbit observation mode of a solar reflection band hyperspectral imager according to claim 9, characterized in that: The automatic planning device for the on-orbit observation mode of the solar reflection band hyperspectral imager updates the orbit prediction data daily through a recursive strategy, with an update frequency of not less than once every 6 hours. The observation target combination module supports various target observations and complex observation combinations included in the two major observation modes of hyperspectral imager instrument self-calibration and Earth-Moon observation.

Images