On-orbit observation mode automatic planning device of solar reflection band hyperspectral imager

Abstract

The application provides an on-orbit observation mode automatic planning device of a solar reflection band hyperspectral imager, and relates to the technical field of satellite remote sensing.The device comprises a track prediction analysis module, an observation mode priority sorting module, an observation target combination module, a control instruction generation module, and an instruction verification and uploading module;by reading and analyzing a satellite track prediction file, track prediction information of the satellite in an earth-centered inertial system is obtained, and the field of view angle and position parameters of the observation target are calculated in combination with the instrument installation coordinates;the observation task priority is dynamically adjusted according to the function composition, observation period and satellite sudden interruption event of the preset lunar observation mode and self-calibration mode;the preset observation target combination rule is called to generate instrument maneuvering control instructions and observation time length control instructions, the integrity of the instruction sequence is verified, and the verified instructions are injected into an instrument execution controller through an instruction uploader, so that the automatic arrangement and generation of the instruction sequence can be realized.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of satellite remote sensing, and particularly relates to an on-orbit observation mode automatic planning device of a solar reflection band hyperspectral imager. BACKGROUND

[0002] In order to detect the information of solar reflection flux incident on the earth, cloud and aerosol characteristics, and ground reflectivity, which is crucial for climate strength, response and feedback, a hyperspectral imager with an accuracy of 0.3% (k=2) for measuring the earth's reflected solar radiation needs to be carried on a remote sensing satellite. The hyperspectral imager mainly calculates the earth reflectivity by measuring the earth radiance spectrum and the solar irradiance spectrum, and takes the sun as the on-orbit radiation calibration source for reflectivity measurement, and traces the solar irradiance spectrum measured by the total solar irradiance spectrometer to the international system of units (SI) power unit watt (Watt). Due to the high intensity of sunlight in space, the instrument cannot directly observe the sun and needs to be attenuated by an attenuator (diaphragm or filter) before being introduced into the instrument, and in order to calibrate the linear response of the instrument on-orbit, the attenuator also needs to be set to different attenuation levels, so the attenuator is generally a wheel structure with through holes (no attenuation) and different attenuation coefficient attenuation pieces, and different levels of attenuation pieces are cut into / out of the imaging instrument light port by rotating the attenuation piece wheel. In addition, as a high-precision imager, its main function is to use the earth stable target, the moon and other pseudo-invariant calibration sources as media, and use the cross-calibration method of satellite sub-satellite points to transfer the radiation calibration accuracy of itself to other satellite remote sensing instruments working in the solar reflection band. Finally, in order to perform high-precision radiation calibration on the raw measurement data of on-orbit observation of the earth, the sun, the moon and other targets, the instrument needs to be immediately observed in the deep cold space of the universe (referred to as "cold space") to obtain the dark background level of the instrument after various target observation is completed.

[0003] Since remote sensing instruments observing global cloud and aerosol properties, surface reflectance are usually deployed in sun-synchronous orbit (e.g. Aqua / MODIS, Landsat / OLI, Sentinel-2 / MSI), deploying hyperspectral imager in an inclined orbit can greatly increase the opportunity of cross-calibration with these nadir-crossing calibrated remote sensing instruments. However, satellites running in an inclined orbit are affected by various complex factors, resulting in changes in its orbital characteristics. On the one hand, the satellite is affected by atmospheric resistance, earth gravity perturbation and other factors, resulting in gradual decay of the orbital height. In order to ensure the long-term stable operation of the satellite, regular orbital adjustment (such as lifting the orbital height) must be carried out. On the other hand, in order to maintain the stability of the internal thermal environment of the remote sensing satellite, a heat dissipation surface is usually installed on one side of the satellite; but for an inclined orbit, the sunlight angle will not be fixed on the same side of the orbital plane, but will appear on both sides of the satellite over time. When the sunlight angle changes and the sun shines on the heat dissipation surface, it will affect the satellite heat dissipation and thermal environment stability, so the satellite needs to make a turn maneuver according to the relationship between the sun azimuth angle (beta angle) to avoid this situation.

[0004] In summary, due to the diversity of the observation targets of the hyperspectral imager, the complexity of the observation mode, and the harsh working conditions in the inclined orbit, it is necessary to configure and install an on-orbit observation mode automatic planning device combining the observation function needs of the satellite instrument and the constraints of the orbital environmental conditions. The device is mainly responsible for formulating and generating multi-target, multi-mode observation instructions, reasonably arranging task scheduling according to the observation task priority and the coordination relationship between observation targets, and realizing the maximum observation benefit.

[0005] The traditional satellite instruction operation mode mainly relies on manual injection of instructions when the satellite flies through the ground control station. Since the observation mode of the general sun-synchronous orbit satellite is relatively simple and the instrument action is regular, manual instruction generation and injection can meet the needs of these simple observation modes with low injection frequency. However, in the face of multi-target, multi-mode observation tasks of the hyperspectral imager, the manual method shows obvious limitations. Under the constraints of the satellite orbit conditions, an observation mode of the instrument may be composed of multiple observation targets, and there are often complex coordination relationships between targets. For example, cold air observation data is the basis for radiation calibration or analysis of lunar and earth observation data, and it is necessary to switch the attenuator filter to observe cold air data before and after the lunar and earth observation task, which requires the observation mode planning device to intelligently generate instruction sequences to control the instrument action according to the task priority and the internal logical relationship between targets. However, the manual injection of instructions is not only prone to human error, but also inefficient in handling a large number of instructions and complex task logic.

[0006] Therefore, in view of the fact that existing satellite observation tasks usually rely on manual programming and uploading of instructions, this way is inefficient and prone to errors in handling multi-target and multi-mode observation tasks, and lacks flexibility. In particular, in the observation tasks of hyperspectral imagers, the diversity of observation targets and the complexity of observation modes make it difficult for manual planning to meet the requirements of real-time and accuracy. Therefore, there is an urgent need for a device that can automatically plan observation modes and generate observation instructions to improve observation efficiency and system reliability. SUMMARY

[0007] Therefore, the purpose of the present application is to provide a solar reflection band hyperspectral imager (hereinafter referred to as "hyperspectral imager") on-orbit observation mode automatic planning device to realize the automatic arrangement and generation of instruction sequences under the combination of multiple observation modes and multiple observation targets. The device can calculate the observation angle and position of different targets in the instrument field of view by combining the orbit prediction with the installation coordinates of the instrument on the satellite. According to the instrument task requirements, the observation mode and the corresponding observation target combination are determined. The device is automatically started by the computer controller every day. Due to the large atmospheric resistance of the satellite in low-inclined orbit, there is a large error in the prediction of the satellite orbit position, so the orbit prediction update frequency needs to be improved, and the corresponding mode automatic planning device also needs to calculate and generate the instruction sequence every day according to the recursive strategy.

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

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

[0010] Orbit prediction analysis module: used for reading and analyzing satellite orbit prediction files regularly, obtaining orbit prediction information of the position, velocity, time and maneuver state identification of the satellite in the earth-centered inertial system, and calculating the field of view angle and position parameters of the observation target in combination with the instrument installation coordinates;

[0011] Observation mode priority sorting module: built-in priority rules of lunar observation mode and self-calibration mode, dynamically adjusting the observation task priority according to the function composition, observation period and satellite sudden interruption event of the preset lunar observation mode (A-1 to A-4) and self-calibration mode (B-1 to B-4);

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

[0013] Control instruction generation module: based on the orbit geometric model, calculating the observation time window, azimuth angle and pitch angle parameters, generating instrument maneuver control instructions and observation time length control instructions;

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

[0015] As a further scheme of the present application, the observation mode priority sorting module comprises:

[0016] The priority rules of the earth-moon observation modes are: pseudo-invariant target observation mode (A-1)>inter-satellite cross-calibration mode (A-2)>solar spectral irradiance observation and in-orbit traceability mode (A-3)>earth patrol mode (A-4);

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

[0018] When the self-calibration mode is triggered, its priority is higher than that of all the earth-moon observation modes.

[0019] As a further scheme of the present application, the earth-moon observation modes are sorted in priority from high to low as follows: pseudo-invariant target observation mode, inter-satellite cross-calibration mode, solar spectral irradiance observation and in-orbit traceability mode, and earth patrol mode.

[0020] As a further scheme of the present application, the observation target combination rules comprise:

[0021] In the pseudo-invariant target observation mode, field tracking observation, solar spectral irradiance observation and instrument dark background observation are combined.

[0022] In the self-calibration mode, solar spectral data are combined to generate attenuation coefficient and response linearity checking instructions through double-rotating attenuator wheel combination.

[0023] As a further scheme of the present application, the self-calibration modes are sorted in priority from high to low as follows: attenuator attenuation coefficient self-checking mode, instrument linear response checking mode, instrument field of view homogenization mode, and spectrum center wavelength checking mode.

[0024] As a further scheme of the present application, the pseudo-invariant target observation mode in the observation target combination module comprises:

[0025] Field substitution calibration mode: a stable area is selected to implement observation of the area, and solar spectral irradiance observation and dark background data are combined to complete earth data radiation calibration and emissivity calculation, thereby generating a reference data set for radiation calibration transfer;

[0026] Moon observation mode: in a certain lunar phase cycle, the combination of moon spectral irradiance observation and solar spectral irradiance observation data, the calculation of lunar albedo and the radiation calibration moon reference data set;

[0027] Inter-satellite cross-calibration mode: according to the orbit parameters of the satellite where the hyperspectral imager is located and the satellite to be compared, the space-time parameters of the subsatellite point intersection event of the two satellites are predicted and the satellite where the imager is located is guided to carry out the observation of the earth.

[0028] As a further scheme of the application, in the control instruction generation module, the sun / moon observation instruction parameters include the azimuth angle and the elevation angle; the ground observation instruction parameters include the subsatellite point position, the observation time window and the restriction conditions including the field of view coverage range.

[0029] As a further scheme of the application, in the instruction verification and loading module, the time sequence logic is used to verify the physical realizability of the observation instruction, including the matching of the turntable motion time and the observation time.

[0030] As a further scheme of the application, the on-orbit observation mode automatic planning device of the solar reflection band hyperspectral imager further comprises:

[0031] Self-calibration mode trigger mechanism: according to the periodic observation rules of self-calibration parameters such as instrument attenuation characteristics and detector response uniformity, self-calibration task trigger instructions are dynamically generated;

[0032] Emergency interruption response module: when the satellite is in motion, the current observation task is terminated and the remaining instruction sequence is re-planned.

[0033] As a further scheme of the application, the on-orbit observation mode automatic planning device of the solar reflection band hyperspectral imager updates the orbit prediction data daily through a recursive strategy, and the update frequency is not less than once every 6 hours, so as to ensure the calculation accuracy of the observation angle under the inclined orbit.

[0034] As a further scheme of the application, the observation target combination module supports each target observation and complex observation combination contained in the two observation modes of instrument self-calibration and earth-moon observation of the hyperspectral imager.

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

[0036] 1. The satellite position and target field angle are calculated in real time by the orbit prediction analysis module, and the dynamic priority sorting mechanism is combined to realize the automatic arrangement of multi-mode observation tasks, effectively solving the problems of low efficiency and poor flexibility of manual instruction generation.

[0037] 2. The application also integrates a self-calibration mode triggering mechanism, which dynamically monitors the instrument attenuation characteristics and response linearity by observing solar spectrum data through a double-rotating attenuator wheel combination, ensures the stability of the instrument attenuator characteristics and radiation calibration performance, and supports solar spectrum irradiance SI tracing and ground observation radiation calibration transfer.

[0038] 3. The application is aimed at multiple target observations and complex combinations of multiple targets involved in instrument self-calibration and ground-moon observation modes, dynamically plans the optimal observation time window in combination with various target observation combination orbit restriction conditions, avoids energy and storage resource waste, and optimizes multi-target collaborative observation capability.

[0039] 4. The built-in instruction verification module of the application ensures the functional compatibility of turntable maneuvering time and observation duration through cyclic redundancy check (CRC) and timing logic verification, effectively reduces the instruction conflict rate. When the satellite platform maneuvers, the emergency interrupt response module can suspend the current task and re-plan the remaining instruction sequence, maximizes the safety of the instrument in-orbit operation, periodically updates the orbit prediction data based on the recursive strategy, ensures the accuracy of the instrument observation target and the long-term stability of the observation data in the inclined orbit, and provides reliable data set for high-precision SI tracing and radiation calibration transfer in the solar reflection band.

[0040] In summary, the on-orbit observation mode automatic planning device of the solar reflection band hyperspectral imager of the application significantly improves the accuracy and execution efficiency of the imaging instrument on-orbit observation task planning through automatic observation planning, multi-target collaborative observation, high robustness verification and other core technologies.

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

[0042] In order to more clearly illustrate the technical solutions in the embodiments of the application or the related art, the following will briefly introduce the drawings needed to be used in the exemplary embodiments or related art description. The drawings are used to provide further understanding of the application, and constitute a part of the specification. The drawings together with the embodiments of the application are used to explain the application, and do not constitute a limitation of the application. In the drawings:

[0043] Figure 1 A work flow chart of a solar reflection band hyperspectral imager on-orbit observation mode automatic planning device according to an embodiment of the application.

[0044] Figure 2A schematic diagram of a sun reflection wave band hyperspectral imager in-orbit observation mode of a sun reflection wave band hyperspectral imager in-orbit observation mode automatic planning device according to an embodiment of the present application.

[0045] Figure 3 A schematic diagram of a field replacement calibration mode observation target combination included in a sun reflection wave band hyperspectral imager in-orbit observation mode automatic planning device according to an embodiment of the present application.

[0046] Figure 4 A schematic diagram of a moon observation mode observation target combination included in a sun reflection wave band hyperspectral imager in-orbit observation mode automatic planning device according to an embodiment of the present application.

[0047] Figure 5 A schematic diagram of an inter-satellite cross calibration mode observation target combination included in a sun reflection wave band hyperspectral imager in-orbit observation mode automatic planning device according to an embodiment of the present application.

[0048] Figure 6 A schematic diagram of a sun spectrum irradiance observation and in-orbit traceability mode observation target combination included in a sun reflection wave band hyperspectral imager in-orbit observation mode automatic planning device according to an embodiment of the present application.

[0049] Figure 7 A schematic diagram of a ground patrol observation mode observation target combination included in a sun reflection wave band hyperspectral imager in-orbit observation mode automatic planning device according to an embodiment of the present application.

[0050] Figure 8 A schematic diagram of an attenuator attenuation coefficient self-checking mode observation target combination included in a sun reflection wave band hyperspectral imager in-orbit observation mode automatic planning device according to an embodiment of the present application.

[0051] Figure 9 A schematic diagram of an instrument response linearity self-checking mode observation target combination included in a sun reflection wave band hyperspectral imager in-orbit observation mode automatic planning device according to an embodiment of the present application.

[0052] Figure 10 A schematic diagram of an instrument field of view homogenization mode observation target combination included in a sun reflection wave band hyperspectral imager in-orbit observation mode automatic planning device according to an embodiment of the present application.

[0053] Figure 11 A schematic diagram of a spectral center wavelength self-checking mode observation target combination included in a sun reflection wave band hyperspectral imager in-orbit observation mode automatic planning device according to an embodiment of the present application.

[0054] Figure 12A schematic diagram of an instrument maneuver control instruction generation template in a sun reflection band hyperspectral imager on-orbit observation mode automatic planning device according to an embodiment of the present application.

[0055] Figure 13 A schematic diagram of an instrument observation time length control instruction generation template in a sun reflection band hyperspectral imager on-orbit observation mode automatic planning device according to an embodiment of the present application.

[0056] Figure 14 A timing execution instruction generation flow chart in a sun reflection band hyperspectral imager on-orbit observation mode automatic planning device according to an embodiment of the present application.

[0057] Figure 15 A schedule execution instruction generation flow chart in a sun reflection band hyperspectral imager on-orbit observation mode automatic planning device according to an embodiment of the present application.

[0058] Figure 16 An instruction template schematic diagram in a sun reflection band hyperspectral imager on-orbit observation mode automatic planning device according to an embodiment of the present application.

[0059] Figure 17 A structure block diagram of a sun reflection band hyperspectral imager on-orbit observation mode automatic planning device according to an embodiment of the present application. DETAILED DESCRIPTION

[0060] Hereinafter, the present application will be further described in conjunction with the accompanying drawings and specific embodiments, and it should be noted that the following described embodiments or technical features can be combined in any manner to form new embodiments without conflict.

[0061] In order to make the objectives, technical solutions and advantages of the present application clearer, further detailed description will be made to the embodiments of the present application in conjunction with specific embodiments and referring to the accompanying drawings. It should be understood that the specific embodiments described herein are only used to explain the present application and should not be used to limit the present application.

[0062] It should be noted that all the expressions of "first" and "second" in the embodiments of the present application are used to distinguish two same name non-same entities or non-same parameters, and it can be seen that "first" and "second" are only used for the convenience of description and should not be understood as a limitation of the embodiments of the present application. In addition, the terms "include" and "have" and any variations thereof are intended to cover non-exclusive inclusion, for example, the process, method, system, product or device inherently includes other steps or units.

[0063] With reference to the accompanying drawings, the technical solutions in the embodiments of the present application will be clearly and completely described below, obviously, the described embodiments are some of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative work belong to the protection scope of the present application.

[0064] The flowchart shown in the drawings is only an example, and does not necessarily include all the contents and operations / steps, nor does it necessarily execute in the order described. For example, some operations / steps can also be decomposed, combined or partially merged, so the actual execution order may be changed according to the actual situation.

[0065] Some embodiments of the present application will be described in detail below with reference to the accompanying drawings. The following embodiments and features in the embodiments can be combined with each other without conflict.

[0066] The existing manual preparation and satellite observation instruction loading mode is inefficient and prone to errors, lack of flexibility and other defects when dealing with hyperspectral imager multi-target, multi-mode observation tasks. The present application provides a kind of solar reflection band hyperspectral imager in-orbit observation mode automatic planning device, which generates an imager observation instruction sequence under the constraints of orbital environment conditions and satellite maneuver state instructions according to the priority of observation task, observation mode observation target combination and observation target coordination time sequence logic, and injects the instrument execution controller after correctness self-check. The device of the present application can realize the automatic generation of instruction sequence under the combination of multiple observation modes and multiple observation targets of the instrument. The device can calculate the observation angle and observation position of different targets in the instrument field of view by combining the instrument installation coordinates with the satellite orbit prediction, determine the observation mode and the corresponding observation target combination according to the instrument task requirement. The device of the present application is automatically started by computer controller every day, and since there is a large error in the prediction of the satellite orbit position in the inclined orbit, the prediction update frequency needs to be improved (such as updating once every 6 hours), and the mode automatic planning device also needs to calculate and generate the instruction sequence every day according to the recursive strategy.

[0067] Referring to Figures 1 to 17 The embodiments of the present application provide a kind of solar reflection band hyperspectral imager in-orbit observation mode automatic planning device, comprising the following modules:

[0068] Orbit prediction analysis module: used for reading and analyzing satellite orbit prediction file regularly, obtaining the position, velocity, time and maneuver state identification of satellite in the earth inertial system, calculating the field of view angle and position parameters of observation target in combination with instrument installation coordinates;

[0069] The observation mode priority sorting module: priority rules of the moon observation mode and the self-calibration mode are built in, and the observation task priority is dynamically adjusted according to preset functions, observation periods and satellite interrupt events of the moon observation mode (A-1 to A-4) and the self-calibration mode (B-1 to B-4);

[0070] The observation target combination module: used for calling preset observation target combination rules according to different observation modes;

[0071] The control instruction generation module: used for calculating observation time windows, azimuth angles and elevation angles of a turntable, generating instrument motion control instructions and observation time length control instructions based on an orbit geometric model;

[0072] The instruction verification and uploading module: used for verifying the integrity of instruction sequences by using a cyclic redundancy check (CRC) and injecting the verified instructions into an instrument execution controller through an instruction uploader.

[0073] Referring to Figure 1 As shown in the figure, the overall working process of the on-orbit observation mode automatic planning device of the solar reflection band hyperspectral imager is as follows:

[0074] The orbit predictor reads and analyzes the orbit prediction file in a timing manner, inputs the orbit prediction file (read satellite position, speed and time), observation mode priority sorting (performs according to priority sorting rules) and observation mode target combination, and according to the above inputs of the orbit prediction file, the instrument is predicted to observe a specified target at a specified angle at a specified time, based on which the motion control instructions and the observation time length control instructions of the instrument are generated, the instructions are combined and verified, the instruction list is generated, the instructions are uploaded through the instruction uploader, and the instrument performs observation according to the instructions.

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

[0076] The moon observation mode priority rules are as follows: 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 self-calibration mode priority rules are as follows: attenuator attenuation coefficient self-checking mode (B-1) > instrument linear response checking mode (B-2) > instrument field of view homogenization mode (B-3) > spectral center wavelength checking mode (B-4);

[0078] When the self-calibration mode is triggered, the priority is higher than that of all moon observation modes.

[0079] Specifically, when reading and analyzing the orbit prediction file, the instruction generation background permanent process of the observation mode automatic planning device computer reads and analyzes the orbit prediction file in time, wherein the orbit prediction information mainly includes the position, velocity, time, satellite maneuver state identification of the satellite in the earth-centered inertial system. Then, when performing observation mode priority sorting, the hyperspectral imager and the conventional earth observation remote sensing instrument have the following main functions: firstly, self-verify the radiation calibration accuracy of the imager in orbit, and trace the earth reflectivity to the international system of units (SI) power unit watt (Watt) through the solar reference spectral irradiance; secondly, transfer the radiation calibration accuracy of the imager to other remote sensing instruments without SI-traceable function through satellite cross-calibration technology or pseudo-invariant target-based alternative calibration technology. In addition, the attenuator attenuation characteristics, detector response linearity, detector response uniformity, spectral calibration stability and other inherent characteristics of the hyperspectral imager related to the instrument radiation calibration accuracy and SI traceable uncertainty also need to carry out self-checking and self-calibration activities in orbit. Therefore, the observation mode of the imager is divided into earth-moon observation mode and self-calibration mode according to function composition and observation period, as shown in Figure 2

[0080] A-1. Pseudo-invariant target observation mode (including field alternative calibration mode based on earth stable target and moon observation mode);

[0081] A-2. Inter-satellite cross-calibration mode;

[0082] A-3. Solar spectral irradiance observation and in-orbit traceable mode;

[0083] A-4. Earth patrol mode;

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

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

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

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

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

[0089] In addition, since the instrument inherent property self-calibration is the basis for maintaining the radiation calibration accuracy and calibration stability of the imager, when the self-calibration opportunity is encountered, the self-calibration mode priority is higher than that of the earth-moon observation mode.

[0090] ​Therefore, the observation mode automatic planning device needs to be built-in with the above observation mode and its priority coding, and then combined with satellite orbit prediction information and observation target observation timing constraint conditions, the observation mode priority of actual execution per day is planned and sorted.

[0091] In the embodiment, the earth-moon observation mode is sorted from high to low priority as follows: pseudo-invariant target observation mode, inter-satellite cross-calibration mode, solar spectral irradiance observation and in-orbit traceability mode, and earth patrol mode.

[0092] The observation target combination rule includes:

[0093] In the pseudo-invariant target observation mode, field tracking observation, solar spectral irradiance observation and instrument dark background observation are combined.

[0094] In the self-calibration mode, solar spectral data are combined by double-rotating attenuator wheel to generate attenuation coefficient and response linearity test instructions.

[0095] In the embodiment, the self-calibration mode is sorted from high to low priority as follows: attenuator attenuation coefficient self-test mode, instrument linear response test mode, instrument field of view homogenization mode, and spectral center wavelength test mode.

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

[0097] Field substitution calibration mode: a stable area is selected to implement the area observation, and the data radiation calibration and emissivity calculation are completed by combining the solar spectral irradiance observation and dark background data to generate a reference data set for radiation calibration transfer;

[0098] Moon observation mode: in a specific lunar phase period, the moon spectral irradiance observation data are combined with the solar spectral irradiance observation data to calculate the lunar albedo and serve as a radiation calibration moon reference data set.

[0099] Inter-satellite cross-calibration mode: according to the orbit parameters of the satellite where the hyperspectral imager is located and the satellite to be compared, the time and space parameters of the subsatellite point intersection event of the two satellites are predicted and the satellite where the imager is located is guided to carry out earth maneuvering observation.

[0100] In the embodiment, the observation mode target combination is composed of various observation modes, so the observation mode automatic planning device combines different observation targets according to different observation modes, and then calls the orbit geometry model to calculate the observation angle and observation position of different observation targets, and generates instrument maneuvering control instructions and observation time length control instructions.

[0101] In the embodiment, the control instruction generating module, the sun / moon observation instruction parameters include the azimuth angle and the elevation angle of the rotating platform; the ground observation instruction parameters include the sub-solar point position, the observation time window, and the limiting conditions including the field of view coverage.

[0102] In the embodiment, the instruction verification and injection module uses time sequence logic to verify the physical realizability of the observation instruction, including the matching of the rotating platform maneuvering time and the observation time length.

[0103] In the embodiment, the observation target combination corresponding to various observation modes is described as follows:

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

[0105] (1) Field substitution calibration mode.

[0106] The field substitution calibration mode selects several regions with stable surface characteristics on the earth (such as the Dunhuang radiometric calibration field in China and the Libyan desert) as the radiometric calibration transfer medium, takes the high radiometric calibration accuracy of the imager as the reference, takes the field measurement data of the known / measurable radiometric information as the intermediary, respectively compares the field observation data of the imager and the measured instrument with the intermediary data, so as to realize the mutual comparison of the radiometric calibration accuracy of the measured instrument and the radiometric calibration accuracy of the imager. Since the radiometric calibration accuracy of the imager is self-checked and SI traced, the radiometric calibration transfer relationship from the SI reference source to the measured instrument is indirectly established (that is, the deviation and uncertainty of the radiometric calibration value and the measurement true value of the measured instrument are obtained). The field substitution calibration has the characteristics that the requirements for the space-time geometric conditions of the observation of the imager and the measured instrument are relatively low compared with the sub-solar point cross calibration, and the requirements for the observation time difference, pointing error, and projection footprint matching error are relatively relaxed. However, the length of the radiometric calibration transfer link is increased by the field measurement data as the intermediary data, which may introduce new uncertainty.

[0107] Since the field substitution calibration takes the earth reflectivity after the radiometric calibration of the imager as the reference source, and the field observation area is relatively limited (such as the Dunhuang radiometric calibration field), the two-dimensional pointing mechanism of the imager needs to implement tracking observation on the field target to accumulate observation samples, and the radiometric calibration and calculation of the earth reflectivity of the observation data require the dark background of the observation instrument and the solar spectral irradiance, so the observation mode automatic planning device needs to combine the three observation targets of field tracking observation, solar spectral irradiance observation, and instrument dark background observation for this mode, such as Figure 3The field tracking observation needs to combine the orbit prediction file and the delineated earth stable target area to calculate the start and end time of the satellite passing through the stable target, the effective tracking angle, the solar spectrum irradiance observation needs to cut in the diffuse transmission plate of the attenuator at the imaging instrument light port to avoid the damage of the direct sunlight to the instrument optical components or the detector, and the instrument dark background observation needs to cut in the maximum level attenuation piece of the attenuator and point the instrument light port to the cold space.

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

[0109] Table 1 Earth stable target point area range

[0110]

[0111]

[0112] (2) Moon observation mode.

[0113] The moon observation mode is similar to the field replacement calibration mode, which selects the moon as a long-term stable on-orbit calibration source to carry out on-orbit radiation calibration of the solar reflection band remote sensing instrument. In the radiation calibration transfer process of the hyperspectral imager, the moon is used as a radiation calibration transfer medium, the high radiation calibration accuracy of the imager is used as a reference, and the moon irradiance model simulation observation moon phase data is used as an intermediary. The moon observation data of the imager and the measured instrument under the same moon phase are compared with the intermediary data, respectively, to realize the mutual comparison of the radiation calibration accuracy of the measured instrument and the radiation calibration accuracy of the imager, and indirectly realize the transfer relationship from the SI reference source to the measured instrument based on the moon observation. Since the moon is the brightest and largest natural light source observed by humans other than the sun, and observing the moon in space will not be affected by atmospheric absorption and scattering, therefore, using the moon as a radiation calibration transfer medium has a unique feature compared to the earth stable target, but the prerequisite is to build a high-precision moon irradiance model.

[0114] The moon observation data needs to be radiometrically calibrated and the lunar albedo needs to be calculated, so the observation mode automatic planning device needs to combine the moon spectral irradiance observation, the solar spectral irradiance observation and the instrument dark background observation for this mode, as shown in Table 2. Figure 4 The control instructions for pointing the two-dimensional pointing mechanism to each target are generated. In order to implement the moon observation, the calculation data of the time, position and velocity of the moon observation in the geocentric geodetic coordinate system need to be added to the orbit prediction file.

[0115] A-2. Cross-calibration mode between satellites.

[0116] The cross-calibration of the sub-satellite point between satellites is an important means to transfer the radiometric calibration accuracy of the hyperspectral imager to the measured instrument. When the imager and the measured instrument observe the same scene on the earth with the same atmospheric path in a short time (such as 300s), it can be considered that the atmospheric state and the ground characteristics will not change significantly in a short time, and the observation data of the two will theoretically remain consistent, so the relative radiometric calibration accuracy of the measured instrument to the imager can be evaluated by directly comparing the reflectivity data of the two observation of the earth. Similarly, since the radiometric calibration accuracy of the imager is self-checked and SI traced, the radiometric calibration transfer relationship from the SI reference source to the measured instrument is indirectly established.

[0117] The observation mode automatic planning device needs to combine three observation targets of the earth cross target observation, the solar spectral irradiance observation and the instrument dark background observation for the cross-calibration mode between satellites, as shown in Figure 5 The control command for pointing each target by the two-dimensional pointing mechanism is generated. Among them, in order to implement the observation of the earth cross target, the calculation data of the time, position and angle of the cross event of the measured instrument satellite orbit and the imager orbit in the orbit prediction file are added, and the two-dimensional pointing mechanism of the imager is controlled to point to the observation area in time.

[0118] A-3. Solar spectral irradiance observation and on-orbit tracing mode.

[0119] The on-orbit solar irradiance spectral observation of the hyperspectral imager is mainly to take the stable solar irradiance as a reference to test the absolute accuracy and stability of the radiometric calibration of the imager. 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 method of thermoelectric power. At this time, the observation mode automatic planning device only needs to control the imager and the electrical substitution radiometer to observe the sun synchronously to realize the solar spectral irradiance observation and on-orbit tracing. If the imager is not equipped with an electrical substitution radiometer, the absolute true value of the solar spectral irradiance cannot be measured independently. 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) to carry out on-orbit solar synchronous observation based on the orbit prediction information, and trace the solar spectral irradiance observation data to the reference instrument. Therefore, the solar spectral irradiance observation and on-orbit tracing mode includes two observation targets of the solar spectral synchronous observation and the instrument dark background observation, as shown in Figure 6 .

[0120] A-4. Patrol observation mode.

[0121] When there is no plan or opportunity to carry out radiation calibration delivery or solar spectral irradiance traceability in the lunar-terrestrial observation activities, the hyperspectral imager mainly carries out the star-point-to-earth patrol observation. At this time, the observation mode automatic planning device controls the two-dimensional pointing mechanism of the imager to point to the star-point observation of the earth (which is also a kind of protection mode to avoid the sun), and observes the solar spectral irradiance and the instrument dark background in time before the earth observation starts out of the earth shadow area or after the observation ends in the earth shadow area (depending on the maneuvering ability of the imager), so as to be used for the radiation calibration of the earth observation data and the reflectivity calculation. Therefore, the observation targets contained in the earth patrol observation mode are shown in the following table. Figure 7

[0122] In order to monitor and maintain the stability of the on-orbit working 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 working to ensure the stability of the attenuation coefficients of each attenuation piece of the attenuator, the stability of the instrument response linearity, the relative uniformity of the spatial response of the detector, and the stability of the dispersion characteristics of the spectrometer. Among them, the attenuation coefficient of the attenuation piece is the most critical parameter to ensure the accuracy of the measurement of the solar spectral irradiance and the integrity of the traceability link. The observation target combination involved in the self-calibration mode instruction sequence compiled by the observation mode automatic planning device is as follows:

[0123] B-1. Attenuator attenuation coefficient self-checking mode.

[0124] The accuracy of the attenuation coefficient of each attenuation piece of the attenuator directly affects the accuracy of the on-orbit measurement of the solar spectral irradiance, so it is necessary to accurately measure the spectral attenuation coefficient of each attenuation piece in the solar reflection band in the pre-launch laboratory measurement activity. After the imager is launched into space, the attenuation characteristics of the attenuation piece should theoretically remain consistent with the pre-launch measurement results, but due to the change of the space working environment and the influence of cosmic rays, its attenuation characteristics may change. Therefore, the on-orbit self-calibration of the imager first needs to measure the attenuation coefficient of the attenuation piece and carry out consistency comparison with the pre-launch measurement results.

[0125] The on-orbit measurement of the attenuation coefficient of the attenuation piece adopts the observation data ratio method, that is, the aperture with the added attenuation piece and the through hole without the added attenuation piece are respectively observed to the same radiation source through the rotating switching of the wheel hole, and then the spectral ratio is calculated to obtain the spectral attenuation coefficient of the attenuation piece.

[0126] ​To ensure that each wheel hole of the attenuator can effectively observe the same radiation source, one approach is to install an artificial light source (such as a calibration lamp and an integrating sphere) on the satellite. However, due to the limited life of the calibration lamp and the difficulty in keeping the light spectrum consistent with the solar spectrum, another approach is to use a double-rotating attenuator wheel to observe the sun, that is, to set two coaxially rotating wheel plates, and to observe the sun through different attenuator wheel hole combinations. In the attenuator attenuation coefficient self-checking mode, the outer wheel plate of the double-rotating attenuator wheel mainly plays a role in dynamic adjustment of radiation, that is, to set an appropriate attenuation level to ensure that the first attenuated sunlight can be effectively responded after passing through the through hole of the inner wheel plate and the maximum attenuation wheel hole. Naturally, the attenuator pieces of each wheel hole of the inner wheel plate are the components whose attenuation coefficients need to be finely measured.

[0127] According to the above principle, the observation mode automatic planning device calculates the accurate sun observation time according to the self-calibration mode planning schedule and the orbit prediction file, drives the two-dimensional pointing mechanism of the imager to stably point to the sun, and controls the inner and outer wheel hole combinations of the attenuator wheel to observe the sun one by one, and calculates the attenuation coefficients of the attenuator pieces according to the measurement data of each wheel hole. The observation target combination is shown in Figure 8 .

[0128] B-2. Instrument response linearity self-checking mode.

[0129] An ideal hyperspectral imager should be a linear response system, but actual instruments always exhibit more or less nonlinear response characteristics. Regularly checking the stability of the instrument response linearity in orbit is an important measure to ensure the accuracy and stability of radiation calibration. The nonlinear response of the instrument mainly includes:

[0130] ① Nonlinear response of the detector to different radiation energy levels under the same integration time;

[0131] ② Nonlinear response of the detector to different integration time signal outputs under the same radiation energy level.

[0132] For the measurement of the first kind of nonlinear response, similar to the attenuation coefficient self-checking mode, the sun attenuation data can be measured under a certain fixed integration time through different attenuator piece combinations. For the measurement of the second kind of nonlinear response, a certain level of attenuator can be fixed, and the sun attenuation data can be measured by changing different integration times. Based on the combination of the two measurement methods, the linearity of the instrument response during the on-orbit operation of the imager can be analyzed and evaluated.

[0133] According to the above principle, the observation mode automatic planning device calculates the accurate sun observation time according to the self-calibration mode planning schedule and the orbit prediction file, drives the two-dimensional pointing mechanism of the imager to stably point to the sun, and controls the inner and outer wheel hole combinations of the attenuator wheel to observe the sun one by one, and calculates the attenuation coefficients of the attenuator pieces according to the measurement data of each wheel hole. The observation target combination is shown in Figure 9 .

[0134] B-3. Instrument field of view uniformity mode.

[0135] A hyperspectral imager is essentially an imaging spectrometer, which images each instantaneous light beam focused on the slit by a slit diaphragm, dispersive optics and a focal plane array detector. Therefore, the instantaneous field of view image reflects the spatial distribution of the scene in one dimension of the rectangular focal plane array (referred to as the "spatial dimension") and the spectral distribution of the scene in the other dimension (referred to as the "spectral dimension"). The relative consistency of the instrument radiation calibration in the two dimensions of the detector is an important factor affecting the accuracy of data measurement and the stability of calibration.

[0136] To ensure the relative consistency of the radiation calibration in the spatial and spectral dimensions, the imager needs to periodically carry out instrument field of view uniformity test activities in orbit. The basic principle is to install a solar attenuation screen (such as a solar diffuse transmission plate) in front of the instrument, and to drive the two-dimensional pointing mechanism to uniformly scan the attenuation screen along the long side of the slit by the observation mode automatic planning device, so 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 on the attenuation screen within the scanning time, the relative calibration consistency of the instrument in the two dimensions (i.e. the field of view uniformity) can be evaluated and corrected. The observation target combination is shown in Figure 10 .

[0137] B-4. Spectral center wavelength self-check mode.

[0138] Spectral calibration accuracy is an important factor that characterizes the performance of a hyperspectral imager and affects the accuracy of radiation calibration. Generally, the measurement and evaluation of the dispersion characteristics of a spectrometer are carried out in the laboratory environment before launch by frequency scanning of a tunable laser. Due to the limitations of satellite resources such as volume, weight and power consumption, it is usually not possible to configure an on-board laser frequency scanning device for the imager, and it is simplified to a small number of discrete lasers of single color wavelength. The imager indirectly evaluates the stability of the spectral calibration of the imager by periodically observing the on-board laser and monitoring the center wavelength changes 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 turn on and off one by one to implement monochromatic laser observation. The observation target combination is shown in Figure 11 .

[0139] In this embodiment, the on-board observation mode automatic planning device of the solar reflection band hyperspectral imager further comprises:

[0140] Self-calibration mode triggering mechanism: dynamically generates self-calibration task triggering instructions according to the periodic observation rules of self-calibration parameters such as instrument attenuation characteristics and detector response uniformity;

[0141] Emergency interruption response module: when the satellite performs a maneuvering action, terminate the current observation task and re-plan the remaining instruction sequence.

[0142] In the embodiment, the observation mode automatic planning device calculates the control information parameters such as observation time and observation angle of each target after completing the observation mode priority ranking and observation target combination according to the orbit prediction file. The information parameter calculation is as follows:

[0143] (1) Calculate the azimuth and elevation angles of the sun / moon observation instrument turntable of the sun reflection wave band hyperspectral imager.

[0144] According to the orbit prediction file and the satellite broadcast sun / moon vector, the sun / moon vector position at a future time is calculated and converted into an elevation angle and an azimuth angle to control the pointing of the turntable. The specific calculation method is as follows:

[0145] The vector of the earth to the sun / moon in the geocentric inertial coordinate system is known The vector in the optical axis coordinate system can be obtained through matrix conversion:

[0146]

[0147] Wherein, subscript optics is the optical axis coordinate axis, eci is the geocentric 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 conversion matrix from the geocentric inertial coordinate system to the orbit coordinate system, T orb2body is the conversion matrix from the orbit coordinate system to the satellite body coordinate system, T body2inst is the conversion matrix from the satellite body coordinate system to the instrument coordinate system, T inst2prism is the conversion matrix from the instrument coordinate system to the instrument prism coordinate system, T prism2optics is the conversion matrix from the instrument prism coordinate system to the optical axis coordinate system.

[0148] The observation mode automatic planning device will judge whether the sun / moon enters the XOY plane in the optical axis coordinate system according to the observation mode to establish a judgment condition:

[0149] α = arctan(r z / r x )<ε (2)

[0150] Wherein, α is the elevation angle, and ε is the set threshold value.

[0151] The azimuth angle β corresponding to the observation mode is calculated as:

[0152] β = arctan(r y / r x ) (3)

[0153] The observation time is calculated: when the pitch angle meets the set threshold condition, the starting time and the ending time that meet the condition are recorded as the target observation time in this observation mode.

[0154] (2) Calculate the azimuth and pitch angle of the satellite ground observation instrument turntable of the solar reflection band hyperspectral imager.

[0155] According to the orbit prediction file, the position of the satellite passing through the Earth-stable target area in the future is calculated and converted into pitch angle and azimuth to control the pointing of the turntable to the position. The specific calculation method is as follows:

[0156] The coordinate vector of the Earth-stable target in the Earth-Centered Fixed (ECF) system is known The coordinate vector of the satellite in the Earth-Centered Fixed (ECF) system is known The vector of the satellite pointing to the Earth-stable target can be expressed as:

[0157]

[0158] After matrix conversion, the vector in the instrument coordinate system can be obtained:

[0159]

[0160] Where, the subscript ecr is the Earth-Centered Fixed (ECF) coordinate system, eci is the Earth-Centered Inertial (ECI) 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 conversion matrix from the Earth-Centered Fixed (ECF) coordinate system to the Earth-Centered Inertial (ECI) coordinate system, T eci2orb is the conversion matrix from the Earth-Centered Fixed (ECF) coordinate system to the orbit coordinate system, T orb2body is the conversion matrix from the orbit coordinate system to the satellite body coordinate system, T body2inst is the conversion matrix from the satellite body coordinate system to the instrument coordinate system, and T inst2cube is the conversion matrix from the instrument coordinate system to the instrument focal plane coordinate system.

[0161] The azimuth calculation formula is:

[0162]

[0163] The pitch angle calculation formula is:

[0164]

[0165] The observation time is determined:

[0166] The coordinate vector of the Earth-stable target in the Earth-Centered Fixed (ECF) system is known The latitude and longitude of the Earth-stable target can be expressed as

[0167]

[0168] where subscript lon is longitude, lat is latitude, r x is the x component in the geocentric geodetic system, r y is the y component in the geocentric geodetic system, r z is the z component in the geocentric geodetic system, e is the eccentricity, and a is the Earth radius.

[0169] According to the Earth stable target point threshold range, the latitude and longitude range is screened, and the start time and end time that meet the screening conditions are recorded as the observation time of the Earth stable target point.

[0170] In this embodiment, when the instrument control instruction is generated, the instrument maneuver control instruction generation step is as follows:

[0171] Step 1: According to the instrument maneuver control instruction generation template shown in Figure 12

[0172] Step 2: Set the instrument maneuver control instruction parameters, and set the necessary instruction parameters in the specified template;

[0173] Step 3: Agree on the star-ground communication format, and agree on the data uploading communication format between the ground user and the on-board computer to ensure correct data transmission and analysis;

[0174] Step 4: Prepare the uploading data, and prepare the instruction uploading data containing the instruction template, instruction parameters and other information according to the agreed communication format.

[0175] When the instrument observation duration control instruction is generated, the steps are as follows:

[0176] Step 1: According to the instrument observation duration control instruction generation template shown in Figure 13

[0177] Step 2: Set the instrument observation duration control instruction parameters, and set the necessary instruction parameters in the specified template;

[0178] Step 3: Calculate the time interval from the observation start time to the end time, accumulate all generated instructions, and judge whether the total instrument observation duration is exceeded according to the accumulated value.

[0179] ​​In this embodiment, when the instruction is checked, the generated observation instruction is checked and merged, and the checking method is cyclic redundancy check (CRC), which ensures the correctness and integrity of the instruction. During CRC checking, a suitable divisor (i.e. a generating polynomial) is selected, the data to be checked is regarded as the dividend, and then a modulo 2 division (i.e. a binary division without considering carry) is performed, and the remainder obtained is the CRC check value. The receiver can verify the integrity of the data by the same operation when receiving the data. If the remainder is zero, it means that the data is error-free; otherwise, the data has errors during transmission. The specific steps of CRC checking are as follows:

[0180] A. Select the generating polynomial: first, a generating polynomial is needed, which is usually a fixed binary number used for CRC check calculation.

[0181] B. Add zero bits: append a certain number of zero bits to the data to be checked (usually also a binary number), and the number of these zero bits is usually equal to the order of the generating polynomial (i.e. the number of bits minus 1).

[0182] C. Perform modulo 2 division: treat the data with appended zero bits as the dividend, and perform modulo 2 division with the generating polynomial as the divisor. During the operation, the division result of each bit is obtained based on the exclusive OR operation.

[0183] D. Obtain the CRC check value: the remainder obtained after the modulo 2 division operation is the CRC check value. This check value will be appended to the end of the original data to form a complete data frame.

[0184] In this embodiment, the on-orbit observation mode automatic planning device of the solar reflection band hyperspectral imager is also provided with an instruction fault-tolerant mechanism, which includes:

[0185] 1. Running monitoring: if abnormal conditions such as resource depletion and instruction execution timeout are found, the program will immediately trigger the error handling mechanism.

[0186] 2. Abnormal capture and processing: the program uses try-catch statement blocks to capture possible exceptions; in the catch block, the program executes corresponding error handling logic according to the exception type, such as logging, releasing resources, etc.

[0187] 3. Automatic retry: for network delays, temporary resource unavailability, etc., the program will attempt to automatically retry the failed instructions. The retry mechanism can configure parameters such as the number of retries and the retry interval to balance performance and reliability.

[0188] In this embodiment, the on-orbit observation mode automatic planning device of the solar reflection band hyperspectral imager updates the orbit forecast data daily through a recursive strategy, with an update frequency of no less than once every 6 hours, to ensure the accuracy of the calculation of the observation angle under the inclined orbit.

[0189] In this embodiment, the observation target combination module supports various target observations and complex observation combinations included in the two observation modes of hyperspectral imager instrument self-calibration and Earth-Moon observation.

[0190] In this embodiment, the timing execution command generation process of the automatic planning device for on-orbit observation mode of the solar reflection band hyperspectral imager is described in [reference needed]. Figure 14 As shown, taking the daily instruction generation process as an example, see [link / reference]. Figure 15 As shown, the instructions are generated daily at a set time, producing two files: one containing only the instructions and the other containing the instructions' description. The instruction template for the automatic planning device of the on-orbit observation mode of the solar reflection band hyperspectral imager is as follows: Figure 16 As shown, the automatic planning device for on-orbit observation modes of the solar reflection band hyperspectral imager of this invention can read and parse orbit prediction files in real time, quickly calculate the position and angle of the observation target, and greatly shorten the planning time for observation tasks. Through intelligent sorting and planning, the device can prioritize high-priority observation tasks, ensuring that important scientific research targets are observed in a timely manner, thereby improving the overall observation efficiency.

[0191] The automatic on-orbit observation mode planning device for the solar reflection band hyperspectral imager of this invention can rationally plan observation time according to satellite orbit characteristics and instrument working capabilities, avoiding waste of observation resources; by setting an upper limit on the number of commands and a limit on the observation duration, it ensures the efficient execution of observation tasks, while reducing the demand on satellite buffering and maneuvering capabilities; the automated command generation and verification mechanism ensures the correctness and integrity of observation commands, reducing the risk of human error; the device adopts a modular design, with each module independent of the others, facilitating maintenance and upgrades, and enhancing the stability and reliability of the system.

[0192] It should be noted that the priority ranking of observation modes and the observation targets of each mode designed in this invention adopt the principle that instrument tracing has the highest priority and radiometric calibration transfer has the next highest priority. Any other scheme that only changes the priority of observation modes without adding new modes or new observation targets is considered to conflict with this invention and should not be protected.

[0193] The test method and observation target in the attenuator attenuation coefficient self-test mode of this invention are aimed at the scheme of observing the sun with a combination of dual rotating attenuator wheels. Other schemes that only change the structure of the attenuator wheels and the observation light source without changing the measurement method are considered to conflict with this invention and should not be protected.

[0194] The application designs a double-holiday judgment condition in the timing execution instruction generation process to realize the unattended operation of the observation mode automatic planning device, and other instruction generation process schemes that have no essential change and only make changes in holiday judgment are considered to conflict with the application and should not be protected.

[0195] The above is the exemplary embodiment disclosed by the application, but it should be noted that various changes and modifications can be made without departing from the scope of the embodiments disclosed by the application defined by the claims. The functions, steps and / or acts of the method claims described herein need not be performed in any particular order. Furthermore, although the elements of the embodiments disclosed by the application can be described or claimed in individual form, they can also be understood as plural unless explicitly limited to a single.

[0196] It should be understood that, as used herein, the singular forms "a", "an" and "the" are intended to include plural forms, unless the context clearly indicates otherwise. It should also be understood that "and / or" as used herein refers to any and all possible combinations of one or more of the associated listed items. The above-mentioned embodiment number of the embodiments disclosed by the application is only for description, not representing the advantages and disadvantages of the embodiments.

[0197] Those skilled in the art should understand that the above discussion of any embodiment is only exemplary and is not intended to imply that the scope of the embodiments disclosed by the application (including the claims) is limited to these examples; under the idea of the embodiments disclosed by the application, the technical features of the above embodiments or different embodiments can also be combined, and there are many other changes of the different aspects of the embodiments disclosed by the application as above. In order to be brief, they are not provided in details. Therefore, any omission, modification, equivalent replacement, improvement, etc. made in the spirit and principle of the embodiments disclosed by the application should be included in the protection scope of the embodiments disclosed by the application.

Claims

1. An on-orbit observation mode automatic planning device for a solar reflection band hyperspectral imager, characterized by, The device comprises the following modules: An orbit prediction analysis module: used for reading and analyzing satellite orbit prediction files in a timely manner, obtaining orbit prediction information of the satellite in the earth-centered inertial system, including the position, velocity, time and maneuver state identifier, and calculating the field of view angle and position parameters of the observation target in combination with the instrument installation coordinates; An observation mode priority sorting module: built-in priority rules of the moon observation mode and the self-calibration mode, dynamically adjusting the observation task priority according to the function composition, observation period and satellite sudden interruption event of the preset moon observation mode and self-calibration mode; An observation target combination module: used for calling the preset observation target combination rule according to different observation modes; A control instruction generation module: based on the orbit geometric model, calculating the observation time window, the azimuth angle and the elevation angle parameters of the turntable, and generating the instrument maneuver control instruction and the observation time length control instruction; An instruction verification and uploading module: using the cyclic redundancy check to verify the integrity of the instruction sequence, and injecting the verified instruction into the instrument execution controller through the instruction uploader; The observation target combination rule comprises: In the pseudo-invariant target observation mode, the field tracking observation, the solar spectrum irradiance observation and the instrument dark background observation are combined; In the self-calibration mode, the solar spectrum data are observed by the double-rotating attenuator wheel combination to generate the attenuation coefficient and the response linearity test instruction; The self-calibration mode is sorted in descending order of priority as follows: the attenuator attenuation coefficient self-check mode, the instrument linear response test mode, the instrument field of view homogenization mode and the spectral center wavelength test mode; The pseudo-invariant target observation mode in the observation target combination module comprises: The field replacement calibration mode: selecting a stable area to implement the area-to-earth observation, and combining the solar spectrum irradiance observation and the dark background data to complete the area-to-earth data radiation calibration and the emissivity calculation, and generating the radiation calibration transfer reference data set; The moon observation mode: in a specific lunar phase period, the moon spectrum irradiance observation data and the solar spectrum irradiance observation data are combined to calculate the lunar albedo and serve as the radiation calibration moon reference data set; The inter-satellite cross-calibration mode: according to the orbit parameters of the satellite where the hyperspectral imager is located and the satellite to be compared, the time and space parameters of the subsatellite point intersection event of the two satellites are predicted and the satellite where the hyperspectral imager is located is guided to carry out the earth maneuver observation; In the instruction verification and uploading module, the physical realizability of the observation instruction is verified by using the time sequence logic, including the matching of the turntable maneuver time and the observation time length; The on-orbit observation mode automatic planning device of the solar reflection band hyperspectral imager further comprises: A self-calibration mode triggering mechanism: dynamically generating the self-calibration task triggering instruction according to the periodic observation rule of the self-calibration parameters such as the instrument attenuation characteristics and the detector response uniformity; An emergency interruption response module: when the satellite is maneuvered, the current observation task is terminated and the remaining instruction sequence is re-planned.

2. The on-orbit observation mode automatic planning device for the solar reflection band hyper-spectral imager according to claim 1, characterized in that, In the observation mode priority sorting module: The priority rules of the moon observation mode are as follows: the pseudo-invariant target observation mode > the inter-satellite cross-calibration mode > the solar spectrum irradiance observation and the on-orbit tracing mode > the earth patrol mode. The self-calibration mode priority rules are: attenuator attenuation coefficient self-checking mode > instrument linear response test mode > instrument field of view homogenization mode > spectral center wavelength test mode; When the self-calibration mode is triggered, the priority is higher than all the lunar-terrestrial observation modes.

3. The on-orbit observation mode automatic planning device for the solar-reflective band hyperspectral imager according to claim 2, characterized in that, The lunar-terrestrial observation modes are ordered from high to low in priority as follows: pseudo-invariant target observation mode, inter-satellite cross-calibration mode, solar spectral irradiance observation and on-orbit traceability mode, and earth patrol mode.

4. The on-orbit observation mode automatic planning device for a solar reflection band hyper-spectral imager according to claim 1, wherein In the control instruction generation module, the solar / moon observation instruction parameters include a turntable azimuth angle and an elevation angle; and the earth observation instruction parameters include a sub-satellite point position, an observation time window, and a restriction condition of a field of view coverage range.

5. The on-orbit observation mode automatic planning device for the solar-reflective band hyperspectral imager according to claim 1, characterized in that, The on-orbit observation mode automatic planning device of the solar reflection band hyperspectral imager updates orbit prediction data every day through a recursive strategy, and the update frequency is not less than once every 6 hours; and the observation target combination module supports each target observation and complex observation combination contained in two observation modes of instrument self-calibration and lunar-terrestrial observation of the hyperspectral imager.

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