An on-orbit automatic operation and control method for a space remote sensing instrument for solar observation

Abstract

The present invention discloses an on-orbit automatic operation and control method for a solar observation space remote sensing instrument, which relates to the technical field of solar observation of remote sensing instruments, and solves the problem that the existing method needs to be carried out by injecting commands on the ground, and when communication problems occur, it affects the calibration of the instrument. The method is as follows: count the number of orbits M, and judge whether there is data injection. If not, take the integer part of M divided by i. If the remainder is 1, the instrument measures the dark current of multiple bands without solar tracking. If the data injection is to switch to the autonomous operation stage, M is cleared and re-counted, and m = [(M - 1) / i] + 1 is calculated. Take the remainder of m divided by 84. If the remainder is 0, perform the quarterly calibration process. If not, take the remainder divided by 28. If it is 0, perform the monthly calibration process. If not, take the remainder divided by 7. If it is 0, perform the weekly calibration process. If not, take the remainder of M divided by i. If the remainder is 1, perform the daily measurement process. If not, judge whether there is data injection.

Description

Technical Field

[0001] The present invention relates to the technical field of remote sensing instruments for solar observation, and particularly to an on-orbit automatic operation and control method for a space remote sensing instrument for solar observation. Background Art

[0002] Solar radiation, as the most important external energy outside the Earth, is an important criterion for evaluating solar activities. High-precision solar radiation measurement can be applied to the research of atmospheric physics and climate physics.

[0003] Space remote sensing instruments are widely used in various aspects, and the accurately measured remote sensing data can provide a scientific basis for multiple fields. Space remote sensing instruments are under the action of space radiation for a long time in orbit, and the performance of the optical system and detectors will inevitably decay. Especially for remote sensing instruments for solar observation, since they need to aim at the sun for a long time, the front-end optical system will be directly exposed to solar radiation for a long time.

[0004] To ensure that the instrument can work stably in orbit for a long time and ensure the accuracy of the remote sensing data obtained by the instrument, scientific designs in many aspects need to be carried out on the instrument.

[0005] As the control core of the instrument, the long-term stability of the electronics system is crucial. When designing the electronics, components with strong radiation resistance need to be selected and special radiation-resistant designs need to be carried out. The electronics system will undergo various harsh environmental tests on the ground, and after passing the tests, it can ensure the long-term stability of working in orbit.

[0006] On the premise that the electronic system meets the conditions, to ensure that the instrument can successfully complete the detection and calibration tasks in orbit, the design of the working mode and the on-orbit process needs to be carried out to obtain long-term detection data and calibration data at different times. The results of on-orbit in-orbit calibration can be used to monitor the long-term performance changes of the remote sensing instrument, intuitively reflect the working state of the remote sensing instrument in orbit, and at the same time, the results of on-orbit calibration are also used to correct the attenuation of the optical system and detectors.

[0007] Generally, the detection tasks of space remote sensing instruments can be automatically executed by program control, but the in-orbit calibration operation needs to be carried out by injecting commands from the ground. Since the satellite is working in orbit, the ground cannot guarantee real-time communication with it, and even if communication is carried out, the communication duration is very short. Therefore, it is necessary to design an operation and control method for a space remote sensing instrument for solar observation that can operate autonomously in orbit. Summary of the Invention

[0008] In order to solve the problem that the in-orbit calibration operation of the existing remote sensing instrument for solar observation needs to be carried out by injecting commands from the ground, which affects the calibration of the instrument when communication problems occur, the present invention provides an on-orbit automatic operation and control method for a space remote sensing instrument for solar observation, so that the space remote sensing instrument for solar observation can automatically perform calibration operations in orbit.

[0009] The technical solution adopted by the present invention to solve the technical problem is as follows:

[0010] An on-orbit automatic operation and control method for a solar observation space remote sensing instrument, comprising the following steps:

[0011] S1. Power on the instrument and proceed to S2;

[0012] S2. Count the number of orbits M of the instrument itself, and determine whether data is injected into the instrument. If no data is injected into the instrument, then take the integer part of M divided by i, where i is a positive integer greater than 1. If the remainder is 1, the instrument measures the dark current of multiple bands without solar tracking, otherwise repeat S2; if data is injected and the injected data includes an instruction to switch to the autonomous operation stage, then clear M and re-count M, and then proceed to S3;

[0013] S3. Calculate m = [(M - 1) / i]+1, take the remainder of m divided by j, where j is equal to 84, 87, 90, or 93. If the remainder is 0, perform the quarterly calibration process; if the remainder of m divided by j is not 0, then take the remainder of m divided by j / 3. If the remainder of m divided by j / 3 is 0, perform the monthly calibration process; if the remainder of m divided by j / 3 is not 0, then take the remainder of m divided by 7. If the remainder of m divided by 7 is 0, perform the weekly calibration process; if the remainder of m divided by 7 is not 0, then take the remainder of M divided by i. If the remainder of M divided by i is 1, perform the daily measurement process; if the remainder of M divided by i is not 1, determine whether data is injected. If data is injected, execute the corresponding command; if no data is injected, increment the orbit number count by 1, and repeat S3;

[0014] The quarterly calibration process, monthly calibration process, and weekly calibration process all include calibration operations.

[0015] The beneficial effects of the present invention are:

[0016] An on-orbit automatic operation and control method for a solar observation space remote sensing instrument of the present invention, with minimal ground intervention, uses the instrument orbit count to automatically complete the conversion of the working mode and the execution of the calibration processes at different times, ensuring the smooth progress of the on-orbit detection and calibration tasks of the instrument. At the same time, the ability to control the instrument with ground commands is retained to ensure the flexibility of control. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 It is a flowchart of an on-orbit automatic operation and control method for a solar observation space remote sensing instrument of the present invention.

[0018] Figure 2 It is a schematic diagram of the front-end design during the on-orbit operation of an on-orbit automatic operation and control method for a solar observation space remote sensing instrument of the present invention. DETAILED DESCRIPTION OF THE INVENTION

[0019] The present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments.

[0020] The present invention provides an on-orbit automatic operation and control method for a solar observation space remote sensing instrument.

[0021] An on-orbit automatic operation and control method for a solar observation space remote sensing instrument includes the following steps:

[0022] S1. Power on the instrument and proceed to S2.

[0023] S2. Count the number of orbits M of the instrument itself, and determine whether data is injected into the instrument. If no data is injected into the instrument, take the integer part of M divided by i, where i is a positive integer greater than 1. If the remainder is 1, measure the dark current of multiple bands without solar tracking. Otherwise, repeat S2. If data is injected and the injected data includes an instruction to switch to the autonomous operation mode, clear M and re-count the number of orbits M, and then proceed to S3.

[0024] S3. Calculate m = [(M - 1) / i] + 1, and take the remainder of m divided by j, where j is equal to 84, 87, 90, or 93. If the remainder is 0, perform the quarterly calibration process. If the remainder of m divided by j is not 0, take the remainder of m divided by j / 3. If the remainder of m divided by j / 3 is 0, perform the monthly calibration process. If the remainder of m divided by j / 3 is not 0, take the remainder of m divided by 7. If the remainder of m divided by 7 is 0, perform the weekly calibration process. If the remainder of m divided by 7 is not 0, take the remainder of M divided by i. If the remainder of M divided by i is 1, perform the daily measurement process. If the remainder of M divided by i is not 1, determine whether data is injected. If data is injected, execute the corresponding command. If no data is injected, increment the orbit number count and repeat S3.

[0025] The above quarterly calibration process, monthly calibration process, and weekly calibration process all include calibration operations, and the calibration operation is to measure and obtain calibration data.

[0026] The on-orbit automatic operation and control method for a solar observation space remote sensing instrument according to the present invention, with minimal ground intervention, uses the instrument orbit count to automatically complete the conversion of the working mode and the execution of the calibration processes at different times, ensuring the smooth progress of the on-orbit detection and calibration tasks of the instrument. At the same time, the ability to control the instrument with ground commands is retained to ensure the flexibility of control.

[0027] The above quarterly calibration process, monthly calibration process, weekly calibration process, and daily measurement process all include operations of solar tracking detection, that is, the solar measurement mode.

[0028] The overall on-orbit operation and control process of the instrument is as Figure 1As shown, the conversion of the working mode and the control of the operation and control process are automatically completed according to the instrument orbit count, greatly reducing the situation of sending control commands from the ground to the satellite and achieving full automation.

[0029] The operation and control method of the present invention will be described in detail below, where i = 14, j = 84, and j / 3 = 28.

[0030] An on-orbit automatic operation and control method for a solar observation space remote sensing instrument, as Figure 1 , includes the following steps:

[0031] S1. Power on the solar observation space remote sensing instrument. At this time, the orbit number M of the remote sensing instrument is 0, in the standby state, and proceed to S2;

[0032] S2. Count the orbit number M of the remote sensing instrument itself, and determine whether there is data injection into the instrument. If there is no data injection, take the integer part of M divided by 14 (i is a positive integer, 14 is taken in this embodiment). If the remainder is 1, the instrument starts the non-tracking dark current continuous spectrum measurement mode, otherwise repeat S2; if there is data injection, determine whether the injected data includes an instruction to switch to the autonomous operation stage. If it includes an instruction to switch to the autonomous operation stage, enter the autonomous operation stage. First, clear the orbit number count (re - count the orbit number), and then proceed to S3. If there is data injection and the injected data does not include an instruction to switch to the autonomous operation stage, execute the command corresponding to the injected data, and then re - execute S2;

[0033] The autonomous operation stage also includes S3.

[0034] S3. Calculate m = [(M - 1) / 14]+1, take the remainder of m divided by 84. If the remainder is 0, perform the quarterly calibration process. If the remainder when divided by 84 is not 0, take the remainder of m divided by 28. If the remainder when divided by 28 is 0, perform the monthly calibration process. If the remainder when divided by 28 is not 0, take the remainder of m divided by 7. If the remainder when divided by 7 is 0, perform the weekly calibration process. If the remainder when divided by 7 is not 0, take the remainder of M divided by 14. If the remainder when divided by 14 is 1, perform the daily measurement process. If the remainder when divided by 14 is not 1, determine whether there is data injection. If there is data injection, execute the corresponding command. If there is no data injection, increment the orbit number count by 1, and repeat S3;

[0035] The above - mentioned quarterly calibration process is as follows:

[0036] Step 3.11. Let m 季 = M;

[0037] Step 3.12. Calculate a = M - m 季, if a is equal to 0 or 14, the instrument automatically switches to the solar measurement mode; if a is equal to 3, the instrument automatically switches to the first UV backup board comparison mode; if a is equal to 6, the instrument automatically switches to the dark current continuous spectrum measurement mode without tracking; if a is equal to 10, the instrument automatically switches to the full-channel backup board comparison mode; if a is equal to 18, the instrument automatically switches to the spectral calibration mode; if a is equal to 22, the instrument automatically switches to the VIS tungsten lamp first mode; if a is equal to 27, update M (M' = M + 1, and let M = M'), and execute S3 again. If a does not belong to any of the above cases, that is, is not equal to any one of 0, 3, 6, 10, 14, 18, 22, and 27, update M (M' = M + 1, and let M = M'), and return to step 3.12 to execute step 3.12 again.

[0038] The above monthly calibration process is as follows:

[0039] Step 3.21: Let m 月 = M;

[0040] Step 3.22: Calculate b = M - m 月 , if b is equal to 0 or 14, the instrument automatically switches to the solar measurement mode; if b is equal to 3, the instrument automatically switches to the first UV backup board comparison mode; if b is equal to 6, the instrument automatically switches to the dark current continuous spectrum measurement mode without tracking; if b is equal to 10, the instrument automatically switches to the full-channel backup board comparison mode; if b is equal to 18, the instrument automatically switches to the spectral calibration mode; if b is equal to 27, update M (M' = M + 1, and let M = M'), and execute S3 again. If b does not belong to any of the above cases, that is, is not equal to any one of 0, 3, 6, 10, 14, 18, and 27, update the M orbit number count by 1 (M' = M + 1, and let M = M'), and return to step 3.22 to execute step 3.22 again.

[0041] The above weekly calibration process is as follows:

[0042] Step 3.31: Let m 周 = M;

[0043] Step 3.32: Calculate c = M - m 周 , if c is equal to 0, the instrument automatically switches to the solar measurement mode; if c is equal to 7, the instrument automatically switches to the first UV backup board comparison mode; if c is equal to 13, update M (M' = M + 1, and let M = M'), and execute S3 again. If c does not belong to any of the above cases, that is, is not equal to any one of 0, 7, and 13, update M, that is, the orbit number count by 1 (M' = M + 1, and let M = M'), and return to step 3.32 to execute step 3.32 again.

[0044] The above daily measurement process is as follows:

[0045] Step 3.41: Let m 日 = M. The instrument automatically switches to the solar measurement mode. After completing the solar measurement mode, update M, that is, increment the orbit number count by 1 (M' = M + 1, let M = M'), and return to S3 to re - execute step 3.

[0046] The above - mentioned on - orbit automatic operation and control method for a solar - observing space remote - sensing instrument further includes an annual calibration process.

[0047] As an embodiment, the annual calibration process is executed through data injection so that it can be carried out at any time when needed, improving the flexibility of control. After injection, stop the autonomous operation phase and start the annual calibration process.

[0048] As another embodiment, the annual calibration process belongs to the autonomous operation phase. The operation and control method of the present invention is specifically as follows:

[0049] S1 and S2 are the same as the above process.

[0050] S3: Calculate m = [(M - 1) / i]+1. Take the remainder of m divided by k, where k is 365, 366 or 4j. If the remainder of the division by k is 0, then perform the annual calibration process; otherwise, take the remainder of m divided by j, where j is equal to 84, 87, 90 or 93. If the remainder is 0, then perform the quarterly calibration process. If the remainder of the division by 84 is not 0, then take the remainder of m divided by 28. If the remainder of the division by 28 is 0, then perform the monthly calibration process. If the remainder of the division by 28 is not 0, then take the remainder of m divided by 7. If the remainder of the division by 7 is 0, then perform the weekly calibration process. If the remainder of the division by 7 is not 0, then take the remainder of M divided by i. If the remainder of the division by i is 1, then perform the daily measurement process. If the remainder of the division by i is not 1, then determine whether there is data injection. If there is data injection, execute the corresponding command. If there is no data injection, increment the orbit number count by 1 and repeat the execution of S3.

[0051] The above annual calibration process is as follows:

[0052] S3.51: Let m 年 = M;

[0053] S3.52: Calculate d = M – m 年, if d equals 0 or 14, the instrument automatically switches to the solar measurement mode; if d equals 3, the instrument automatically switches to the first UV backup board comparison mode; if d equals 5, the instrument automatically switches to the dark current continuous spectrum measurement mode without tracking; if d equals 8, the instrument automatically switches to the full-channel backup board comparison mode; if d equals 11, the instrument automatically switches to the second UV backup board comparison mode; if d equals 17, the instrument automatically switches to the spectral calibration mode; if a equals 20, the instrument automatically switches to the VIS tungsten lamp first mode; if d equals 23, the instrument automatically switches to the VIS tungsten lamp second mode. If d does not fall into any of the above cases, that is, it is not equal to any of 0, 3, 5, 8, 11, 17, 20, and 23, then update M (M' = M + 1, let M = M'), and return to step 3.52 to re-execute step 3.52.

[0054] The on-orbit operation and control process is divided into the initial on-orbit stage and the autonomous operation stage. Starting from when the instrument is powered on after the satellite platform is stable until the ground sends a control command (instruction) to the satellite to switch to the autonomous operation stage, it is the initial on-orbit stage. The initial on-orbit stage is used to verify whether the functions of each component of the instrument and the data transmission link are normal, and by default, a dark current continuous spectrum measurement mode without tracking is carried out once a day (taking 14 orbits as an example).

[0055] After switching to the autonomous operation stage, it is divided into daily measurement, weekly calibration, monthly calibration, quarterly calibration, and annual calibration according to the mission type and execution cycle. The execution cycle of daily measurement is once a day, the execution cycle of weekly calibration is once a week, the execution cycle of monthly calibration is once a month, the execution cycle of quarterly calibration is once a quarter (3 months), and the execution cycle of annual calibration is once a year (12 months).

[0056] Comparing the daily measurement data detected by the instrument with the calibration data of different execution cycles can be used to correct the decay of the optical system and the detector caused by space radiation. The calibration data of weekly calibration is compared and corrected with the daily measurement detection data, the calibration data of monthly calibration is compared and corrected with the weekly calibration and daily measurement data, the calibration data of quarterly calibration is corrected and compared with the monthly calibration, weekly calibration, and daily measurement data, and the calibration data of annual calibration is corrected and compared with the quarterly calibration, monthly calibration, weekly calibration, and daily measurement data.

[0057] In order to ensure the flexibility of instrument control and restore the instrument to normal through ground control in the event of an emergency, the on-orbit automated control process can also change the working mode through ground injection commands. In the initial stage on-orbit, when data injection conflicts with the default working mode, data injection is performed; in the autonomous operation stage, when data injection conflicts with the default working mode, the default working mode is executed in this embodiment (i.e., the autonomous operation stage is executed), but it is not limited to this. The calibration process of different cycles is a whole and cannot be interrupted by other modes, and the required calibration data can be fully acquired. Therefore, in order to ensure the smooth progress of the instrument's on-orbit detection and calibration tasks, while minimizing ground intervention, the present invention uses instrument orbit counting to automatically complete the conversion of working modes and the execution of calibration processes in different periods. At the same time, in order to ensure the flexibility of control and safety in the event of an emergency, the ability to change the working mode by ground commands is retained.

[0058] The space remote sensing instrument for solar observation has a set of commonly used main boards, multiple sets of spare boards and blind boards. Different windows are used in different working modes for detection or calibration. At the same time, the obtained spectral data are cross-compared to correct the attenuation of the optical system and detector. Figure 2 As shown, sunlight passes through the flat window and then through the attenuation plate or filter into the instrument.

[0059] The space remote sensing instrument has a standby mode and an operating mode. The operating mode includes multiple modes, including: solar measurement mode, first UV standby plate comparison mode, full channel standby plate comparison mode, second UV standby plate comparison mode, VIS tungsten lamp first mode, VIS tungsten lamp second mode, spectrum calibration mode, dark current continuous spectrum measurement mode without tracking, cold air mode, dark current continuous spectrum measurement mode under tracking, dark current fixed-point measurement mode without tracking, and pointing adjustment mode. The conversion between any two operating modes is carried out through the standby mode, and the original operating mode is first converted to the standby mode and then converted to the target operating mode. For example, the original operating mode is the dark current continuous spectrum measurement mode without tracking, and the target operating mode is the solar measurement mode. The dark current continuous spectrum measurement mode without tracking is converted to the solar measurement mode through the standby mode.

[0060] Standby mode: The instrument enters standby mode after power-on or any working mode ends. The switching between various working modes is carried out through the standby mode, and the original working mode is switched to the standby mode and then to the target working mode.

[0061] Sun measurement mode: It belongs to the detection mode and is used to obtain fixed-cycle sun detection data. The sun measurement mode uses the mainboard to track the sun.

[0062] The first UV spare board comparison mode: This mode includes calibration (calibration operation). In this mode, the first set of spare boards is used for solar tracking measurement to obtain calibration data under the backup window, and the calibration data under the backup window is compared with the daily detection data;

[0063] Full-channel spare board comparison mode: This mode includes calibration. In this mode, the second set of spare boards is used for solar tracking measurement to obtain calibration data under the full-channel backup window, and the calibration data under the full-channel backup window is compared with the daily detection data;

[0064] The second UV spare board comparison mode: This mode includes calibration. In this mode, the third set of spare boards is used for solar tracking measurement to obtain calibration data under the backup window, and the calibration data under this backup window is compared with the calibration data of the full-channel spare board comparison mode;

[0065] VIS tungsten lamp first mode: This mode includes calibration. In this mode, the first blind plate is used to block sunlight from entering the instrument, and the spectral data of the primary tungsten lamp is measured. The obtained spectral data of the primary tungsten lamp is used for radiometric calibration;

[0066] VIS tungsten lamp second mode: This mode includes calibration. In this mode, the first blind plate is used to block sunlight from entering the instrument, and the spectral data of the backup tungsten lamp is measured. The obtained spectral data of the backup tungsten lamp is used for radiometric calibration and compared with the spectral data of the primary tungsten lamp;

[0067] Spectral calibration mode: This mode includes calibration. In this mode, the first blind plate is used to block sunlight from entering the instrument, and the spectral data of the mercury lamp is measured. The spectral data of the mercury lamp is used for spectral calibration;

[0068] Dark current continuum measurement mode without tracking: In this mode, without solar tracking, the first blind plate is used to block sunlight from entering the instrument. This mode is the main working mode in the initial stage of orbit. This mode is used to (in the initial stage of orbit) verify whether the functions of each component of the space remote sensing instrument and the data transmission link are normal. At the same time, this mode can measure the dark background of each band, that is, measure the dark current of multiple bands. The obtained dark background of each band is used for remote sensing data processing;

[0069] Cold space mode: This mode includes calibration. The main board is used for cold space detection, and the cold space detection results are used for comparison with the solar measurement data;

[0070] Dark current continuum measurement mode with tracking: This mode includes calibration. The first blind plate is used to block sunlight from entering the instrument, and the dark background of each band is measured during solar tracking to verify the influence of the solar tracking device on the dark background;

[0071] Dark current fixed-point measurement mode without tracking: This mode includes calibration. A first blind plate is used to block sunlight from entering the instrument. Multiple measurements of the dark background are performed at specific wavelength positions to calculate the average value of the dark background;

[0072] Pointing adjustment mode: Without detection, this mode is used to verify the function and accuracy of the solar tracking device.

[0073] The windows and working cycles used in each working mode are different, so long-term detection data and calibration data for different cycles can be obtained and compared and corrected with each other.

[0074] Among them, the dark current continuous spectrum measurement mode without tracking can inject data into the instrument and can also be used as a working mode during the autonomous operation stage of the instrument, and can also be operated in the initial stage of orbit.

[0075] The full-channel spare board comparison mode, the dark current continuous spectrum measurement mode without tracking, the solar measurement mode, the second UV spare board comparison mode, the VIS tungsten lamp first mode, the spectral calibration mode, the first UV spare board comparison mode, and the VIS tungsten lamp second mode can all inject data into the instrument and can also be used as a working mode during the autonomous operation stage of the instrument.

[0076] The dark current continuous spectrum measurement mode with tracking, the cold sky mode, and the pointing adjustment mode are all modes in which the instrument executes the corresponding mode after data is injected into the instrument, and do not belong to the autonomous operation stage.

[0077] The data injection described in the above S2 and S3 can be an instruction to execute a certain working mode, that is, the data injected can be an instruction to switch to a certain working mode.

[0078] It should be noted that the descriptions involving "first", "second", etc. in this application are only for descriptive purposes and should not be construed as indicating or implying their relative importance or implicitly specifying the quantity of the indicated technical features.

[0079] The above are only the preferred embodiments of the present invention. It should be pointed out that for those of ordinary skill in the art, without departing from the principle of the present invention, several improvements and refinements can be made, and these improvements and refinements should also be regarded as the protection scope of the present invention.

Claims

1. An on-orbit automated control method for a solar observation space remote sensing instrument, characterized in that: The steps include: S1, power on the instrument and proceed to S2; S2, count the number of tracks M of the instrument itself, and determine whether there is data injected into the instrument. If no data is injected into the instrument, M is rounded to i, where i is a positive integer greater than 1. If the remainder is 1, the instrument measures the dark current of multiple bands without sun tracking, otherwise S2 is re-executed; if data is injected and the injected data includes an instruction to switch to the autonomous operation stage, M is cleared and M is counted again, and then S3 is performed; S3, calculate m=[(M-1) / i]+1, m takes the remainder with respect to j, where j is equal to 84, 87, 90 or 93, if the remainder is 0, then perform the quarterly calibration process, if the remainder with respect to j is not 0, then m takes the remainder with respect to j / 3, if the remainder with respect to j / 3 is 0, then perform the monthly calibration process, if the remainder with respect to j / 3 is not 0, then m takes the remainder with respect to 7, if the remainder with respect to 7 is 0, then perform the weekly calibration process, if the remainder with respect to 7 is not 0, then M takes the remainder with respect to i, if the remainder with respect to i is 1, then perform the daily measurement process, if the remainder with respect to i is not 1, then determine whether there is data injection, if there is data injection, execute the corresponding command, if there is no data injection, then add 1 to the orbit number count, and repeat S3; The quarterly calibration process, monthly calibration process, and weekly calibration process all include calibration operations.

2. The on-orbit automatic operation and control method of a solar observation space remote sensing instrument according to claim 1, characterized in that: The instrument has a standby mode and an operating mode, wherein the operating mode includes a solar measurement mode, a first UV standby plate comparison mode, a dark current continuous spectrum measurement mode without tracking, a full-channel standby plate comparison mode, a spectrum calibration mode, and a VIS tungsten lamp first mode; the conversion between any two operating modes is performed through the standby mode; the instrument enters a dark current continuous spectrum measurement mode without tracking when measuring dark currents of multiple bands without sun tracking.

3. The on-orbit automatic operation and control method of a solar observation space remote sensing instrument according to claim 2, characterized in that, The solar measurement mode is used to obtain solar detection data of a fixed period; The first UV backup board comparison mode is used to obtain calibration data under the backup window for daily tracking measurement, and compare the calibration data under the backup window with the daily detection data; The dark current continuous spectrum measurement mode without tracking is used to verify whether the functions of each component of the instrument and the data transmission link are normal, and is used to measure the dark current of each band; the full-channel backup board comparison mode is used to obtain the calibration data under the full-channel backup window for daily tracking measurement, and compare the calibration data under the full-channel backup window with the daily detection data; the spectral calibration mode is used to block sunlight from entering the instrument and measure the spectral data of the mercury lamp at the same time, and the spectral data of the mercury lamp is used for spectral calibration; the VIS tungsten lamp first mode is used to block sunlight from entering the instrument and measure the spectral data of the main tungsten lamp at the same time, and the spectral data of the main tungsten lamp is used for radiation calibration.

4. The on-orbit automatic operation and control method for a solar observation space remote sensing instrument according to claim 2 or 3, characterized in that, The working modes include a second UV standby board comparison mode, a VIS tungsten lamp second mode, a cold air mode, a dark current continuous spectrum measurement mode under tracking, a dark current fixed-point measurement mode under non-tracking, and a pointing adjustment mode; The second UV standby board comparison mode is used to obtain calibration data under the backup window for daily tracking measurement, and compare the calibration data under the backup window with the calibration data of the full-channel standby board comparison mode; The second mode of VIS tungsten lamp is used to block sunlight from entering the instrument and measure the spectral data of the backup tungsten lamp at the same time. The spectral data of the backup tungsten lamp is used for radiation calibration and for comparison with the spectral data of the main tungsten lamp; the cold space mode is used for cold space detection, and the results of cold space detection are used for comparison with solar measurement data; the dark current continuous spectrum measurement mode under tracking is used to block sunlight from entering the instrument and perform dark current measurements in various bands for sun tracking; the dark current fixed-point measurement mode under non-tracking is used to block sunlight from entering the instrument and perform multiple measurements of dark current at specific wavelength positions; the pointing adjustment mode is used to verify the function and accuracy of the sun tracking equipment.

5. The on-orbit automatic operation and control method of a solar observation space remote sensing instrument according to claim 1, characterized in that: The seasonal calibration process is as follows: Step 3.11, let m 季 = M; Step 3.

12. Calculate a = M - m 季 , if a = 0 or a = 14, the instrument automatically switches to the solar measurement mode; if a = 3, the instrument automatically switches to the first UV standby board comparison mode; if a = 6, the instrument automatically switches to the dark current continuous spectrum measurement mode without tracking; if a = 10, the instrument automatically switches to the full-channel standby board comparison mode; if a = 18, the instrument automatically switches to the spectral calibration mode; if a = 22, the instrument automatically switches to the VIS tungsten lamp first mode; if a = 27, then M' = M + 1, let M = M', and re-execute S3; if a is not equal to any one of 0, 3, 6, 10, 14, 18, 22, and 27, then M' = M + 1, let M = M', and re-execute Step 3.

12.

6. The on-orbit automatic operation and control method of a solar observation space remote sensing instrument according to claim 1, characterized in that: The monthly calibration process is as follows: Step 3.21, let m 月 = M; Step 3.22, calculate b = M - m 月 , if b = 0 or b = 14, the instrument automatically switches to the solar measurement mode; if b equals 3, the instrument automatically switches to the first UV backup board comparison mode; if b equals 6, the instrument automatically switches to the dark current continuous spectrum measurement mode without tracking; if b = 10, the instrument automatically switches to the full-channel backup board comparison mode; if b = 18, the instrument automatically switches to the spectral calibration mode; if b = 27, then M' = M + 1, let M = M', and re-execute S3; if b is not equal to any one of 0, 3, 6, 10, 14, 18, and 27, then M' = M + 1, let M = M', and re-execute Step 3.

22.

7. The on-orbit automatic operation and control method of a solar observation space remote sensing instrument according to claim 1, characterized in that: The weekly calibration process is as follows: Step 3.

31. Let m 周 = M; Step 3.32, calculate c = M – m 周 , if c = 0, the instrument automatically switches to the sun measurement mode; if c = 7, the instrument automatically switches to the first UV standby board comparison mode; if c = 13, then M’ = M + 1, let M = M’, and re - execute S3; if c is not equal to any one of 0, 7, and 13, then M’ = M + 1, let M = M’, and re - execute Step 3.

32.

8. The on-orbit automatic operation and control method of a solar observation space remote sensing instrument as claimed in claim 1, characterized in that: The daily measurement process is as follows: Let m 日 = M. The instrument automatically switches to the solar measurement mode. After completing the solar measurement mode, M' = M + 1. Let M = M', and repeat step 3.

9. The on-orbit automatic operation and control method of a solar observation space remote sensing instrument according to claim 1, characterized in that: The operation and control method includes injecting an annual calibration process execution command into the instrument by means of data injection.

10. The on-orbit automatic operation and control method of a solar observation space remote sensing instrument according to claim 9, characterized in that: The annual calibration process is as follows: S3.

51. Let m 年 = M; S3.

52. Calculate d = M – m 年 , if d is equal to 0 or 14, the instrument automatically switches to the solar measurement mode; if d is equal to 3, the instrument automatically switches to the first UV backup board comparison mode; if d is equal to 5, the instrument automatically switches to the dark current continuous spectrum measurement mode without tracking; if d is equal to 8, the instrument automatically switches to the full-channel backup board comparison mode; if d is equal to 11, the instrument automatically switches to the second UV backup board comparison mode; if d is equal to 17, the instrument automatically switches to the spectral calibration mode; if a is equal to 20, the instrument automatically switches to the VIS tungsten lamp first mode; if d is equal to 23, the instrument automatically switches to the VIS tungsten lamp second mode; if d is not equal to any one of 0, 3, 5, 8, 11, 17, 20, and 23, then M' = M + 1, let M = M', and re-execute step 3.52.

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