A method for orbital process control of spaceborne equipment with adjustable multidimensional parameters

Abstract

This invention provides a multi-dimensional parameter adjustable orbital process control method for spaceborne equipment, belonging to the field of remote sensing technology. The method includes: Step S1, receiving the test phase of the payload; Step S2, determining the test content based on the test phase; Step S3, obtaining test working parameters based on the test content; Step S4, generating payload orbital process annotation instructions according to the satellite annotation instruction format by combining the test process event set, the execution time set, and the imaging mode set based on the orbital process test task model; Step S5, scheduling and executing the payload's Earth observation and calibration tasks according to the satellite orbital period via the main controller based on the payload orbital process annotation instructions. This invention solves the problem of inconsistent parameters in phased ground testing and on-orbit testing of the payload, providing high test coverage and effectively improving the system's testing flexibility and convenience.

Description

Technical Field

[0001] This invention relates to the field of remote sensing technology, and in particular to a method for controlling the orbital process of spaceborne equipment with adjustable multi-dimensional parameters. Background Technology

[0002] Spaceborne remote sensing equipment, carried on satellite platforms, conducts Earth observations, acquiring important characteristic parameters of the Earth's surface and atmosphere. It is a crucial tool in fields such as atmospheric environmental monitoring, meteorology, and military reconnaissance, possessing significant scientific and practical value. For example, a spaceborne imaging spectrometer can obtain spectral information from solar backscattering at the Earth's surface. This spectral information represents the absorption spectra after absorption by gas molecules along atmospheric transport paths, containing characteristic absorption information of certain gaseous components such as nitrogen oxides, sulfides, and ozone. Differential absorption spectroscopy algorithms can be used to deduce the concentration of trace gases in the Earth's atmosphere, obtaining hyperspectral remote sensing products in the ultraviolet to visible bands, enabling quantitative monitoring of the distribution and changes of trace atmospheric components globally. Quantitatively obtaining information on global air quality changes and the distribution and transport processes of pollutants and aerosols, monitoring the impact of industrial emissions and bioburning on atmospheric composition and global climate change, can contribute to the establishment of an atmospheric composition monitoring and early warning technology system.

[0003] The main controller is the core control unit of the spaceborne imaging spectrometer, responsible for setting and managing the orbital procedures and parameters. Atmospheric environment monitoring satellites typically operate in sun-synchronous orbits, and the detection area, light intensity, and latitude of the detection area vary with each orbit around the Earth (e.g., land detection versus ocean detection, illuminated area detection versus shadowed area detection), resulting in payloads with multiple imaging mode parameters. These payload imaging mode parameters need to be adjusted according to the satellite's orbital position to meet different detection requirements. Reasonable and efficient orbital scheduling and flexible and reliable parameter control are crucial for acquiring remote sensing information of the target area and achieving mission objectives.

[0004] The conventional control methods of the spaceborne master controller for the payload include: (1) a fixed orbit process design, in which the payload works strictly according to the orbit process set by the master controller. Its characteristics are high reliability of orbit process execution, but its disadvantage is weak adaptability. It is suitable for some application scenarios with relatively fixed parameters; (2) a fixed orbit process design, in which the payload master controller can receive the injection modification of some key parameters, and then the payload works strictly according to the orbit process set by the master controller. It has a certain degree of adaptability, but only a small number of key parameters can be adjusted. Summary of the Invention

[0005] The purpose of this invention is to provide a multi-dimensional parameter adjustable orbital process control method for spaceborne equipment, which solves the problems of weak adaptability and limited adjustable parameters in existing orbital process testing.

[0006] To achieve the above objectives, the present invention provides a method for orbital process control of spaceborne equipment with adjustable multi-dimensional parameters, the method comprising:

[0007] Step S1: Receive the test phase of the load. The test phase includes the preliminary research phase, the initial prototype design phase, and the final prototype design phase.

[0008] Step S2: Determine the test content according to the test stage. The test content includes acceptance test, satellite installation test, integrated electrical test, thermal test and launch site test.

[0009] Step S3: Obtain test working parameters based on the test content. The test working parameters include a set of test process events, a set of execution times, and a set of imaging modes. Establish a track process test task model based on the test working parameters.

[0010] Step S4: Based on the orbital process test task model, generate payload orbital process annotation instructions by combining the test process event set, the execution time set, and the imaging mode set according to the satellite annotation instruction format;

[0011] Step S5: According to the payload orbit process annotation instructions, the main controller schedules and executes the payload Earth observation and calibration tasks according to the satellite orbit period.

[0012] The beneficial effects of this invention are as follows:

[0013] This invention provides a basis and reference for the ground testing and on-orbit application parameter adjustment of the spaceborne imaging spectrometer payload system, solves the problem of inconsistent parameters in the phased ground testing and on-orbit testing of the payload, has high test coverage, and effectively improves the system testing flexibility and convenience. Specifically, it includes: (1) all parameters involved in various orbital process test tasks can be adjusted through the annotation command. Each orbital process test task can set multiple test process events, and the test process events can be set with arbitrary execution time and imaging mode; (2) various orbital process tasks can be scheduled through the annotation command, and the most commonly used orbital process task parameters are stored in the various designed orbital processes, which is conducive to the calling of the payload master controller, and the orbital process tasks in the actual on-orbit application of the payload can meet the test requirements. Attached Figure Description

[0014] The accompanying drawings are provided to further illustrate embodiments of the present invention and form part of the specification. They are used together with the following detailed description to explain the embodiments of the present invention, but do not constitute a limitation thereof. In the drawings:

[0015] Figure 1 A flowchart of the orbital process control method for spaceborne equipment with adjustable multi-dimensional parameters provided by the present invention;

[0016] Figure 2 This is a schematic diagram of the orbital process priority for the multi-dimensional parameter adjustable orbital process control of spaceborne equipment provided by the present invention. Detailed Implementation

[0017] To make the objectives, technical solutions, and advantages of this invention clearer, the invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative and not intended to limit the invention. Furthermore, the technical features involved in the various embodiments of this invention described below can be combined with each other as long as they do not conflict with each other. To achieve the above objectives, this invention adopts the following technical solution.

[0018] Figure 1 A flowchart of the multi-dimensional parameter adjustable orbital process control method for spaceborne equipment provided by the present invention is shown below. Figure 1 As shown, the method includes:

[0019] Step S1: Receive the test phase of the load. The test phase includes the preliminary research phase, the initial prototype design phase, and the final prototype design phase.

[0020] Step S2: Determine the test content according to the test phase. The test content includes acceptance test, satellite installation test, integrated electrical test, thermal test and launch site test.

[0021] Step S3: Obtain test working parameters based on the test content. The test working parameters include the test process event set, execution time set, and imaging mode set. Establish a track process test task model based on the test working parameters.

[0022] Step S4: Based on the orbital process test task model, generate payload orbital process annotation instructions by combining the test process event set, execution time set, and imaging mode set according to the satellite annotation instruction format;

[0023] Step S5: According to the payload orbit process annotation instructions, the main controller schedules and executes the payload Earth observation and calibration tasks according to the satellite orbit period.

[0024] The track process test task model has a tree structure, including a set of track process test tasks, a set of test process events, a set of execution times, and a set of imaging modes from top to bottom. The track process test task model includes multiple track process test tasks (i.e., a set of track process test tasks). Each track process test task corresponds to a set of test process events. Each test process event in the set of test process events corresponds to an execution time to form an execution time set. At each execution time, the corresponding imaging mode is executed to form an imaging mode set.

[0025] In space payload missions, payload development is generally divided into three phases according to schedule: pre-research, prototype design, and final design. Throughout the development cycle, a series of tests are conducted based on the objectives of each phase. The orbital process tests at each phase are particularly important for the payload. These orbital process tests include acceptance testing, satellite installation testing, integrated electrical testing, thermal testing, and launch site testing.

[0026] The test process events include dark background test events, standby events, internal lamp pixel detection and calibration test events, and normal observation events. Each test process event corresponds to a specific load observation or calibration task.

[0027] The execution time is less than or equal to the satellite's orbital period, which is calculated using spacecraft orbital dynamics formulas.

[0028] The imaging mode is composed of the integration time of the charge-coupled device (CCD) detector, the CCD image pixel merging mode, and the CCD imaging gain coefficient. The integration time, CCD image pixel merging mode, and imaging gain coefficient are predetermined based on the intensity of backscattered solar light from the Earth through ground simulation or on-orbit calibration data.

[0029] The payload master controller defines the specific tasks performed by the payload within one orbital period around the Earth as "orbital process test tasks" and their corresponding "test process events," "execution times," and "imaging modes." The master control program schedules the imaging modes of each event sequentially according to a predetermined order, ultimately completing all test process events. "Orbital process test tasks" are performed on a per-orbit basis, with the payload executing one test task per orbit. Each test task consists of n test process events, where n can be, for example, 16. The test process events are executed sequentially according to their numbers, and each test process event has a corresponding execution time. "Imaging modes" can be arbitrarily set according to the payload's imaging mode and parameters, with each test process event corresponding to any imaging mode. The parameter definitions, execution order, and "execution times" of the "orbital process test tasks," "test process events," and "imaging modes" can all be arbitrarily modified or recombinated using annotation commands, thereby achieving orbital number control.

[0030] One orbit around the Earth constitutes one orbit. The main controller uses the nadir night command received from the satellite platform as the start time for a new orbit. An orbital procedure test task is an abstraction by the main control program of "the satellite executing a series of corresponding test procedure events (i.e., combinations of observation or calibration events) during its orbit around the Earth in different time zones," defined as a set of test procedure events (e.g., a set of n test procedure events). The main control software allows users to define multiple (e.g., 16) different test procedure events; that is, a test procedure event set includes multiple test procedure events. Each orbital procedure test task contains an execution orbital period parameter q, where q is a positive integer. This means that an orbital procedure test task is scheduled once every q orbits. The execution priority can be identified by the orbital procedure test task number. When two single-orbit orbital procedure test task periods overlap, the main control program schedules the higher-priority orbital procedure test task and the lower-priority orbital procedure test task in the next orbit. When executing a test procedure event, the main control program uses the imaging mode parameters defined in the test procedure event as the current system parameters, and this continues until the end of that test procedure event.

[0031] This invention takes the specific implementation process of an atmospheric trace gas differential absorption spectrometer (EMI) payload as an example.

[0032] First, the track process test task model is designed as follows:

[0033] 1) Track process test task set This indicates that k represents the number of track process test tasks. This represents the m-th orbital process test task, where m is an integer from 1 to k, designed according to the spectral imaging requirements;

[0034] 2) Test process event set E indicates i This represents the i-th test process event, where n is the number of test process events, and i is an integer from 1 to n, which can be determined according to different test requirements;

[0035] 3) Set of execution times for test process events , among which, T i This represents the execution time of the i-th test process event. The execution time is in seconds. The orbital period of the satellite is calculated using the spacecraft orbital dynamics formula. The payload in this invention is in a sun-synchronous orbit satellite with a fixed orbital period of approximately 100 minutes.

[0036] 4) Imaging mode set It means that, among them, This represents the integration time of the charge-coupled device detector corresponding to the i-th test procedure event in the u-th spectral imaging channel. This represents the charge-coupled device (CCD) imaging pixel combining mode corresponding to the i-th test procedure event in the u-th spectral imaging channel. This represents the imaging gain coefficient of the charge-coupled device (CCD) corresponding to the i-th test process event in the u-th spectral imaging channel, where u is an integer from 1 to j, and j is the number of spectral imaging channels. The integration time, CCD imaging pixel merging mode, and imaging gain coefficient are predetermined based on the intensity of backscattered solar light from the Earth through ground simulation or on-orbit calibration data. For example, when the satellite's nadir point passes over the ocean, a set of parameters for the integration time, CCD imaging pixel merging mode, and imaging gain coefficient are pre-calculated; when it passes over land, a set of parameters for the integration time, CCD imaging pixel merging mode, and imaging gain coefficient are calculated.

[0037] Each test process event is configured individually. The individual configuration includes setting the enable status, execution order, and associated parameters for each test process event independently. When performing load orbit process testing on the ground, all pre-set test cases are traversed according to the individual configuration to verify the functional correctness of each test process event.

[0038] The set of orbital process test tasks includes at least standby process tasks, calibration process tasks, Earth observation tasks, and dark background test tasks.

[0039] The orbital procedure test task set can also include ground test tasks for conducting ground tests on all preset orbital procedure test tasks. Specifically, it can cover all preset test procedure events, preset execution times, and preset imaging modes. In practice, ground test tasks can be set to the highest priority.

[0040] Step S2 includes: determining the test content based on the test phase using the load task book, which includes the correspondence between the test phase and the test content. Specifically, the test content is determined by the test requirements pre-set in the load task book.

[0041] Step S5 includes: according to the payload orbit process annotation command, after receiving the satellite nadir point night command, executing the orbit process test task, the ground imaging area corresponding to the payload is night, the payload executes the dark background test task in the ground imaging area, after the dark background test is completed, the calibration process task of internal lamp pixel detection is carried out, and the Earth observation task is executed in the illuminated area.

[0042] Figure 2 This invention provides a schematic diagram of the orbital process priority for orbital process control of spaceborne equipment with adjustable multidimensional parameters, as shown in the following figure. Figure 2The diagram illustrates the priority scheduling logic when multiple track process test tasks coexist. When processes from different cycles conflict in time, the system makes a decision based on preset static priorities, ensuring that high-priority processes execute first, while low-priority processes are deferred to the next available track cycle. Figure 2 In the test task set for the track process, k takes the value of 8, and in the test process event, n takes the value of 16, such as... Figure 2 As shown, processes 1, 2...8 represent the track process test tasks. , ... Event 1, Event 2...Event 16 represent the test process events respectively. , ... ,exist Figure 2 In this process, process 1 has the highest priority.

[0043] The optional embodiments of the present invention have been described in detail above with reference to the accompanying drawings. However, the embodiments of the present invention are not limited to the specific details in the above embodiments. Within the scope of the technical concept of the embodiments of the present invention, various simple modifications can be made to the technical solutions of the embodiments of the present invention, and these simple modifications all fall within the protection scope of the embodiments of the present invention.

[0044] It should also be noted that the various specific technical features described in the above embodiments can be combined in any suitable manner without contradiction. To avoid unnecessary repetition, the embodiments of the present invention will not describe the various possible combinations separately.

[0045] Furthermore, various different implementations of the present invention can be combined arbitrarily, as long as they do not violate the spirit of the present invention, they should also be regarded as the content disclosed in the present invention.

Claims

1. A method for orbital process control of spaceborne equipment with adjustable multi-dimensional parameters, characterized in that, The method includes: Step S1: Receive the test phase of the load. The test phase includes the preliminary research phase, the initial prototype design phase, and the final prototype design phase. Step S2: Determine the test content according to the test stage. The test content includes acceptance test, satellite installation test, integrated electrical test, thermal test and launch site test. Step S3: Obtain test working parameters based on the test content. The test working parameters include a set of test process events, a set of execution times, and a set of imaging modes. Establish a track process test task model based on the test working parameters. Step S4: Based on the orbital process test task model, generate payload orbital process annotation instructions by combining the test process event set, the execution time set, and the imaging mode set according to the satellite annotation instruction format; Step S5: According to the payload orbit process annotation instructions, the main controller schedules and executes the payload Earth observation and calibration tasks according to the satellite orbit period.

2. The method for controlling the orbital process of spaceborne equipment with adjustable multi-dimensional parameters according to claim 1, characterized in that, The track process test task model is a tree structure, including a set of track process test tasks, a set of test process events, a set of execution times, and a set of imaging modes from top to bottom. The track process test task model includes multiple track process test tasks, each track process test task corresponds to a set of test process events, each test process event in the set of test process events corresponds to an execution time to form an execution time set, and the corresponding imaging mode is executed at each execution time to form an imaging mode set.

3. The method for controlling the orbital process of spaceborne equipment with adjustable multi-dimensional parameters according to claim 2, characterized in that, The test process events include dark background test events, standby events, internal lamp pixel detection and calibration test events, and normal observation events. Each test process event corresponds to a specific load observation or calibration task.

4. The method for controlling the orbital process of spaceborne equipment with adjustable multi-dimensional parameters according to claim 3, characterized in that, The execution time is less than or equal to the satellite's orbital period, which is calculated using spacecraft orbital dynamics formulas.

5. The method for controlling the orbital process of spaceborne equipment with adjustable multi-dimensional parameters according to claim 4, characterized in that, The imaging mode is composed of the integration time of the charge-coupled device (CCD) detector, the CCD image pixel merging mode, and the CCD imaging gain coefficient. The integration time, CCD image pixel merging mode, and imaging gain coefficient are predetermined based on the intensity of backscattered solar light from the Earth through ground simulation or on-orbit calibration data.

6. The method for controlling the orbital process of spaceborne equipment with adjustable multi-dimensional parameters according to claim 3, characterized in that, The test process events are configured individually. The individual configuration includes setting the enable state, execution order and associated parameters of each test process event independently. When performing load orbit process testing on the ground, all pre-set test cases are traversed according to the individual configuration to verify the functional correctness of each test process event.

7. The method for controlling the orbital process of spaceborne equipment with adjustable multi-dimensional parameters according to claim 2, characterized in that, The set of orbital process test tasks includes at least standby process tasks, calibration process tasks, Earth observation tasks, and dark background test tasks.

8. The method for controlling the orbital process of spaceborne equipment with adjustable multi-dimensional parameters according to claim 7, characterized in that, The orbital process test task set also includes ground test tasks, which are used to conduct ground tests on all preset orbital process test tasks.

9. The method for controlling the orbital process of spaceborne equipment with adjustable multi-dimensional parameters according to claim 1, characterized in that, Step S2 includes: determining the test content based on the test phase using a load task book, wherein the load task book includes the correspondence between the test phase and the test content.

10. The multi-dimensional parameter adjustable orbital process control method for spaceborne equipment according to claim 7, characterized in that, Step S5 includes: According to the payload orbit process annotation instructions, after receiving the satellite nadir point night command, the orbit process test task is executed. The ground imaging area corresponding to the payload is in darkness, and the payload performs a dark background test task in the ground imaging area. After the dark background test is completed, the calibration process task of internal lamp pixel detection is performed, and the Earth observation task is performed in the illuminated area.

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