Sun observation method based on task guidance combination system

Abstract

The invention discloses a sun-oriented observation method based on a task guidance combination system, and the method comprises the steps: determining a solar elevation angle in the operation process of a satellite, determining a sun-oriented observation task based on the solar elevation angle through the task guidance combination system, and finally adjusting the attitude of the satellite according to a preset guidance law through the task guidance combination system. And the load is controlled according to the load parameters, and corresponding sun observation tasks are carried out, so that the satellite can autonomously execute different sun observation tasks in orbit according to the solar altitude.

Description

Technical Field

[0001] The present invention relates to the field of aerospace technology, and particularly relates to a task guidance joint system and method with multi-system coupling.

[0002] This application is a divisional application based on the parent case "A Task Guidance Joint System and Method with Multi-system Coupling" (Application No.: 2022109844240, Application Date: August 17, 2022). Background Art

[0003] With the development of science and technology, the payloads carried by satellites are increasing, and the functions of satellites are becoming more and more complex. Currently, in the on-orbit mission planning of satellites, most still judge the on-board environment on the ground, then complete the planning according to the current state, and control the satellite to complete the mission by means of command uploading. Using this method for mission planning, the on-board program is simple, but it is difficult to plan some tasks that are sensitive to the on-board environment and need to react in real time according to the satellite state. Summary of the Invention

[0004] In view of some or all of the problems in the prior art, on the one hand, the present invention provides a task guidance joint system with multi-system coupling, including:

[0005] A storage module for storing the payload parameters required during the mission; and

[0006] A task guidance module communicatively connected to each module and payload of the satellite, and configured to receive the task type uploaded from the ground, determine the overall mode and overall sub-mode of the satellite according to the task type, then adjust the satellite attitude according to a preset guidance law, and control the payload according to the payload parameters.

[0007] Further, the guidance law includes at least one turntable guidance law and at least one platform guidance law, wherein the turntable guidance law and the platform guidance law are respectively used to guide the turntable and the platform into corresponding attitudes according to the overall sub-mode.

[0008] Further, the turntable guidance law includes: high-speed maneuvering, low-frequency tracking, low-speed maneuvering, medium-speed maneuvering, positioning, and high-frequency tracking.

[0009] Further, the platform guidance law includes: invalid mode, vertical drift, lateral drift, vertical non-drift, lateral non-drift, tracking, orbit system fixed pointing, and inertial system fixed pointing.

[0010] Further, the overall mode includes stellar observation mission, sun-facing observation mission, space environment mission, fixed pointing, minimum power-on mode, orbit insertion mode, and overall safety mode.

[0011] Further, the stellar observation mission includes the following spacecraft sub - modes: high - orbit stellar observation, low - orbit stellar observation, vertical non - observation, and lateral non - observation; and / or

[0012] The solar observation mission includes the following spacecraft sub - modes: solar eclipse observation, first solar observation, second solar observation, vertical non - observation, and lateral non - observation; and / or

[0013] The space environment mission includes the following spacecraft sub - modes: environment observation, patrol observation, vertical non - observation, and lateral non - observation; and / or

[0014] The fixed - pointing includes the following spacecraft sub - modes: orbital - system fixed - pointing observation, inertial - system fixed - pointing observation, vertical non - observation, and lateral non - observation.

[0015] Further, the minimum power - on mode includes a minimum power - on sub - mode, which is the default power - on mode of the satellite.

[0016] Further, at satellite - rocket separation, the minimum power - on sub - mode automatically switches to the in - orbit sub - mode.

[0017] Based on the aforementioned mission guidance and joint system, another aspect of the present invention provides a mission guidance and joint method for multi - system coupling, including:

[0018] When the satellite enters the territory, receive the mission type uploaded from the ground and store the required payload parameters in the designated area of the storage module;

[0019] The mission guidance module determines whether the current orbit and energy conditions of the satellite meet the mission requirements:

[0020] If not, independently abandon the mission; and

[0021] If so, enter the corresponding spacecraft mode and spacecraft sub - mode:

[0022] According to the external environment of the satellite, issue the corresponding platform guidance law and turntable guidance law to adjust the satellite to enter the corresponding attitude and make attitude preparations for the mission process; and

[0023] When the attitude, orbit, and external environment meet the requirements, turn on the corresponding payload to complete the corresponding mission; and

[0024] After the mission type is executed, the satellite platform and turntable switch to the default attitude and wait for the ground to re - inject the mission type.

[0025] Further, the mission guidance and joint method further includes:

[0026] If the mission requirements cannot be met, abandon the current mission for the next mission process, store the corresponding status, and upload it to the ground during the next entry.

[0027] The present invention provides a multi-system coupled mission guidance joint system and method, which divides common satellite mission types into multiple whole-device modes according to the required payload, mission environment, etc., and further divides them into multiple whole-device sub-modes according to different requirements of the attitude in the mission, and provides corresponding platform attitude control working modes, turntable guidance laws and platform guidance laws for different whole-device sub-modes. During the on-orbit operation of the satellite, the ground only needs to tell the satellite the type of mission that needs to be completed at present, and the mission guidance module will automatically select the corresponding turntable guidance law and platform guidance law according to the external environment to adjust the satellite to enter the corresponding attitude and orbital altitude, and start the corresponding payload. Each module cooperates to complete the on-orbit mission, so as to realize the satellite's autonomous execution of the mission on orbit. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] To further illustrate the above and other advantages and features of various embodiments of the present invention, a more specific description of various embodiments of the present invention will be presented with reference to the accompanying drawings. It will be understood that these drawings only depict typical embodiments of the present invention and are therefore not to be considered as limiting the scope thereof. In the accompanying drawings, for clarity, identical or corresponding parts will be represented by identical or similar reference numerals.

[0029] Figure 1 A schematic diagram showing the structure of a multi-system coupled task guidance joint system according to an embodiment of the present invention;

[0030] Figure 2 A schematic diagram showing data interaction between a mission guidance module and other satellite modules according to an embodiment of the present invention;

[0031] Figure 3 A schematic diagram showing the switching logic of the working sub-modes of the whole device system according to an embodiment of the present invention is shown;

[0032] Figure 4 A schematic diagram showing the relationship between the turntable guidance law, the whole device sub-mode, the platform attitude control working mode, and the platform guidance law according to an embodiment of the present invention;

[0033] Figure 5 A schematic diagram showing a flow chart of a multi-system coupling task-guided joint method according to an embodiment of the present invention; and

[0034] Figure 6 A schematic diagram showing a solar observation mission according to an embodiment of the present invention. DETAILED DESCRIPTION

[0035] In the following description, the present invention is described with reference to various embodiments. However, those skilled in the art will recognize that the embodiments can be implemented without one or more specific details or in conjunction with other alternative and / or additional methods or components. In other instances, well-known structures or operations are not shown or described in detail to avoid obscuring the inventive aspects of the present invention. Similarly, for purposes of explanation, specific numbers and configurations are set forth in order to provide a thorough understanding of the embodiments of the present invention. However, the present invention is not limited to these specific details. In addition, it should be understood that the embodiments shown in the drawings are illustrative representations and are not necessarily drawn to scale.

[0036] In this specification, the reference to "an embodiment" or "the embodiment" means that the specific features, structures, or characteristics described in connection with the embodiment are included in at least one embodiment of the present invention. The phrase "in an embodiment" that appears throughout this specification does not necessarily refer to the same embodiment.

[0037] It should be noted that the embodiments of the present invention describe the method steps in a specific order. However, this is only for the purpose of explaining the specific embodiment and does not limit the order of the steps. On the contrary, in different embodiments of the present invention, the order of the steps can be adjusted according to actual needs.

[0038] In order to enable a satellite to autonomously perform tasks in orbit, the present invention provides a joint task guidance strategy for multi-system coupling, which divides the common task types of the satellite into multiple integrator modes according to the required payloads, task environments, etc., and further divides them into multiple integrator sub-modes according to different requirements for attitudes, etc. in the task, and corresponding platform attitude control working modes, turntable guidance laws, and platform guidance laws are set for different integrator sub-modes, so that during the in-orbit operation of the satellite, the ground only needs to tell the satellite the current task type that needs to be completed, and the task guidance module will automatically select the corresponding turntable guidance law and platform guidance law according to the external environment to adjust the satellite to enter the corresponding attitude and orbital altitude, and turn on the corresponding payload, and each module cooperates to complete the in-orbit task.

[0039] The following further describes the solution of the present invention with reference to the accompanying drawings of the embodiments.

[0040] Figure 1Schematic diagram of the structure of a multi-system coupled task guidance joint system showing an embodiment of the present invention. As shown in the figure, a multi-system coupled task guidance joint system includes a storage module 101 and a task guidance module 102. Among them, the storage module 101 is used to store the payload parameters required during the task, and the task guidance module 102 is communicatively connected to each module and payload of the satellite, and is used to receive the task type uploaded from the ground, and determine the overall satellite mode and the overall satellite sub-mode according to the task type uploaded from the ground, and then adjust the satellite attitude according to the preset guidance law, and control the payload according to the payload parameters.

[0041] Figure 2 Schematic diagram of data interaction between the task guidance module and other modules of the satellite showing an embodiment of the present invention. As Figure 2 shown, after receiving the task type, the task guidance module automatically adjusts the satellite to enter the corresponding attitude and orbital altitude according to the external environment, such as the solar elevation angle, etc., and turns on the corresponding payload, so that each module cooperates to complete the on-orbit task. During the autonomous execution of the task on orbit, the task guidance module will control multiple systems, such as data interaction exists between the uplink and downlink management module, turntable mechanism, attitude control module, data transmission module, orbit control module, orbit module, payload, common area and other interfaces. Specifically, the uplink and downlink management module is used to realize the communication between the satellite and the ground. It sends the data remote control instructions uploaded from the ground to the task guidance module, and sends the telemetry data of the task guidance module to the ground. The orbit module, orbit control module, data transmission module and other interfaces respectively provide orbit data, orbit control request flag, data transmission task flag and various flag quantities on the satellite for the task guidance module. The task guidance module determines the overall satellite mode and sub-mode, platform guidance law and turntable guidance law, and payload instructions according to the received task type, and sends them to the common area, attitude control module, turntable mechanism and payload respectively. After executing the corresponding instructions, the common area, attitude control module, turntable mechanism and payload return information such as the mode of each subsystem, corresponding flags, transformation matrix, solar vector, payload status, etc.

[0042] The overall satellite mode refers to the task type that needs to be executed currently. The task types that need to be executed currently include two major categories: optical payload task mode and optical payload task service mode. In an embodiment of the present invention, according to the required payload and task environment, it is subdivided into the following overall satellite modes: star observation task, sun observation task, space environment task, fixed pointing, minimum power-on mode, orbit entry mode and overall satellite safety mode. Among them, the star observation task, sun observation task and space environment task belong to the optical payload task mode, that is, the task mode, and the minimum power-on mode, orbit entry mode and overall satellite safety mode belong to the optical payload task service mode, that is, the service mode.

[0043] The aligner mode is further classified into aligner sub - modes. Different aligner sub - modes will adopt different attitude control working modes, as well as platform guidance laws and turntable guidance laws, which are important bases for each subsystem and payload on the satellite to perform tasks. In an embodiment of the present invention, the stellar observation task includes the following aligner sub - modes: high - orbit stellar observation, low - orbit stellar observation, vertical non - observation, and lateral non - observation. In an embodiment of the present invention, the solar observation task includes the following aligner sub - modes: solar eclipse observation, first solar observation, second solar observation, vertical non - observation, and lateral non - observation. In an embodiment of the present invention, the space environment task includes the following aligner sub - modes: environment observation, patrol observation, vertical non - observation, and lateral non - observation. In an embodiment of the present invention, the fixed pointing includes the following aligner sub - modes: orbital - system fixed - pointing observation, inertial - system fixed - pointing observation, vertical non - observation, and lateral non - observation. In an embodiment of the present invention, the minimum power - on mode, also known as the launch vehicle test mode, includes the minimum power - on sub - mode, or the launch vehicle test mode, which is the default power - on mode of the satellite platform. In an embodiment of the present invention, the orbit - entry mode includes an orbit - entry sub - mode. At the moment of satellite - rocket separation, that is, when the satellite - rocket separation hardware signal is collected or the "soft satellite - rocket separation" instruction is received, the minimum power - on sub - mode switches to the orbit - entry sub - mode, and at the same time, the aligner mode automatically switches to the orbit - entry mode. In an embodiment of the present invention, the aligner safety mode includes an aligner safety sub - mode.

[0044] Figure 3 Figure 4 shows a schematic diagram of the switching logic of the working sub - modes of the aligner system according to an embodiment of the present invention. As Figure 3As shown, before orbit injection, the satellite is in the power-on default mode, i.e., the minimum plus electronic mode. After the separation of the satellite and the rocket, it enters the orbit injection sub-mode. After a certain period of time, when the satellite establishes an upright attitude towards the ground, the orbit injection sub-mode autonomously enters the upright non-observation regulator sub-mode, and at the same time, the on-board regulator mode autonomously switches to the fixed pointing mode. In addition, the switching of each regulator sub-mode can be controlled according to the mission type uploaded from the ground. In an embodiment of the present invention, the primary prerequisite for each regulator sub-mode to enter is that the current on-board regulator mode is the regulator mode to which the corresponding sub-mode to enter belongs. At the same time, before each regulator sub-mode executes and switches to other regulator sub-modes, it is necessary to determine whether it meets the conditions for entering the regulator safety sub-mode. If it meets the conditions, the regulator mode is the regulator safety mode, and the regulator sub-mode enters the regulator safety sub-mode. After meeting the conditions for switching out of the regulator safety mode, it will then switch out of the corresponding regulator mode according to the ground command and enter the corresponding regulator sub-mode according to the conditions of the ground command or the autonomous switching logic sub-diagram. In the embodiments of the present invention, except for the minimum plus electronic mode, all other regulator sub-modes can switch into the regulator safety sub-mode. Among them, since the orbit injection sub-mode belongs to a specific period, that is, a special regulator sub-mode during the period from the separation of the satellite and the rocket to before the satellite establishes an upright comparison attitude, when it meets the conditions for entering the regulator safety sub-mode, it can switch into the regulator safety sub-mode, but it cannot enter the orbit injection sub-mode from the regulator safety sub-mode. That is to say, after the orbit injection process is completed or ended, the mission guidance module will no longer enter the orbit injection sub-mode. In the embodiments of the present invention, the upright non-observation and the lateral non-observation are sub-modes serving the optical payload observation mission, acting as transition modes during the payload mission intervals. The corresponding parameters can also be modified to the guidance law module through the ground command. When the duration of the payload not observing exceeds the preset value, for example, when it does not observe within 25 minutes, the upright non-offset or upright offset, lateral non-offset or lateral offset is selected. In an embodiment of the present invention, the preset value can be modified through the command. All observation modes are one of the cut-in conditions for the attitude control corresponding observation mode. When the mission guidance module enters the corresponding regulator sub-mode, it first outputs the corresponding platform guidance law. After the attitude control receives the platform guidance law, it enters the preparation stage of the corresponding mission. After the attitude control is ready, it can execute the observation mission.

[0045] In one embodiment of the present invention, the guidance law includes a turntable guidance law and a platform guidance law. Among them, the platform guidance law is output by the mission guidance module 102 and is an algorithm for guiding the platform into a corresponding attitude. According to the platform guidance law output by the mission guidance module 102, the attitude control module enters a corresponding working mode to adjust the attitude of the platform. In one embodiment of the present invention, the platform guidance law mainly includes: invalid mode, erect drift, lateral drift, erect non-drift, lateral non-drift, tracking, orbit system fixed pointing, and inertial system fixed pointing. The turntable guidance law is also output by the mission guidance module 102 and is an algorithm for guiding the turntable into a corresponding attitude. In one embodiment of the present invention, the turntable guidance law mainly includes: high-speed maneuvering, low-frequency tracking, low-speed maneuvering, medium-speed maneuvering, positioning, and high-frequency tracking.

[0046] Figure 4 The schematic diagram showing the relationship between the turntable guidance law, the integrator sub-mode, the platform attitude control working mode, and the platform guidance law in one embodiment of the present invention is as follows. As Figure 4 described, different integrator sub-modes, on the one hand, require one or more turntable guidance laws to cooperate so that the turntable enters a corresponding attitude, and on the other hand, can trigger different platform attitude control working modes, while different platform attitude controls require different platform guidance laws to control the platform to enter a corresponding attitude.

[0047] Based on the mission guidance joint system described above, Figure 5 The schematic diagram showing the process of a mission guidance joint method with multi-system coupling in one embodiment of the present invention is as follows. As Figure 5 shown, a mission guidance joint method with multi-system coupling includes:

[0048] First, in step 501, the mission type is received. When the satellite enters the country, the ground uploads an instruction to inform the satellite of the mission type that needs to be completed, and stores the payload parameters required during the satellite mission in a specified area of the storage module. In one embodiment of the present invention, the uploaded mission type can be one or a series of mission processes;

[0049] Next, in step 502, it is judged whether the orbit and energy conditions meet the mission requirements. After receiving the instruction, the mission guidance module judges whether the orbit, energy, and other conditions of the satellite meet the mission requirements. If they are met, it enters step 503 and enters the integrator mode, that is, enters the corresponding integrator mode and integrator sub-mode according to the mission type. If they are not met, it enters step 504 and autonomously abandons the mission;

[0050] Next, in step 505, the attitude is adjusted. After the mission guidance module enters the corresponding whole device mode and whole device sub-mode, it issues corresponding platform guidance laws and turntable guidance laws according to the external environment of the satellite, such as the solar altitude angle, to adjust the satellite to the corresponding attitude and prepare for the mission process. In one embodiment of the present invention, adjusting the attitude of the satellite includes: such as calculating the solar altitude angle in real time, and ensuring that the payload optical axis forms a certain angle with the solar altitude angle;

[0051] Next, in step 506, the payload is turned on. After the attitude, orbit and external environment meet the mission requirements, the corresponding payload is turned on to complete the corresponding mission. In one embodiment of the present invention, if the attitude, orbit or external environment does not meet the mission requirements, the current mission is abandoned and the next mission process is carried out, the corresponding state is stored, and it is transmitted to the ground at the next entry; and

[0052] Finally, in step 507, the default attitude is switched. After all the mission types stored on the satellite are executed, the satellite platform and the turntable switch to the default attitude and wait for the ground to re-inject the mission type.

[0053] Figure 6 FIG. 1 is a schematic diagram of a solar observation mission according to an embodiment of the present invention. The +X direction is the satellite flight direction, and the display plane is the orbital plane. Figure 6 As shown in the figure, the solar observation mission can be divided into multiple whole-device sub-modes according to the different solar altitude angles. Specifically, when the spacecraft moves out of the shadow, the solar altitude angle gradually increases; when the spacecraft moves into the shadow, the solar altitude angle gradually decreases; at different solar altitude angles, different observation tasks need to be performed. During the satellite's orbital motion, the solar altitude angle changes in real time, and it is difficult to plan tasks on the ground. The mission guidance module is used for autonomous mission planning. The solar altitude angle is used as a variable input, and the mission process can be judged in real time. Different platform guidance laws and turntable guidance laws can be output to adjust the satellite to the corresponding attitude, so as to facilitate the corresponding solar observation mission.

[0054] Although various embodiments of the present invention are described above, it should be understood that they are presented as examples only and not as limitations. It is obvious to those skilled in the relevant art that various combinations, modifications and changes can be made thereto without departing from the spirit and scope of the present invention. Therefore, the breadth and scope of the present invention disclosed herein should not be limited by the exemplary embodiments disclosed above, but should only be defined according to the attached claims and their equivalents.

Claims

1. A solar observation method based on a mission guidance joint system. It is characterized in that Includes steps: During satellite operation, determine the solar altitude angle; Determining a solar observation task based on the solar altitude angle through a task guidance joint system; as well as Through the mission guidance joint system, the satellite attitude is adjusted according to the preset guidance law, and the payload is controlled according to the payload parameters to carry out the corresponding solar observation mission.

2. The solar observation method according to claim 1, It is characterized in that The load parameters are stored in a designated area of ​​the task guidance joint system storage module, and the solar observation method further comprises the steps of: When the satellite enters the country, the payload parameters required for the solar observation mission are stored in the designated area of ​​the storage module by ground injection instructions.

3. The solar observation method according to claim 1, It is characterized in that Also includes the steps: Before carrying out a solar observation mission, determine whether the satellite's current orbit and energy conditions meet the mission requirements: If you are not satisfied, you can abandon the task on your own initiative. as well as If satisfied, the satellite attitude is adjusted according to the preset guidance law, and the payload is controlled according to the payload parameters to perform the corresponding solar observation mission.

4. The solar observation method according to claim 1, It is characterized in that The preset guidance law includes a platform guidance law and a turntable guidance law.

5. The solar observation method according to claim 4, It is characterized in that The turntable guidance laws include: high-speed maneuvering, low-frequency tracking, low-speed maneuvering, medium-speed maneuvering, positioning and high-frequency tracking.

6. The solar observation method according to claim 4, It is characterized in that The platform guidance laws include: invalid mode, upright bias flow, lateral bias flow, upright non-bias flow, lateral non-bias flow, tracking, orbital fixed orientation and inertial fixed orientation.

7. The solar observation method according to claim 1, It is characterized in that The solar observation tasks include: solar occultation observation tasks, first solar observation tasks, second solar observation tasks, upright non-observation tasks and side-lying non-observation tasks.

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