A method and device for sun orientation planning of a remote sensing satellite

Abstract

The application discloses a kind of remote sensing satellite sun orientation planning method and device, the method includes: S1, obtaining the information set of earth observation task;S2, the information set of earth observation task is handled, and satellite can obtain the information set of earth observation task;S3, the earth observation action sequence in the satellite can obtain the information set of earth observation task is spliced, and satellite observation action sequence is obtained;S4, action insertion processing is carried out to the satellite observation action sequence, and satellite execution action sequence is obtained.The application realizes dynamic development sun orientation while carrying out the task such as earth observation, reaches the requirement of energy balance.

Description

Technical Field

[0001] This invention belongs to the field of remote sensing satellite mission planning technology, specifically a method and device for sun orientation planning of remote sensing satellites. Background Technology

[0002] When remote sensing satellites conduct autonomous Earth observation missions, they need to meet constraints such as energy, storage, and lateral tilting. Energy balance, in particular, affects the overall safety of the satellite, ground telemetry and control, and the effectiveness of satellite observations. The satellite design must ensure that it remains sun-oriented when not conducting Earth observations, powered by solar arrays. Remote sensing satellites must simultaneously meet the requirements of autonomous Earth observation, Earth data transmission, and attitude maneuvering for sun-oriented missions.

[0003] Current remote sensing satellites achieve sun orientation through timed settings, a strategy that lacks flexibility and fails to fully utilize the satellite's capabilities and benefits. This timed setting method does not take full advantage of idle periods without observation needs, potentially resulting in short sun orientation times and severely impacting the overall safety of the remote sensing satellite. Summary of the Invention

[0004] The technical problem to be solved by the present invention is to provide a method and device for planning the orientation of a remote sensing satellite toward the sun, which can dynamically conduct orientation toward the sun while carrying out tasks such as Earth observation, so as to achieve energy balance requirements.

[0005] To address the aforementioned technical problems, a first aspect of the present invention discloses a method for planning the sun orientation of a remote sensing satellite, the method comprising: S1, acquire the Earth observation mission information set; the Earth observation mission information set includes information on several Earth observation missions; the Earth observation mission information includes Earth observation action sequences, mission levels, and satellite operating energy parameter sets; The Earth observation action sequence includes several Earth observation actions; The satellite's operating energy parameter set includes the mission start time, mission end time, solar array output power, sunshine duration, charging efficiency, payload peak power consumption, payload power-on duration, single attitude maneuver power consumption, number of maneuvers, actual solar cell temperature, long-term platform power consumption, shadow duration, and discharge efficiency. S2, process the Earth observation mission information set to obtain a satellite Earth observation mission information set; the satellite Earth observation mission information set includes N Information on the Earth observation missions described above; N It is an integer greater than 1; S3, splice the Earth observation action sequence in the satellite Earth observation mission information set to obtain the satellite observation action sequence; It should be noted that the above-mentioned satellite observation action sequence includes several Earth observation actions; the basis for splicing the Earth observation action sequence is to splice them together in the order of the start times of the corresponding tasks.

[0006] S4, perform action insertion processing on the satellite observation action sequence to obtain the satellite execution action sequence.

[0007] In a first aspect of the present invention, processing the Earth observation mission information set to obtain a satellite Earth observation mission information set includes: S21, The Earth observation mission information set is processed to obtain an energy value set; the energy value set includes the energy value corresponding to each Earth observation mission information in the Earth observation mission information set. S22, determine whether each energy value is less than a preset first threshold, and obtain the corresponding first judgment result; When the first judgment result is yes, a second judgment result is obtained by judging whether the mission level of the Earth observation mission information corresponding to the energy value is urgent. When the second judgment result is negative, the Earth observation mission information corresponding to the energy value is deleted from the Earth observation mission information set; S24 is executed; If the second judgment result is yes, execute S23; S23, determine whether each energy value is less than a preset second threshold, and obtain the corresponding third judgment result; When the third judgment result is yes, the Earth observation mission information corresponding to the energy value is deleted from the Earth observation mission information set; When the third judgment result is negative, the Earth observation mission information set remains unchanged; S24, the Earth observation mission information set is determined as the satellite Earth observation mission information set.

[0008] In a first aspect of the present invention, processing the Earth observation mission information set to obtain an energy value set includes: S211, using a charging quantity calculation model, the Earth observation mission information set is processed to obtain a charging quantity value set; the charging quantity value set includes... N Individual charging value; S212, using a discharge quantity calculation model, the Earth observation mission information set is processed to obtain a discharge quantity value set; the discharge quantity value set includes... N One discharge quantity value; S213, using the energy value calculation model, process the charging value set and the discharging value set to obtain the energy value.

[0009] In a first aspect of the present invention, the expression for the charging amount calculation model is: In the formula, For the first of the set of charging values i The charging amount value mentioned above; 1≤ i ≤ N， and i It is an integer; 、 、 , 、 、 and These are respectively the first of the Earth observation mission information sets. i The satellite's operating energy parameters include the solar array output power, illumination duration, charging efficiency, payload peak power consumption, payload power-on duration, single attitude maneuver power consumption, and number of maneuvers.

[0010] In a first aspect of the present invention, the expression for the discharge quantity calculation model is as follows: In the formula, The first of the set of discharge values i The discharge quantity value; 、 、 、 and These are respectively the first of the Earth observation mission information sets. i The temperature influence factor of the satellite's operating energy parameter set, the actual temperature of the solar cell, the long-term power consumption of the platform, the duration of the shadow period, and the discharge efficiency; The preset temperature compensation coefficient, This is the preset reference standard temperature.

[0011] In a first aspect of the present invention, the energy value calculation model expression is: In the formula, For the energy value set, the firstv The energy value stated; For the preset first u Individual power loss rate; 2≤ v ≤ N， and v It is an integer; This is the preset initial charge of the solar array; For the first u The time interval between the end time of the first task and the start time of the (u+1)th task.

[0012] In a first aspect of the present invention, the step of performing action insertion processing on the satellite observation action sequence to obtain a satellite execution action sequence includes: S41, traverse the time intervals between adjacent Earth observation actions in the satellite observation action sequence to obtain a time interval sequence; S42, the loop variable k Initialize to 1; S43, for the first time interval sequence k The fourth judgment result is obtained by judging whether the time interval is greater than a preset third threshold. When the fourth judgment result is yes, the preset sun-oriented action is inserted into the first step of the satellite observation action sequence. k Between the first Earth observation action and the (k+1)th Earth observation action; When the fourth judgment result is negative, the satellite observation action sequence remains unchanged; S44, k Increment the value by 1; S45, repeat S43~S44 until... k Greater than the number of Earth observation actions in the satellite observation action sequence; S46, the satellite observation action sequence is determined as the satellite execution action sequence.

[0013] A second aspect of this invention discloses a remote sensing satellite sun orientation planning device, the device comprising: The Earth observation mission information set acquisition module is used to acquire the Earth observation mission information set; The Earth observation mission information set generation module is used to process the Earth observation mission information set to obtain the satellite Earth observation mission information set; The observation action sequence generation module is used to splice the Earth observation action sequences in the satellite Earth observation mission information set to obtain the satellite observation action sequence; An action sequence generation module is used to perform action insertion processing on the satellite observation action sequence to obtain a satellite execution action sequence.

[0014] A third aspect of this invention discloses another remote sensing satellite sun orientation planning device, the device comprising: Memory containing executable program code; A processor coupled to the memory; The processor calls the executable program code stored in the memory to execute some or all of the steps in the remote sensing satellite sun orientation planning method disclosed in the first aspect of the present invention.

[0015] The fourth aspect of the present invention discloses a computer-readable storage medium storing computer instructions, which, when invoked, are used to execute some or all of the steps in the remote sensing satellite sun orientation planning method disclosed in the first aspect of the present invention.

[0016] Compared with the prior art, the embodiments of the present invention have the following beneficial effects: This invention initiates solar orientation when the idle period without observation demand exceeds a first threshold; prioritizes solar orientation when the satellite's battery power falls below a second threshold before the start of the observation mission preparation; and abandons the observation mission when the satellite's battery power falls below a third threshold. Through these methods, the satellite maintains solar orientation as much as possible when not conducting Earth observations, and is powered by a solar array, achieving dynamic solar orientation while performing Earth observations and other missions, thus meeting the requirements of energy balance. Attached Figure Description

[0017] To more clearly illustrate the technical solutions in the embodiments of the present invention, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the accompanying drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0018] Figure 1 This is a flowchart illustrating a method for sun orientation planning of a remote sensing satellite disclosed in an embodiment of the present invention.

[0019] Figure 2 This is a schematic diagram of the structure of a remote sensing satellite sun orientation planning device disclosed in an embodiment of the present invention.

[0020] Figure 3 This is a schematic diagram of another remote sensing satellite sun orientation planning device disclosed in an embodiment of the present invention. Detailed Implementation

[0021] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0022] In the description of this invention, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing the invention and for simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on the invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0023] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0024] In all embodiments of the present invention, the variables involved in all computational expressions or mathematical functions are dimensionless before calculation. The values ​​of the independent variables in all computational expressions or mathematical functions in these embodiments conform to the reasonable requirements of the input range of the computational expression or mathematical function, ensuring that the computational expression or mathematical function can be calculated smoothly without violating physical laws or mathematical rules.

[0025] Example 1 Please see Figure 1 . Figure 1 This is a flowchart illustrating a method for sun-alignment planning of a remote sensing satellite, as disclosed in an embodiment of the present invention. Figure 1 The described method for sun orientation planning of remote sensing satellites is applied in the field of sun orientation planning for remote sensing satellites, and the embodiments of this invention are not limited thereto. Figure 1 As shown, the method includes: S1, accept Earth observation missions and obtain Earth observation mission information set; the Earth observation mission information set includes information on several Earth observation missions; the Earth observation mission information includes Earth observation action sequence, mission level and satellite operating energy parameter set; The Earth observation action sequence includes several Earth observation actions; It should be noted that Earth observation actions may include sensor start-up and shutdown, attitude adjustment, data acquisition, etc. For example, an Earth observation task can be decomposed into a series of action units such as: lateral maneuvering → multispectral scanning → data compression → storage, etc. The embodiments of the present invention are not limited to this.

[0026] The task level is either urgent or non-urgent; The satellite's operating energy parameter set includes the mission start time, mission end time, solar array output power, sunshine duration, charging efficiency, payload peak power consumption, payload power-on duration, single attitude maneuver power consumption, number of maneuvers, actual solar cell temperature, long-term platform power consumption, shadow duration, and discharge efficiency. S2, process the Earth observation mission information set to obtain a satellite Earth observation mission information set; the satellite Earth observation mission information set includes N Information on the Earth observation missions described above; N It is an integer greater than 1; S3, splice the Earth observation action sequence in the satellite Earth observation mission information set to obtain the satellite observation action sequence; S4, perform action insertion processing on the satellite observation action sequence to obtain the satellite execution action sequence.

[0027] In an optional embodiment, the above-described processing of the Earth observation mission information set to obtain a satellite Earth observation mission information set includes: S21, The Earth observation mission information set is processed to obtain an energy value set; the energy value set includes the energy value corresponding to each Earth observation mission information in the Earth observation mission information set. S22, determine whether each energy value is less than a preset first threshold, and obtain the corresponding first judgment result; When the first judgment result is yes, a second judgment result is obtained by judging whether the mission level of the Earth observation mission information corresponding to the energy value is urgent. When the second judgment result is negative, the Earth observation mission information corresponding to the energy value is deleted from the Earth observation mission information set; S24 is executed; If the second judgment result is yes, execute S23; S23, determine whether each energy value is less than a preset second threshold, and obtain the corresponding third judgment result; When the third judgment result is yes, the Earth observation mission information corresponding to the energy value is deleted from the Earth observation mission information set; When the third judgment result is negative, the Earth observation mission information set remains unchanged; S24, the Earth observation mission information set is determined as the satellite Earth observation mission information set.

[0028] It should be noted that the above energy values ​​are the percentage of the satellite's remaining battery power relative to its initial power.

[0029] Preferably, the first threshold is 50%.

[0030] Preferably, the second threshold is 30%.

[0031] In another optional embodiment, the above-described processing of the Earth observation mission information set to obtain an energy value set includes: S211, using a charging quantity calculation model, the Earth observation mission information set is processed to obtain a charging quantity value set; the charging quantity value set includes... N Individual charging value; S212, using a discharge quantity calculation model, the Earth observation mission information set is processed to obtain a discharge quantity value set; the discharge quantity value set includes... N One discharge quantity value; S213, using the energy value calculation model, process the charging value set and the discharging value set to obtain the energy value.

[0032] It should be noted that the above energy values ​​represent the percentage of the satellite's battery remaining power relative to its initial power.

[0033] In yet another optional embodiment, the above-mentioned charging amount calculation model expression is: In the formula, For the first of the set of charging values i The charging amount value mentioned above; 1≤ i ≤ N， and i It is an integer; 、 、 , 、 、 and These are respectively the first of the Earth observation mission information sets. i The satellite's operating energy parameters include the solar array output power, illumination duration, charging efficiency, payload peak power consumption, payload power-on duration, single attitude maneuver power consumption, and number of maneuvers.

[0034] In yet another optional embodiment, the expression for the above discharge quantity calculation model is: In the formula, The first of the set of discharge values i The discharge quantity value; 、 、 、 and These are respectively the first of the Earth observation mission information sets. i The temperature influence factor of the satellite's operating energy parameter set, the actual temperature of the solar cell, the long-term power consumption of the platform, the duration of the shadow period, and the discharge efficiency; The preset temperature compensation coefficient, This is the preset reference standard temperature.

[0035] In yet another optional embodiment, the above energy value calculation model expression is: In the formula, For the energy value set, the first v The energy value stated; For the preset first u Individual power loss rate; 2≤ v ≤ N， and v It is an integer; This is the preset initial charge of the solar array; For the first u The time interval between the end time of the first task and the start time of the (u+1)th task.

[0036] In another optional embodiment, the above-described action insertion processing of the satellite observation action sequence to obtain the satellite execution action sequence includes: S41, traverse the time intervals between adjacent Earth observation actions in the satellite observation action sequence to obtain a time interval sequence; S42, the loop variable kInitialize to 1; S43, for the first time interval sequence k The fourth judgment result is obtained by judging whether the time interval is greater than a preset third threshold. When the fourth judgment result is yes, the preset sun-oriented action is inserted into the first step of the satellite observation action sequence. k Between the first Earth observation action and the (k+1)th Earth observation action; When the fourth judgment result is negative, the satellite observation action sequence remains unchanged; S44, k Increment the value by 1; S45, repeat S43~S44 until... k Greater than the number of Earth observation actions in the satellite observation action sequence; S46, the satellite observation action sequence is determined as the satellite execution action sequence.

[0037] It should be noted that the value of the third threshold mentioned above must be greater than the sum of the time of the diversion-to-day orientation maneuver and the diversion-to-ground maneuver.

[0038] Preferably, the third threshold is 10 minutes.

[0039] As can be seen, by implementing the remote sensing satellite sun-orientation planning method described in the embodiments of the present invention, the satellite can maintain sun orientation as much as possible when not conducting Earth observations. By powering the satellite with solar cell arrays, the satellite can dynamically conduct sun orientation while carrying out Earth observations and other tasks, thus achieving the requirement of energy balance.

[0040] Example 2 Please see Figure 2 , Figure 2 This is a schematic diagram of the structure of a remote sensing satellite sun-orientation planning device disclosed in an embodiment of the present invention. Wherein, Figure 2 The described remote sensing satellite sun orientation planning device can be applied to the field of remote sensing satellite sun orientation planning, and the embodiments of the present invention are not limited thereto. Figure 2 As shown, the device may include an Earth observation mission information set acquisition module 201, an Earth observation mission information set generation module 202, an observation action sequence generation module 203, and an execution action sequence generation module 204. Earth observation mission information set acquisition module 201 is used to acquire Earth observation mission information set; The Earth observation mission information set generation module 202 is used to process the Earth observation mission information set to obtain the satellite Earth observation mission information set; The observation action sequence generation module 203 is used to splice the Earth observation action sequence in the satellite Earth observation mission information set to obtain the satellite observation action sequence. The action sequence generation module 204 is used to perform action insertion processing on the satellite observation action sequence to obtain the satellite execution action sequence.

[0041] As can be seen, by implementing the remote sensing satellite sun-orientation planning device described in the embodiments of the present invention, the satellite can maintain sun orientation as much as possible when not conducting Earth observations. By powering the satellite with a solar cell array, the satellite can dynamically conduct sun orientation while carrying out Earth observations and other tasks, thus achieving the requirement of energy balance.

[0042] Example 3 Please see Figure 3 , Figure 3 This is a schematic diagram of another remote sensing satellite sun-orientation planning device disclosed in an embodiment of the present invention. Wherein, Figure 3 The described remote sensing satellite sun orientation planning device can be applied to the field of remote sensing satellite sun orientation planning, and the embodiments of the present invention are not limited thereto. Figure 3 As shown, the remote sensing satellite sun orientation planning device may include the following parts: Memory 301 storing executable program code; Processor 302 coupled to memory 301; The processor 302 calls the executable program code stored in the memory 301 to execute the steps in the remote sensing satellite sun orientation planning method described in Embodiment 1.

[0043] Example 4 This invention discloses a computer-readable storage medium storing a computer program for electronic data interchange, wherein the computer program causes a computer to perform the steps in the remote sensing satellite sun orientation planning method described in Embodiment 1.

[0044] The device embodiments described above are merely illustrative. The modules described as separate components may or may not be physically separate, and the components shown as modules may or may not be physical modules; that is, they may be located in one place or distributed across multiple network modules. Some or all of the modules can be selected to achieve the purpose of this embodiment according to actual needs. Those skilled in the art can understand and implement this without any creative effort.

[0045] Through the detailed description of the above embodiments, those skilled in the art can clearly understand that each implementation method can be implemented by means of software plus necessary general-purpose hardware platforms, and of course, it can also be implemented by hardware. Based on this understanding, the above technical solutions, in essence or the part that contributes to the prior art, can be embodied in the form of a software product. This computer software product can be stored in a computer-readable storage medium, including read-only memory (ROM), random access memory (RAM), programmable read-only memory (PROM), erasable programmable read-only memory (EPROM), one-time programmable read-only memory (OTPROM), electrically-Erasable Programmable Read-Only Memory (EEPROM), compact disc read-only memory (CD-ROM) or other optical disc storage, disk storage, magnetic tape storage, or any other computer-readable medium that can be used to carry or store data.

[0046] Finally, it should be noted that the remote sensing satellite sun orientation planning method and apparatus disclosed in the embodiments of the present invention are merely preferred embodiments of the present invention, and are only used to illustrate the technical solutions of the present invention, not to limit it; although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features; and these modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A method for planning the orientation of a remote sensing satellite towards the sun, characterized in that, The method includes: S1, acquire the Earth observation mission information set; the Earth observation mission information set includes information on several Earth observation missions; the Earth observation mission information includes Earth observation action sequences, mission levels, and satellite operating energy parameter sets; The Earth observation action sequence includes several Earth observation actions; The satellite's operating energy parameter set includes the mission start time, mission end time, solar array output power, sunshine duration, charging efficiency, payload peak power consumption, payload power-on duration, single attitude maneuver power consumption, number of maneuvers, actual solar cell temperature, long-term platform power consumption, shadow duration, and discharge efficiency. S2, process the Earth observation mission information set to obtain a satellite Earth observation mission information set; the satellite Earth observation mission information set includes N Information on the Earth observation missions described above; N It is an integer greater than 1; S3, splice the Earth observation action sequence in the satellite Earth observation mission information set to obtain the satellite observation action sequence; S4, perform action insertion processing on the satellite observation action sequence to obtain the satellite execution action sequence.

2. The method for sun-oriented remote sensing satellite planning according to claim 1, characterized in that, The process of processing the Earth observation mission information set to obtain a satellite Earth observation mission information set includes: S21, The Earth observation mission information set is processed to obtain an energy value set; the energy value set includes the energy value corresponding to each Earth observation mission information in the Earth observation mission information set. S22, determine whether each energy value is less than a preset first threshold, and obtain the corresponding first judgment result; When the first judgment result is yes, a second judgment result is obtained by judging whether the mission level of the Earth observation mission information corresponding to the energy value is urgent. When the second judgment result is negative, the Earth observation mission information corresponding to the energy value is deleted from the Earth observation mission information set; S24 is executed; If the second judgment result is yes, execute S23; S23, determine whether each energy value is less than a preset second threshold, and obtain the corresponding third judgment result; When the third judgment result is yes, the Earth observation mission information corresponding to the energy value is deleted from the Earth observation mission information set; When the third judgment result is negative, the Earth observation mission information set remains unchanged; S24, the Earth observation mission information set is determined as the satellite Earth observation mission information set.

3. The remote sensing satellite sun orientation planning method according to claim 2, characterized in that, The process of processing the Earth observation mission information set to obtain an energy value set includes: S211, using a charging quantity calculation model, the Earth observation mission information set is processed to obtain a charging quantity value set; the charging quantity value set includes... N Each charging value; S212, using a discharge quantity calculation model, the Earth observation mission information set is processed to obtain a discharge quantity value set; the discharge quantity value set includes... N One discharge quantity value; S213, using the energy value calculation model, process the charging value set and the discharging value set to obtain the energy value.

4. The method for sun-oriented remote sensing satellite planning according to claim 3, characterized in that, The expression for the charging amount calculation model is as follows: In the formula, For the first of the set of charging values i The stated charging amount value; 1≤ i ≤ N， and i It is an integer; 、 、 , 、 、 and These are respectively the first of the Earth observation mission information sets. i The satellite's operating energy parameters include the solar array output power, illumination duration, charging efficiency, payload peak power consumption, payload power-on duration, single attitude maneuver power consumption, and number of maneuvers.

5. The remote sensing satellite sun-orientation planning method according to claim 4, characterized in that, The expression for the discharge quantity calculation model is as follows: In the formula, The first of the set of discharge values i The discharge quantity value; 、 、 、 and These are respectively the first of the Earth observation mission information sets. i The temperature influence factor of the satellite's operating energy parameter set, the actual temperature of the solar cell, the long-term power consumption of the platform, the duration of the shadow period, and the discharge efficiency; The preset temperature compensation coefficient, This is the preset reference standard temperature.

6. The method for planning the orientation of a remote sensing satellite towards the sun according to claim 5, characterized in that, The energy value calculation model expression is as follows: In the formula, For the energy value set, the first v The energy value stated; For the preset first u Individual power loss rate; 2≤ v ≤ N， and v It is an integer; This is the preset initial charge of the solar array; For the first u The time interval between the end time of the first task and the start time of the (u+1)th task.

7. The method for sun-oriented planning of remote sensing satellites according to claim 1, characterized in that, The step of performing action insertion processing on the satellite observation action sequence to obtain the satellite execution action sequence includes: S41, traverse the time intervals between adjacent Earth observation actions in the satellite observation action sequence to obtain a time interval sequence; S42, the loop variable k Initialize to 1; S43, for the first time interval sequence k The fourth judgment result is obtained by judging whether the time interval is greater than a preset third threshold. When the fourth judgment result is yes, the preset sun-oriented action is inserted into the first step of the satellite observation action sequence. k Between the first Earth observation action and the (k+1)th Earth observation action; When the fourth judgment result is negative, the satellite observation action sequence remains unchanged; S44, k Increment the value by 1; S45, repeat S43~S44 until... k Greater than the number of Earth observation actions in the satellite observation action sequence; S46, the satellite observation action sequence is determined as the satellite execution action sequence.

8. A remote sensing satellite sun-orientation planning device, characterized in that, The device includes: The Earth observation mission information set acquisition module is used to acquire the Earth observation mission information set; The Earth observation mission information set generation module is used to process the Earth observation mission information set to obtain the satellite Earth observation mission information set; The observation action sequence generation module is used to splice the Earth observation action sequences in the satellite Earth observation mission information set to obtain the satellite observation action sequence; An action sequence generation module is used to perform action insertion processing on the satellite observation action sequence to obtain a satellite execution action sequence.

9. A remote sensing satellite sun orientation planning device, characterized in that, The device includes: Memory containing executable program code; A processor coupled to the memory; The processor calls the executable program code stored in the memory to execute the remote sensing satellite sun orientation planning method as described in any one of claims 1 to 7.

10. A computer-readable storage medium, characterized in that, The computer-readable storage medium stores computer instructions, which, when invoked, are used to execute the remote sensing satellite sun orientation planning method as described in any one of claims 1 to 7.

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