Planning and executing method of satellite observation plan

Abstract

The invention belongs to the technical field of photoelectric telescope control, and particularly relates to a satellite observation plan planning and executing method. The method comprises the following steps: S1, acquiring a two-row orbit element set, and setting an observation time range of an all-day telescope; s2, generating a satellite observation plan sequence according to the two rows of orbital element sets and the observation time range; and S3, according to the satellite observation plan sequence, controlling the all-time telescope satellite observation system to observe the satellite until the observation plan is completed. The satellite observation plan can be automatically planned, and the observation frequencies of different satellites are more uniform by adjusting the observation weights of the satellites.

Description

Technical Field

[0001] The invention belongs to the technical field of photoelectric telescope control, and in particular relates to a method for planning and executing a satellite observation plan. Background Art

[0002] In recent years, traditional photoelectric telescopes used for nighttime observations mainly use visible light cameras with a large field of view. When observing at night when the atmospheric transmittance is good, in addition to satellites, there will be many stars used for astronomical positioning in the image. Unlike traditional photoelectric telescopes, all-day telescopes use short-wave infrared detectors and have a very small field of view, usually about 10' diagonally. When observing satellites, not only is the signal-to-noise ratio low, but there will not be enough stars in the field of view for astronomical positioning. Therefore, after observing a satellite, the all-day telescope needs to sweep and swing to observe the stars around the satellite trajectory and calculate the precise direction of the satellite through a certain algorithm.

[0003] When using an all-day telescope to observe satellites, the operator usually executes the observation plan manually. The operator performs orbit calculation based on the two-row orbit element set of the satellite to be observed, and manually selects a satellite to be observed in a certain time period. After observing the satellite, the operator manually selects the stars around it that can be used for auxiliary positioning for observation, and then calculates the precise direction of the satellite. The operator's manual execution of the observation plan has the following disadvantages: 1) The equipment operation method is relatively complicated and errors are prone to occur during the operation process; 2) After each satellite observation, the star must be manually selected, and the operator needs to continue to operate the equipment to complete all target observations. 3) When there are many satellite targets to be observed, it is difficult for the operator to plan the satellite observation sequence, and some targets may be observed too frequently, and some targets may have no observation records for a long time. 4) The quality of the observation results depends on the experience of the operator, and the operator is not easily replaceable.

[0004] In the night observation telescope scheme based on a large field of view of visible light, the operator inputs the observation plan sequence (not the two-row orbital element set) into the telescope control software, and the telescope tracks according to the given observation plan sequence. However, actual satellite observation work not only has an observation plan sequence, but also a two-row orbital element set. If the observation plan cannot be planned for the two-row orbital element set, the execution of the observation work has great limitations. In addition, when an all-day telescope observes medium and high-orbit satellite targets, it is necessary to plan a neighboring star observation plan for auxiliary positioning. This scheme is not suitable for all-day telescopes. Summary of the invention

[0005] In view of this, the invention aims to provide a method for planning and executing a satellite observation plan to solve the above problems. The invention inputs two sets of orbital elements into the all-day telescope satellite observation system. The system will solve the observation trajectory of each satellite to be observed and list these observation trajectories in the entire observation plan. After the observation of each medium- and high-orbit satellite is completed, a star observation plan for auxiliary positioning is added. Finally, the all-day telescope satellite observation system automatically executes all observation plans.

[0006] To achieve the above object, the technical solution created by the present invention is implemented as follows: A method for planning and executing a satellite observation plan, comprising the following steps: S1: Get two sets of orbital elements and set the observation time range of the all-sky telescope; S2: Generate satellite observation plan sequence based on two sets of orbital elements and observation time range; S3: According to the satellite observation plan sequence, control the all-day telescope satellite observation system to observe the satellite until the observation plan is completed.

[0007] Furthermore, step S2 specifically includes the following steps: S21: Let the observation time range of the all-sky telescope be T, and within the observation time range T, let the set of all arc segments that meet the observation requirements selected from the two-row orbit element number set be S; S22: Set the starting time within the observation time range T to t i , at this time, i=0; S23: At t i At time , set the arc set that meets the observation requirements as O, arc set O∈S, and determine whether the arc set O is non-empty. If so, execute step S24, otherwise execute step S25; S24: selecting an observation arc according to the satellite arc strategy, adding the observation arc to the satellite observation plan sequence, and arranging the observation arcs included in the satellite observation plan sequence in the order of addition; S25: Set i=i+1, update time t i , i=1, 2, 3, ..., and judge the current time t i Is it less than the end time of the observation time range T? If so, use the current time t i Replace the time t in step S23 i , execute step S23, otherwise obtain the final satellite observation plan sequence. Further, in step S21 and step S23, the observation requirement means that the elevation angle of the satellite to be measured relative to the ground is greater than 20°, and the observation arc of the satellite to be measured is greater than 2 minutes.

[0008] Furthermore, in step S25, the specific steps of obtaining the updated time include: When the arc set O is empty, then t i =t i +1min; When the arc set O is not empty, if the observation arc selected according to the satellite arc strategy is a low-orbit satellite arc, t i The value is assigned to the end time of the observation arc + 1min; If the observation arc segment selected according to the satellite arc segment strategy is a medium-high orbit satellite arc segment, t i Reassign the value to the end time of the observation arc + 3 minutes.

[0009] Furthermore, the satellite arc segment strategy is as follows: Obtain an arc set O, and select an arc set R of a satellite with the largest weight from the arc set O; Select the low-orbit satellite arc set R from the arc set R L ; If the low-orbit satellite arc segment set R L If the arc set R is empty, arc N is randomly selected from the arc set R, and part of arc N is intercepted as the observation arc. L Contains an arc segment, then the low-orbit satellite arc segment set R L The included arcs are taken as observation arcs; if the low-orbit satellite arc set R L If the number of included arcs is greater than 1, then in the observation arc set R L Randomly select an arc segment as the observation arc segment; The satellite weight corresponding to the currently selected observation arc is reduced, and the satellite weights corresponding to other arcs in the arc set O are increased, and the satellite weight corresponding to the observation arc has the lowest weight among the satellites corresponding to the arc set O.

[0010] Furthermore, before generating the satellite observation plan sequence, the weights of all satellites corresponding to the two rows of orbital element sets are initialized.

[0011] Furthermore, in step S3, the all-day telescope satellite observation system includes a timing module, a main control module, an image module and a telescope. The timing module sends a trigger frequency and UTC time to the main control module, the main control module sends a guidance instruction to the telescope, and the main control module also sends an observation instruction to the image module. The image module receives the observation instruction and sends a camera control instruction to the telescope. The telescope rotates under the guidance of the main control module and sends the satellite observation image to the image module for real-time processing.

[0012] Furthermore, step S3 specifically includes the following steps: S31: The timing module provides the trigger frequency and UTC time to the main control module; S32: Input the satellite observation plan sequence into the main control module. The main control module checks the satellite observation plan sequence at the initial time t based on the trigger frequency and UTC time. i The type of observation plan it belongs to. At this time, i=0, and the observation plan types include idle, medium- and high-orbit satellite observation plan, and low-orbit satellite observation plan; S33: If the observation plan type is idle, the all-day telescope satellite observation system is in a non-observation state, otherwise it is determined whether the observation plan type is a medium-orbit satellite observation plan, if so, step S34 is executed; otherwise, step S35 is executed, and the observation plan type is a low-orbit satellite observation plan; S34: The all-day telescope satellite observation system selects neighboring stars of the current observation satellite for auxiliary positioning, observes the arc segment to be measured, obtains positioning data of the satellite to be measured, and executes step S36; S35: The all-day telescope satellite observation system observes the arc segment to be measured, obtains the positioning data of the satellite to be measured, and executes step S36; S36: Set i=i+1, update time t i , i=1, 2, 3, ..., using the current time t i Replace the time t in step S32 i , repeat steps S32-S35 until the satellite observation plan is completed. Compared with the prior art, the invention can achieve the following beneficial effects: (1) The satellite observation plan planning and execution method created by the present invention can automatically plan the satellite observation plan and make the observation frequency of different satellites more uniform by adjusting the observation weights of the satellites.

[0013] (2) The satellite observation plan planning and execution method created by the present invention does not require operators to participate in the observation work execution. The operation during observation is simple, does not rely on experienced operators, and is not prone to operational errors. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] The drawings constituting part of the present invention are used to provide a further understanding of the present invention. The exemplary embodiments and descriptions of the present invention are used to explain the present invention and do not constitute an improper limitation on the present invention. In the drawings: Figure 1 A schematic diagram of a process flow of a satellite observation plan planning and execution method according to an embodiment of the present invention; Figure 2 A schematic diagram of a process for generating a satellite observation plan sequence according to an embodiment of the present invention; Figure 3A schematic diagram of the flow chart of the satellite arc segment strategy described in the embodiment of the present invention; Figure 4 A schematic diagram of the structure of the all-day telescope satellite observation system according to an embodiment of the present invention; Figure 5 The present invention is a flowchart of controlling the all-day telescope satellite observation system to observe satellites according to an embodiment of the present invention.

[0015] Description of reference numerals: 1. Timing module; 2. Main control module; 3. Image module; 4. Telescope; 11. Time trigger submodule; 21. Task execution submodule; 22. Guidance submodule; 23. Image instruction sending submodule; 31. Image instruction receiving submodule; 32. Image processing submodule; 41. Telescope control submodule; 42. Image acquisition submodule. DETAILED DESCRIPTION

[0016] In order to make the purpose, technical solution and advantages of the invention more clear, the invention is further described in detail below in conjunction with the accompanying drawings and specific embodiments. It should be understood that the specific embodiments described here are only used to explain the invention and do not constitute a limitation of the invention.

[0017] It should be noted that, in the absence of conflict, the embodiments of the present invention and the features in the embodiments may be combined with each other.

[0018] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside" and the like indicate positions or positional relationships based on the positions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention. In addition, the terms "first", "second", etc. are only used for descriptive purposes, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, features defined as "first", "second", etc. may explicitly or implicitly include one or more of the features. In the description of the present invention, unless otherwise specified, "multiple" means two or more.

[0019] In the description of the invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installation", "connection" and "connection" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the invention can be understood according to specific circumstances.

[0020] The present invention will be described in detail below with reference to the accompanying drawings and in combination with embodiments.

[0021] like Figure 1 As shown, the planning and execution method of the satellite observation plan provided by the present invention specifically includes the following steps: S1: obtaining a two-row orbital element number set and setting the observation time range of the all-day telescope; S2: generating a satellite observation plan sequence according to the two-row orbital element number set and the observation time range; S3: controlling the all-day telescope satellite observation system to observe the satellite according to the satellite observation plan sequence until the observation plan is completed.

[0022] The present invention is a satellite observation plan sequence suitable for an all-day telescope. The satellite observation plan sequence is generated according to a two-row orbit element number set and an observation time range, so that an operator can use the all-day telescope satellite observation system to execute the satellite observation plan sequence at the beginning of work, thereby saving labor costs and reducing the experience requirements for the operator.

[0023] It should be noted that satellite tracking usually uses two-line orbital elements (TLE) to calculate the observable orbit of artificial satellites and guide the telescope to track and observe. Two-line orbital elements are a kind of orbit encoding method. At a given epoch, using a suitable prediction model, the position and velocity of the target satellite at any point in the orbit can be calculated with a certain accuracy. The calculation model corresponding to the two-line orbital elements is the simplified perturbations model. In general, the SGP4 and SDP4 models are usually used to calculate the motion trajectory of artificial satellites and space debris in the observable time period. Star tracking and satellite tracking are important functional components of horizontal telescopes. Star tracking plays an important role in astronomical observation, pointing correction and astronomical positioning. The commonly used star pointing calculation tool is the SOFA (Standards of Fundamental Astronomy) code toolkit. The telescope control system uses the input UTC time, station address and star information (right ascension, declination) to accurately calculate the position (azimuth, pitch) of the star at the station at that moment, thereby guiding the telescope to observe stars.

[0024] In some embodiments, Figure 2 As shown, step S2 specifically includes the following steps: S21: Assume that the observation time range of the all-day telescope is T, and within the observation time range T, set the set of all arc segments that meet the observation requirements selected from the two-row orbit element number set as S; S22: Set the starting time within the observation time range T as t i , at this time, i=0; S23: at t i At time t, set the arc set that meets the observation requirements as O, arc set O∈S, and determine whether the arc set O is non-empty. If so, execute step S24, otherwise execute step S25; S24: select the observation arc according to the satellite arc strategy, add the observation arc to the satellite observation plan sequence, and arrange the observation arcs contained in the satellite observation plan sequence in the order of joining; S25: let i=i+1, update time t i , i=1, 2, 3, ..., and judge the current time t i Is it less than the end time of the observation time range T? If so, use the current time t i Replace the time t in step S23 i , execute step S23, otherwise obtain the final satellite observation plan sequence.

[0025] It should be noted that, through the above operations, all observation arcs within the observation time range T can be obtained, so that the all-day telescope satellite observation system executes the corresponding observation plan corresponding to the time sequence within the observation time range T.

[0026] In some embodiments, in step S21 and step S23, the observation requirement means that the elevation angle of the satellite to be measured relative to the ground is greater than 20°, and the observation arc of the satellite to be measured is greater than 2 minutes.

[0027] It should be noted that if the elevation angle of the satellite to be measured relative to the ground is less than 20°, the telescope cannot observe the satellite all day long, and if the observation arc of the satellite to be measured is less than 2 minutes, the observation time is too short and observation errors are prone to occur.

[0028] In some embodiments, in step S25, the specific steps of obtaining the updated time include: when the arc segment set O is empty, then t i =t i +1min; when the arc set O is not empty, if the observation arc selected according to the satellite arc strategy is a low-orbit satellite arc, t i Assign the value to the end time of the observation arc + 1min; if the observation arc selected according to the satellite arc strategy is a medium-high orbit satellite arc, set t i Reassign the value to the end time of the observation arc + 3 minutes.

[0029] It should be noted that the observation arc is a period of time during which the arc appears, and the end time of the observation arc here refers to the total duration of the observation arc. When the observation arc is a low-orbit satellite arc, after the observation of the current observation arc is finished, it is necessary to make preliminary preparations for switching to the next observation arc, including turning the telescope direction and calculating positioning data. Therefore, t i The value assigned is the end time of the observation arc + 1min. The preliminary preparation is completed within 1min. When the observation arc is a medium-high orbit satellite arc, before calculating the positioning data of the satellite to be measured, it is necessary to photograph the neighboring stars of the current observation satellite, so as to use the neighboring stars of the current observation satellite for auxiliary positioning, observe the arc to be measured, and obtain the positioning data of the satellite to be measured. In addition, after the observation of the current observation arc is completed, it is also necessary to make preliminary preparations for switching to the next observation arc, so t i The value is reassigned to the end time of the observation arc + 3 minutes, and the photography of the neighboring stars of the current observation satellite and the preliminary preparations are completed within 3 minutes.

[0030] In some embodiments, Figure 3 As shown in the figure, the satellite arc strategy is as follows: in the arc set O, select the arc set R of the satellite with the largest weight; in the arc set R, select the low-orbit satellite arc set R L ; If the low-orbit satellite arc set R LIf the arc set R is empty, arc N is randomly selected from the arc set R, and part of arc N (the start time of arc N + 5 minutes) is intercepted as the observation arc; if the low-orbit satellite arc set R L Contains an arc segment, then the low-orbit satellite arc segment set R L The included arcs are taken as observation arcs; if the low-orbit satellite arc set R L If the number of included arcs is greater than 1, then in the observation arc set R L An arc segment is randomly selected as the observation arc segment; the satellite weight corresponding to the currently selected observation arc segment is reduced, and the satellite weights corresponding to other arc segments in the arc segment set O are increased, and the satellite weight corresponding to the observation arc segment has the lowest weight among the satellites corresponding to the arc segment set O.

[0031] It should be noted that the purpose of using the satellite arc strategy is to make each satellite have the closest possible probability of being observed. Furthermore, in the two-row orbit element set, each element represents a satellite, and each element will generate 0 or more observable arcs. A weight value w is initialized for each target. i =5 (w represents weight, i represents satellite number). If the target arc is selected, its weight is reduced, otherwise its weight is increased. If the satellite weights corresponding to all arcs contained in the observable arc set O are different, the arcs corresponding to high-weight satellites are given priority; if there are more than one arcs corresponding to the highest-weight satellite, the low-orbit satellite target arcs are given priority. Because medium- and high-orbit satellites move slowly and have a limited range of movement, if a medium- and high-orbit satellite target is within the observable range of the telescope at a certain time, it is likely that it will remain within the observable range of the telescope for a long time. Therefore, if the low-orbit satellite arc set R L If it is empty, arc segment N is randomly selected from the arc segment set R, and part of arc segment N (start time of arc segment N + 5min) is intercepted as the observation arc segment to avoid the satellite being unchanged for a long time and always being a medium-high orbit satellite. In addition, since medium-high orbit satellites have higher positioning accuracy requirements than low-orbit satellites, for all-day telescopes, after observing the arc segment of medium-high orbit satellites, it is still necessary to observe the neighboring stars for auxiliary positioning (the auxiliary positioning method is consistent with the medium-high orbit satellite positioning data generation method adopted by the invention entitled "A high-precision positioning method and system based on ground-based optical telescope" with a publication date of December 28, 2024, publication number CN117870647A, and invention name "A high-precision positioning method and system based on ground-based optical telescope"); after observing the arc segment of low-orbit satellites, the axis system positioning can be directly used as the measurement result.

[0032] In some examples, before generating a satellite observation plan sequence, weights of all satellites corresponding to two sets of orbital elements are initialized.

[0033] It should be noted that the weight of each satellite is initialized to ensure that the probability of each satellite being observed is basically the same.

[0034] In some instances, such as Figure 4 As shown, in step S3, the all-day telescope 4 satellite observation system includes a timing module 1, a main control module 2, an image module 3 and a telescope 4. The timing module 1 sends a trigger frequency and UTC time to the main control module 2, the main control module 2 sends a guidance instruction to the telescope 4, the main control module 2 also sends an observation instruction to the image module 3, the image module 3 receives the observation instruction, and sends a camera control instruction to the telescope 4, the telescope 4 rotates under the guidance of the main control module 2, and sends the satellite observation image to the image module 3 for real-time processing.

[0035] In some examples, the trigger frequency is 50 Hz or 100 Hz.

[0036] It should be noted that a time trigger submodule 11 is provided in the timing module 1, a task execution submodule 21, a guidance submodule 22 and an image instruction sending submodule 23 are provided in the main control module 2, a telescope 4 control submodule and an image acquisition submodule 42 are provided in the telescope 4, and an image instruction receiving submodule 31 and an image processing submodule 32 are provided in the image module 3 to complete the corresponding functions. Specifically, the time trigger submodule 11 sends the trigger frequency and UTC time to the task execution submodule 21, the guidance submodule 22 sends the guidance instruction to the telescope 4 control submodule, the image instruction sending submodule 23 sends the observation instruction to the image instruction receiving submodule 31, the image processing submodule 32 sends the camera control instruction to the image acquisition submodule 42, and the image acquisition submodule 42 sends the satellite observation image to the image processing submodule 32, so that the image acquisition submodule 42 processes the satellite observation image in real time and performs data analysis.

[0037] In some examples, step S3 specifically includes the following steps: S31: the timing module 1 provides the trigger frequency and UTC time to the main control module 2; S32: input the satellite observation plan sequence into the main control module 2, and check the satellite observation plan sequence at the initial time t i The type of observation plan it belongs to, at this time, i=0, the observation plan types include idle, medium and high orbit satellite observation plan, and low orbit satellite observation plan; S33: If the observation plan type is idle, the all-day telescope 4 satellite observation system is in a non-observation state, otherwise it is determined whether the observation plan type is a medium and high orbit satellite observation plan, if so, execute step S34; otherwise, execute step S35, the observation plan type is a low orbit satellite observation plan; S34: The all-day telescope 4 satellite observation system selects the neighboring stars of the current observation satellite for auxiliary positioning, observes the arc segment to be measured, obtains the positioning data of the satellite to be measured, and executes step S36; S35: The all-day telescope 4 satellite observation system observes the arc segment to be measured, obtains the positioning data of the satellite to be measured, and executes step S36; S36: Let i=i+1, update time ti , i=1, 2, 3, ..., using the current time t i Replace the time t in step S32 i , repeat steps S32-S35 until the execution of the satellite observation plan is completed.

[0038] It should be noted that the task execution sequence of the medium and high orbit satellite observation plan is as follows: photograph the neighboring stars of the current observation satellite, and the photographing time is less than 3 minutes. At the beginning of the satellite arc segment, the main control module 2 guides the telescope 4 to rotate according to the satellite trajectory, and controls the telescope 4 to start image acquisition; at the middle state of the satellite arc segment, the main control module 2 guides the telescope 4 to rotate according to the satellite trajectory, so that the image module 3 processes the satellite observation image data in real time; at the end of the satellite arc segment, the image module 3 controls the telescope 4 to end image acquisition, and the main control module 2 stops guiding the telescope 4 to rotate. At the beginning of the star arc segment, the main control module 2 guides the telescope 4 to rotate according to the star trajectory, and controls the telescope 4 to start image acquisition; at the middle state of the star arc segment, the main control module 2 guides the telescope 4 to rotate according to the star trajectory, so that the image module 3 processes the star observation image data in real time; at the end of the star arc segment, the image module 3 controls the telescope 4 to end image acquisition, and the main control module 2 stops guiding the telescope 4 to rotate, and generates satellite positioning data.

[0039] It should be noted that the task execution sequence of the low-orbit satellite observation plan is as follows: at the beginning state of the satellite arc, the main control module 2 guides the telescope 4 to rotate according to the satellite trajectory, and controls the telescope 4 to start image acquisition; in the middle state of the satellite arc, the main control module 2 guides the telescope 4 to rotate according to the satellite trajectory, so that the image module 3 processes the satellite observation image data in real time; at the end state of the satellite arc, the image module 3 controls the telescope 4 to end image acquisition, and the main control module 2 stops guiding the telescope 4 to rotate, and generates satellite positioning data.

[0040] Furthermore, the generation of medium and high orbit satellite positioning data is an existing technology; low orbit satellite positioning data uses axis positioning.

[0041] It should be understood that the various forms of processes shown above can be used to reorder, add or delete steps. For example, the steps described in the disclosure of the present invention can be performed in parallel, sequentially or in different orders, as long as the desired results of the technical solution disclosed in the present invention can be achieved, and this document does not limit this.

[0042] The above specific implementations do not constitute a limitation on the protection scope of the present invention. It should be understood by those skilled in the art that various modifications, combinations, sub-combinations and substitutions can be made according to design requirements and other factors. Any modification, equivalent substitution and improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. A method for planning and executing a satellite observation plan, characterized in that: The specific steps include: S1: Get two sets of orbital elements and set the observation time range of the all-sky telescope; S2: Generate satellite observation plan sequence based on two sets of orbital elements and observation time range; S3: According to the satellite observation plan sequence, control the all-day telescope satellite observation system to observe the satellite until the observation plan is completed.

2. The method for planning and executing a satellite observation plan according to claim 1, characterized in that: Step S2 specifically includes the following steps: S21: Let the observation time range of the all-sky telescope be T, and within the observation time range T, let the set of all arc segments that meet the observation requirements selected from the two-row orbit element number set be S; S22: Set the starting time within the observation time range T to t i , at this time, i=0; S23: At t i At time , set the arc set that meets the observation requirements as O, arc set O∈S, and determine whether the arc set O is non-empty. If so, execute step S24, otherwise execute step S25; S24: selecting an observation arc according to the satellite arc strategy, adding the observation arc to the satellite observation plan sequence, and arranging the observation arcs included in the satellite observation plan sequence in the order of addition; S25: Set i=i+1, update time t i , i=1, 2, 3, ..., and judge the current time t i Is it less than the end time of the observation time range T? If so, use the current time t i Replace the time t in step S23 i , execute step S23, otherwise obtain the final satellite observation plan sequence.

3. The method for planning and executing a satellite observation plan according to claim 2, characterized in that: In step S21 and step S23, the observation requirement is that the elevation angle of the satellite to be measured relative to the ground is greater than 20°, and the observation arc of the satellite to be measured is greater than 2 minutes.

4. The method for planning and executing a satellite observation plan according to claim 1, characterized in that: In step S25, the specific steps of obtaining the updated time include: When the arc set O is empty, then t i =t i +1min; When the arc set O is not empty, if the observation arc selected according to the satellite arc strategy is a low-orbit satellite arc, t i The value is assigned to the end time of the observation arc + 1min; If the observation arc segment selected according to the satellite arc segment strategy is a medium-high orbit satellite arc segment, t i Reassign the value to the end time of the observation arc + 3 minutes.

5. The method for planning and executing a satellite observation plan according to claim 2 or 4, characterized in that: The satellite arc strategy is as follows: Obtain an arc set O, and select an arc set R of a satellite with the largest weight from the arc set O; Select the low-orbit satellite arc set R from the arc set R L ; If the low-orbit satellite arc segment set R L If the arc set R is empty, arc N is randomly selected from the arc set R, and part of arc N is intercepted as the observation arc. L Contains an arc segment, then the low-orbit satellite arc segment set R L The included arcs are taken as observation arcs; if the low-orbit satellite arc set R L If the number of included arcs is greater than 1, then in the observation arc set R L Randomly select an arc segment as the observation arc segment; The satellite weight corresponding to the currently selected observation arc is reduced, and the satellite weights corresponding to other arcs in the arc set O are increased, and the satellite weight corresponding to the observation arc has the lowest weight among the satellites corresponding to the arc set O.

6. The method for planning and executing a satellite observation plan according to claim 5, characterized in that: Before generating the satellite observation plan sequence, the weights of all satellites corresponding to the two rows of orbital element sets are initialized.

7. The method for planning and executing a satellite observation program according to claim 1, characterized in that: In step S3, the all-day telescope satellite observation system includes a timing module, a main control module, an image module and a telescope. The timing module sends a trigger frequency and UTC time to the main control module, the main control module sends a guidance instruction to the telescope, and the main control module also sends an observation instruction to the image module. The image module receives the observation instruction and sends a camera control instruction to the telescope. The telescope rotates under the guidance of the main control module and sends the satellite observation image to the image module for real-time processing.

8. The method for planning and executing a satellite observation plan according to claim 7, characterized in that: Step S3 specifically includes the following steps: S31: The timing module provides the trigger frequency and UTC time to the main control module; S32: Input the satellite observation plan sequence into the main control module. The main control module checks the satellite observation plan sequence at the initial time t based on the trigger frequency and UTC time. i The type of observation plan it belongs to. At this time, i=0, and the observation plan types include idle, medium- and high-orbit satellite observation plan, and low-orbit satellite observation plan; S33: If the observation plan type is idle, the all-day telescope satellite observation system is in a non-observation state, otherwise it is determined whether the observation plan type is a medium- and high-orbit satellite observation plan, and if so, step S34 is executed; Otherwise, execute step S35, and the observation plan type is a low-orbit satellite observation plan; S34: The all-day telescope satellite observation system selects neighboring stars of the current observation satellite for auxiliary positioning, observes the arc segment to be measured, obtains positioning data of the satellite to be measured, and executes step S36; S35: The all-day telescope satellite observation system observes the arc segment to be measured, obtains the positioning data of the satellite to be measured, and executes step S36; S36: Set i=i+1, update time t i , i=1, 2, 3, ..., using the current time t i Replace the time t in step S32 i , repeat steps S32-S35 until the execution of the satellite observation plan is completed.

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