Method for Planning and Executing a Satellite Observation Plan

Abstract

The present invention belongs to the technical field of optoelectronic telescope control, and particularly relates to a method for planning and executing a satellite observation plan. The method includes: S1: obtaining a set of two-line orbital elements and setting the observation time range of the all-weather telescope; S2: generating a satellite observation plan sequence according to the set of two-line orbital elements and the observation time range; S3: controlling the all-weather telescope satellite observation system to observe the satellite according to the satellite observation plan sequence until the observation plan is completed. The present invention can automatically plan the satellite observation plan, and make the observation frequencies of different satellites more uniform by adjusting the observation weights of the satellites.

Description

Technical Field

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

[0002] In recent years, optoelectronic telescopes conventionally used for night observations mainly use visible light cameras and have a relatively large field of view. When observing under the condition of good atmospheric transmittance at night, there are many stars for astronomical positioning in the image in addition to satellites. Different from traditional optoelectronic telescopes, all-weather telescopes use short-wave infrared detectors and have a very small field of view, usually about 10' in diagonal. When observing satellites, not only is the signal-to-noise ratio low, but there are not enough stars for astronomical positioning in the field of view. Therefore, after observing a satellite, an all-weather telescope needs to sweep and swing to observe the stars around the satellite trajectory and calculate the precise pointing of the satellite through a certain algorithm.

[0003] When using an all-weather telescope to observe satellites, the observation plan is usually manually executed by an operator. The operator performs orbit calculation based on the set of two-line element sets of the satellite to be observed, manually selects to observe a certain satellite during a certain time period, manually selects the stars around it that can be used for auxiliary positioning for observation after observing the satellite, and then calculates the precise pointing of the satellite. The manual execution of the observation plan by the operator has the following disadvantages: 1) The operation method of the equipment is relatively complex, and errors are likely to occur during the operation process; 2) After observing each satellite, the operator has to manually select stars, and the operator needs to continuously operate the equipment to complete the observation of all targets. 3) When there are many satellite targets to be observed, it is difficult for the operator to plan the satellite observation order, and there may be a situation where some targets are observed too frequently, while some targets 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 solution based on a large visible light field of view, the operator inputs the observation plan sequence (not the set of two-line element sets) into the telescope control software, and the telescope tracks according to the given observation plan sequence. However, in actual satellite observation work, there are not only observation plan sequences but also forms of sets of two-line element sets. If the observation plan cannot be planned for the set of two-line element sets, the execution of the observation work has great limitations. In addition, when observing high-orbit satellite targets with an all-weather telescope, it is necessary to plan the observation plan of neighboring stars for auxiliary positioning, and this solution is not applicable to all-weather telescopes. Summary of the Invention

[0005] In view of this, the present invention aims to provide a method for planning and executing a satellite observation plan to solve the above problems. The present invention inputs a set of two-line orbital elements into the all-weather telescope satellite observation system, and the system will calculate the observation trajectories of each satellite to be observed and arrange these observation trajectories into 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-weather telescope satellite observation system automatically executes all observation plans.

[0006] To achieve the above object, the technical solution of the present invention is realized as follows:

[0007] A method for planning and executing a satellite observation plan specifically includes the following steps:

[0008] S1: Obtain a set of two-line orbital elements and set the observation time range of the all-weather telescope;

[0009] S2: Generate a satellite observation plan sequence according to the set of two-line orbital elements and the observation time range;

[0010] S3: According to the satellite observation plan sequence, control the all-weather telescope satellite observation system to observe the satellite until the observation plan is completed.

[0011] Further, step S2 specifically includes the following steps:

[0012] S21: Let the observation time range of the all-weather telescope be T, and within the observation time range T, set the set of all arcs that meet the observation requirements selected from the set of two-line orbital elements as S;

[0013] S22: Set the starting moment within the observation time range T as t i , at this time, i = 0;

[0014] S23: At the moment of t i , set the set of arcs that meet the observation requirements as O, and the set of arcs O ∈ S. Determine whether the set of arcs O is non-empty. If so, execute step S24; otherwise, execute step S25;

[0015] S24: Select an observation arc according to the satellite arc strategy, add the observation arc to the satellite observation plan sequence, and the observation arcs included in the satellite observation plan sequence are arranged in the order of addition;

[0016] S25: Let i = i + 1, update the moment t i , i = 1, 2, 3,..., and determine whether the current moment t i is less than the end time of the observation time range T. If so, replace the moment t i in step S23 with the current moment t i, perform step S23; otherwise, obtain the final satellite observation plan sequence. Further, in steps S21 and S23, the observation requirement means that the pitch angle of the satellite to be measured relative to the ground is greater than 20°, and the observation arc segment of the satellite to be measured is greater than 2 min.

[0017] Further, in step S25, the specific steps to obtain the updated time include:

[0018] When the arc segment set O is empty, then t i = t i + 1 min;

[0019] When the arc segment set O is not empty, if the observed arc segment selected according to the satellite arc segment strategy is a low-earth orbit satellite arc segment, assign t i to the end time of the observed arc segment + 1 min;

[0020] If the observed arc segment selected according to the satellite arc segment strategy is a medium-high earth orbit satellite arc segment, re-assign t i to the end time of the observed arc segment + 3 min.

[0021] Further, the satellite arc segment strategy is specifically:

[0022] Obtain the arc segment set O, and select the arc segment set R of the satellite with the largest weight in the arc segment set O;

[0023] Select the low-earth orbit satellite arc segment set R in the arc segment set R L ;

[0024] If the low-earth orbit satellite arc segment set R L is empty, then randomly select an arc segment N in the arc segment set R, and intercept a partial arc segment of the arc segment N as the observed arc segment; if the low-earth orbit satellite arc segment set R L contains one arc segment, then use the arc segment contained in the low-earth orbit satellite arc segment set R L as the observed arc segment; if the low-earth orbit satellite arc segment set R L contains more than one arc segment, then randomly select an arc segment in the observed arc segment set R L as the observed arc segment;

[0025] Reduce the weight of the satellite corresponding to the currently selected observed arc segment, increase the weights of the satellites corresponding to the other arc segments in the arc segment set O, and the weight of the satellite corresponding to the observed arc segment is the lowest among the weights of the satellites corresponding to the arc segment set O.

[0026] Further, before generating the satellite observation plan sequence, initialize the weights of all satellites corresponding to the two-line orbital element sets.

[0027] Further, in step S3, the all-weather 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 guiding instruction to the telescope and 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.

[0028] Further, step S3 specifically includes the following steps:

[0029] S31: The timing module provides a trigger frequency and UTC time to the main control module;

[0030] S32: Input the satellite observation plan sequence into the main control module. The main control module checks the observation plan type to which the satellite observation plan sequence belongs at the initial time t i where i = 0. The observation plan types include idle, medium-high orbit satellite observation plan, and low-earth orbit satellite observation plan;

[0031] S33: If the observation plan type is idle, the all-weather telescope satellite observation system is in a non-observation state. Otherwise, determine whether the observation plan type is a medium-high orbit satellite observation plan. If so, execute step S34; otherwise, execute step S35, where the observation plan type is a low-earth orbit satellite observation plan;

[0032] S34: The all-weather telescope satellite observation system selects neighboring stars of the currently observed satellite for assisted positioning, observes the arc segment to be measured, obtains the positioning data of the satellite to be measured, and executes step S36;

[0033] S35: The all-weather 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;

[0034] S36: Let i = i + 1, update the time t i where i = 1, 2, 3, …, and use the current time t i to replace the time t in step S32 i and repeat steps S32 - S35 until the execution of the satellite observation plan is completed. Compared with the prior art, the present invention can achieve the following beneficial effects:

[0035] (1) The method for planning and executing the satellite observation plan according to the present invention can automatically plan the satellite observation plan and make the observation frequencies of different satellites more uniform by adjusting the observation weights of the satellites.

[0036] (2)The method for planning and executing the satellite observation plan according to the present invention does not require operators to participate in the execution of the observation work. The operation during observation is simple, does not rely on experienced operators, and is not prone to operation errors. BRIEF DESCRIPTION OF THE DRAWINGS

[0037] The drawings constituting a part of the present invention are used to provide a further understanding of the present invention. The schematic embodiments and descriptions thereof of the present invention are used to explain the present invention and do not constitute an improper limitation to the present invention. In the drawings:

[0038] Figure 1 is a schematic flow chart of the method for planning and executing the satellite observation plan according to the embodiment of the present invention;

[0039] Figure 2 is a schematic flow chart of generating a satellite observation plan sequence according to the embodiment of the present invention;

[0040] Figure 3 is a schematic flow chart of the satellite arc segment strategy according to the embodiment of the present invention;

[0041] Figure 4 is a schematic structural diagram of the all-weather telescope satellite observation system according to the embodiment of the present invention;

[0042] Figure 5 is a schematic flow chart of controlling the all-weather telescope satellite observation system to observe a satellite according to the embodiment of the present invention.

[0043] Description of the reference numerals:

[0044] 1, time synchronization module; 2, main control module; 3, image module; 4, telescope; 11, time trigger sub-module; 21, task execution sub-module; 22, guiding sub-module; 23, image instruction sending sub-module; 31, image instruction receiving sub-module; 32, image processing sub-module; 41, telescope control sub-module; 42, image acquisition sub-module. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0045] In order to make the objectives, technical solutions and advantages of the present invention clearer, the present invention will be further described in detail below with reference to the drawings and specific embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and do not constitute a limitation to the present invention.

[0046] It should be noted that, without conflict, the embodiments in the present invention and the features in the embodiments can be combined with each other.

[0047] In the description of the present invention, it should be understood that the orientation or positional relationship indicated by the terms "center", "longitudinal", "transverse", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. is based on the orientation or positional relationship shown in the drawings. It is 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 thus should not be construed as a limitation to 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 specifying the quantity of the indicated technical features. Thus, the features defined with "first", "second", etc. may explicitly or implicitly include one or more of such features. In the description of the present invention, unless otherwise stated, the meaning of "a plurality" is two or more.

[0048] In the description of the present invention, it should be noted that unless otherwise clearly specified and limited, the terms "mounted", "connected", "coupled" should be understood in a broad sense. For example, it may be a fixed connection, a detachable connection, or an integral connection; it may be a mechanical connection or an electrical connection; it may be directly connected or indirectly connected through an intermediate medium, and it may be the communication inside two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood through specific circumstances.

[0049] The present invention will be described in detail below with reference to the drawings and in conjunction with embodiments.

[0050] As Figure 1 shown, the method for planning and executing a satellite observation plan provided by the present invention specifically includes the following steps: S1: Obtain a set of two-line element sets and set the observation time range of the all-weather telescope; S2: Generate a satellite observation plan sequence according to the set of two-line element sets and the observation time range; S3: According to the satellite observation plan sequence, control the all-weather telescope satellite observation system to observe the satellite until the observation plan is completed.

[0051] The present invention is a satellite observation plan sequence applicable to an all-weather telescope. A satellite observation plan sequence is generated according to a set of two-line element sets and an observation time range, enabling an operator to execute the satellite observation plan sequence using the all-weather telescope satellite observation system at the beginning of work, saving labor costs and reducing the experience requirements for operators.

[0052] It should be noted that satellite tracking usually calculates the observable orbit of artificial satellites using two-line element sets (TLEs) and guides the telescope for tracking observations. Two-line element sets are a way of orbit encoding. At a given epoch, using a suitable prediction model, the position and velocity of a target satellite at any point on the orbit can be calculated with a certain accuracy. The calculation model corresponding to two-line element sets is the simplified perturbations model. Generally, models SGP4 and SDP4 are usually used to calculate the motion trajectories of artificial satellites and space debris during the observable time period. Star tracking and satellite tracking are important functional components of altazimuth telescopes. Star tracking plays an important role in astronomical observations, pointing corrections, and astronomical positioning. The commonly used star pointing calculation tool is the SOFA (Standards of Fundamental Astronomy) code toolkit. The telescope control system accurately calculates the position (azimuth, elevation) of the star at the station at that moment by inputting the UTC time, station location, and star information (right ascension, declination), so as to guide the telescope for star observations.

[0053] In some embodiments, as Figure 2 shown, step S2 specifically includes the following steps: S21: Set the observation time range of the all-sky telescope as T, and within the observation time range T, set the set of all arcs that meet the observation requirements selected from the two-line element set as S; S22: Set the starting moment within the observation time range T as t i , at this time, i = 0; S23: At the moment of t i , set the set of arcs that meet the observation requirements as O, and the set of arcs O ∈ S. Determine whether the set of arcs 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 the observation arcs included in the satellite observation plan sequence are arranged in the order of addition; S25: Let i = i + 1, update the moment t i , i = 1, 2, 3,..., and determine whether the current moment t i is less than the termination time of the observation time range T. If so, replace the moment t i in step S23 with the current moment t i , execute step S23, otherwise obtain the final satellite observation plan sequence.

[0054] It should be noted that through the above operations, all the observation arcs within the observation time range T can be obtained, so that the all-sky telescope satellite observation system executes the corresponding observation plan according to the time sequence within the observation time range T.

[0055] In some embodiments, in steps S21 and S23, the observation requirements mean 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.

[0056] 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 throughout the day, 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 likely to occur.

[0057] In some embodiments, in step S25, the specific steps for obtaining the updated time include: when the arc segment set O is empty, then t i = t i + 1 minute; when the arc segment set O is not empty, if the observation arc segment selected according to the satellite arc segment strategy is a low-earth orbit satellite arc segment, assign t i to the end time of the observation arc segment + 1 minute; if the observation arc segment selected according to the satellite arc segment strategy is a medium-high earth orbit satellite arc segment, re-assign t i to the end time of the observation arc segment + 3 minutes.

[0058] It should be noted that the observation arc segment is a period of time when the arc segment appears. The end time of the observation arc segment here refers to the total duration when the arc segment appears. When the observation arc segment is a low-earth orbit satellite arc segment, after the observation of the current observation arc segment is completed, it is necessary to make preparations for switching to the next observation arc segment, including turning the telescope direction and calculating positioning data, etc. Therefore, assign t i to the end time of the observation arc segment + 1 minute, and the preparatory work is completed within 1 minute. When the observation arc segment is a medium-high earth orbit satellite arc segment, 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 assisted positioning, observe the arc segment to be measured, and obtain the positioning data of the satellite to be measured. In addition, after the observation of the current observation arc segment is completed here, it is also necessary to make preparations for switching to the next observation arc segment. Therefore, re-assign t i to the end time of the observation arc segment + 3 minutes, and photograph the neighboring stars of the current observation satellite and the preparatory work are completed within 3 minutes.

[0059] In some embodiments, as Figure 3 shown, the satellite arc segment strategy is specifically: in the arc segment set O, select the arc segment set R of the satellite with the largest weight; in the arc segment set R, select the low-earth orbit satellite arc segment set R L ; if the low-earth orbit satellite arc segment set R LIf it is empty, randomly select an arc segment N from the set R of arc segments, and intercept a partial arc segment of arc segment N (start time of arc segment N + 5 min) as the observation arc segment; if the set R of low-earth orbit satellite arc segments L contains one arc segment, then use the arc segment contained in the set R of low-earth orbit satellite arc segments L as the observation arc segment; if the set R of low-earth orbit satellite arc segments L contains more than one arc segment, then randomly select an arc segment from the set R of observation arc segments L as the observation arc segment; reduce the weight of the satellite corresponding to the currently selected observation arc segment, increase the weights of the satellites corresponding to the other arc segments in the set O of arc segments, and the weight of the satellite corresponding to the observation arc segment is the lowest among the weights of the satellites corresponding to the set O of arc segments.

[0060] It should be noted that the purpose of using the satellite arc segment strategy is: to make the observed probabilities of each satellite as close as possible. Further, in the set of two-line orbital elements, each orbital element represents a satellite, and each orbital element generates zero or more observable arc segments. Initialize a weight value w i = 5 (w represents the weight, and i represents the satellite number). If the target arc segment is selected, reduce its weight; otherwise, increase its weight. If the weights of the satellites corresponding to all the arc segments contained in the observable set O of arc segments are different, give priority to the arc segments corresponding to the satellites with high weights; if there is more than one arc segment corresponding to the satellite with the highest weight, give priority to the low-earth orbit satellite target arc segments. Because medium and high-earth orbit satellites move slowly and have a limited range of motion. If a medium and high-earth orbit satellite target is within the observable range of the telescope at a certain time, it is very likely to still be within the observable range of the telescope for a long time. Therefore, if the set R L of low-earth orbit satellite arc segments is empty, randomly select an arc segment N from the set R of arc segments, and intercept a partial arc segment of arc segment N (start time of arc segment N + 5 min) as the observation arc segment, so as to avoid the satellite being observed for a long time remaining unchanged, which is always the medium and high-earth orbit satellite. In addition, since medium and high-earth orbit satellites have higher requirements for positioning accuracy than low-earth orbit satellites, for a full-time telescope, after observing the arc segments of medium and high-earth orbit satellites, it is still necessary to observe the neighboring stars for auxiliary positioning (the auxiliary positioning method is the same as the method for generating medium and high-earth orbit satellite positioning data used in the patent with the publication date of December 28, 2024, publication number CN117870647A, and invention name "A High-Precision Positioning Method and System Based on a Ground-Based Optical Telescope"); after observing the arc segments of low-earth orbit satellites, the axis system positioning can be directly used as the measurement result.

[0061] In some instances, before generating the satellite observation plan sequence, initialize the weights of all the satellites corresponding to the set of two-line orbital elements.

[0062] It should be noted that initializing the weights of each satellite ensures that the observed probabilities of each satellite are basically the same.

[0063] In some instances, such as Figure 4 shown, in step S3, the all-weather 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 guiding 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.

[0064] In some instances, the trigger frequency is 50 Hz or 100 Hz.

[0065] It should be noted that a time trigger sub-module 11 is provided in the timing module 1, a task execution sub-module 21, a guiding sub-module 22, and an image instruction sending sub-module 23 are provided in the main control module 2, a telescope 4 control sub-module and an image acquisition sub-module 42 are provided in the telescope 4, and an image instruction receiving sub-module 31 and an image processing sub-module 32 are provided in the image module 3 to complete corresponding functions. Specifically, the time trigger sub-module 11 sends a trigger frequency and UTC time to the task execution sub-module 21, the guiding sub-module 22 sends a guiding instruction to the telescope 4 control sub-module, the image instruction sending sub-module 23 sends an observation instruction to the image instruction receiving sub-module 31, the image processing sub-module 32 sends a camera control instruction to the image acquisition sub-module 42, and the image acquisition sub-module 42 sends the satellite observation image to the image processing sub-module 32, enabling the image acquisition sub-module 42 to perform real-time processing of the satellite observation image and conduct data analysis.

[0066] In some instances, step S3 specifically includes the following steps: S31: The timing module 1 provides a 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 observation plan type to which the satellite observation plan sequence belongs at the initial moment t i where i = 0 at this time, and the observation plan types include idle, medium-high orbit satellite observation plan, and low-earth orbit satellite observation plan; S33: If the observation plan type is idle, the all-weather telescope 4 satellite observation system is in a non-observation state. Otherwise, determine whether the observation plan type is a medium-high orbit satellite observation plan. If so, execute step S34; otherwise, execute step S35, where the observation plan type is a low-earth orbit satellite observation plan; S34: The all-weather telescope 4 satellite observation system selects the neighboring stars of the currently observed satellite for auxiliary positioning, observes the arc to be measured, obtains the positioning data of the satellite to be measured, and executes step S36; S35: The all-weather telescope 4 satellite observation system observes the arc to be measured, obtains the positioning data of the satellite to be measured, and executes step S36; S36: Let i = i + 1 and update the moment ti where \(i = 1, 2, 3,\cdots\), and the current time \(t\) is used i to replace the time \(t\) in step S32 i , and steps S32 - S35 are repeated until the execution of the satellite observation plan is completed.

[0067] It should be noted that the task execution sequence of the medium - high - orbit satellite observation plan is as follows: photograph the neighboring stars of the current observation satellite, with the photographing time less than 3 minutes. At the start state 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, enabling the image module 3 to perform real - time processing on the satellite observation image data; at the end state 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 start state 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, enabling the image module 3 to perform real - time processing on the star observation image data; at the end state 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, generating satellite positioning data.

[0068] It should be noted that the task execution sequence of the low - orbit satellite observation plan is as follows: at the start state 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, enabling the image module 3 to perform real - time processing on the satellite observation image data; at the end state 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, generating satellite positioning data.

[0069] Furthermore, the generation of medium - high - orbit satellite positioning data is prior art; low - orbit satellite positioning data uses axis - system positioning.

[0070] It should be understood that the various forms of processes shown above can be reordered, steps can be added or deleted. For example, the steps described in the disclosure of the present invention can be executed 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 no limitations are imposed herein.

[0071] The above specific embodiments do not constitute a limitation to the protection scope of the present invention. Those skilled in the art should understand that various modifications, combinations, sub-combinations and substitutions can be made according to design requirements and other factors. Any modifications, equivalent substitutions and improvements made within the spirit and principle of the present invention shall be included within 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; 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; S3: Control the all-day telescope satellite observation system to observe the satellite according to the satellite observation plan sequence until the observation plan is completed; The all-day telescope satellite observation system includes a timing module, a main control module, an imaging module and a telescope; 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.

2. The method for planning and executing a satellite observation plan according to claim 1, 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.

3. 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.

4. The method for planning and executing a satellite observation program according to claim 3, 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 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.

5. The method for planning and executing a satellite observation plan according to claim 4, 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.

6. The method for planning and executing a satellite observation program according to claim 1, characterized in that: In step S3, the timing module sends the 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.

Images