Occultation ephemeris prediction system and method based on Astrogator propagation model

Abstract

The present invention provides an occultation ephemeris prediction system and method based on an Astrogator propagation model, comprising a satellite configuration file module, a time setting module, a configuration file loading module, a propagation model setting module, a satellite establishment module and an ephemeris output module, wherein the satellite configuration file module, the time setting module, the configuration file loading module, the scene opening module, the propagation model setting module, the satellite establishment module and the ephemeris output module are sequentially connected in communication. Beneficial effects of the present invention: The present invention provides a method for calculating satellite ephemeris data, and further provides a method for automatically converting into a fixed ephemeris format and tracking strategy required by a collision emergency center.

Description

Technical Field

[0001] The invention belongs to the field of ephemeris prediction, and in particular relates to an occultation ephemeris prediction system and method based on an Astrogator propagation model. Background Art

[0002] In recent years, the commercial space industry has flourished. As more and more spacecraft are launched into space, there is a risk of collision between spacecraft and other spacecraft and space debris. To avoid this, the Collision Emergency Center will monitor all spacecraft and space debris targets in space. When a rocket is launched, the Collision Emergency Center will collect information about the satellites on board and number the satellites before launch. As time goes by and solar activity generates large geomagnetic storms that affect satellites in orbit, the orbital heights of most low-orbit satellites decay. To ensure the on-orbit life and orbital stability of satellites, on-orbit thruster devices are required to perform orbit raising and lowering operations on satellites to maintain the satellite's orbital height and phase and extend the satellite's life. Daily satellite monitoring and on-orbit orbit raising and lowering operations may create the risk of collision between satellites and space debris.

[0003] To predict the risk of collision in advance, it is necessary to know the future position information of the satellite. The future position information of the satellite is then used as satellite ephemeris information. The satellite ephemeris information is compared with the orbital position information of all satellites and space debris in space to predict whether the satellite will have a collision risk in the future.

[0004] The satellite ephemeris contains the position and velocity information in the XYZ axis direction based on the satellite's own coordinate system (the satellite's own coordinate system has the satellite's center of mass as the origin, the satellite's speed direction as the X axis, the satellite's direction pointing to the center of the earth as the Z axis, and the Y axis perpendicular to the XOZ plane).

[0005] Disadvantages: First, there is a lack of methods for predicting ephemeris information; second, the ephemeris format used for verification by the collision emergency center is fixed. Summary of the invention

[0006] In view of this, the present invention aims to propose an occultation ephemeris prediction system and method based on the Astrogator propagation model to solve at least one problem existing in the above-mentioned prior art.

[0007] To achieve the above object, the technical solution of the present invention is achieved as follows:

[0008] In a first aspect, the present invention provides an occultation ephemeris prediction system based on an Astrogator propagation model, comprising a satellite configuration file module, a time setting module, a configuration file loading module, a propagation model setting module, a satellite establishment module and an ephemeris output module, wherein the satellite configuration file module, the time setting module, the configuration file loading module, the scene opening module, the propagation model setting module, the satellite establishment module and the ephemeris output module are communicatively connected in sequence.

[0009] In a second aspect, based on the same concept, the present invention also provides an occultation ephemeris prediction method based on the Astrogator propagation model, comprising the following steps:

[0010] S1. Set the satellite configuration file based on the satellite configuration file module and formulate a satellite ignition plan;

[0011] S2, setting the start / end time of the occultation orbit data based on the time setting module;

[0012] S3, select the satellite configuration file based on the configuration file loading module, and generate a simulation scene based on the start time and end time set in step S2;

[0013] S4. Setting the Astrogator propagation model based on the propagation model setting module;

[0014] S5, establishing a satellite based on the data of step S3 and step S4 and a satellite establishing module;

[0015] S6, setting the time interval for calculating satellite ephemeris;

[0016] S7, outputting the ephemeris based on the ephemeris output module;

[0017] S8. Output tracking strategy based on the ephemeris output in step S7.

[0018] Furthermore, in step S1, a satellite ignition plan is formulated, and the ignition time, maneuvering time, speed increment, fuel consumption, satellite mass, and windward surface information need to be filled into the configuration file.

[0019] Furthermore, in step S2, a time setting module is used to set a time period for calculating the forecast satellite ephemeris data.

[0020] Further, in step S2, the start time is set to include the epoch time of the satellite's initial orbit, or is directly set to the epoch time of the initial orbit; the end time is set to the last ignition time plus three days as the end time.

[0021] Furthermore, in step S8, the output tracking strategy based on the ephemeris output in step S7 includes:

[0022] The first step is to convert the output ephemeris information into a format that can be recognized by the collision emergency center;

[0023] The second step is to use the output tracking strategy to output the tracking strategy.

[0024] Furthermore, the tracking strategy includes the instantaneous root number corresponding to the planned ignition time in the ephemeris data, the ignition time, the number of ignitions, and the fuel consumption information.

[0025] Compared with the prior art, the occultation ephemeris prediction system and method based on the Astrogator propagation model described in the present invention has the following advantages:

[0026] The present invention discloses an occultation ephemeris prediction system and method based on the Astrogator propagation model. The present invention provides a method for calculating satellite ephemeris data. In addition, the present invention also provides a method for automatically converting the fixed ephemeris format and tracking strategy required by the collision emergency center. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] The accompanying drawings constituting a part of the present invention are used to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation of the present invention. In the accompanying drawings:

[0028] Figure 1 It is a schematic diagram of the overall system flow according to an embodiment of the present invention;

[0029] Figure 2 A schematic diagram of the method flow of the embodiment of the present invention;

[0030] Figure 3 This is a schematic diagram of a satellite configuration file according to an embodiment of the present invention. DETAILED DESCRIPTION

[0031] 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.

[0032] 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 limiting the present invention. In addition, the terms "first", "second", and the like 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", and the like 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.

[0033] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" 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 present invention can be understood by specific circumstances.

[0034] The present invention will be described in detail below with reference to the accompanying drawings and in conjunction with embodiments.

[0035] Glossary:

[0036] Astrogator: Astrogator is a computational model for interplanetary navigation, mainly used in the aerospace field. Its main function is to provide the spacecraft with the optimal path to the target planet based on the position and speed of stars, planets, satellites and interstellar dust, as well as the state of the spacecraft itself.

[0037] like Figures 1 to 3 As shown, the occultation ephemeris prediction system based on the Astrogator propagation model includes a satellite configuration file module, a time setting module, a configuration file loading module, a propagation model setting module, a satellite establishment module and an ephemeris output module. The satellite configuration file module, the time setting module, the configuration file loading module, the scene opening module, the propagation model setting module, the satellite establishment module and the ephemeris output module are communicatively connected in sequence.

[0038] The occultation ephemeris prediction method based on the Astrogator propagation model includes the following steps:

[0039] 1. Set up the satellite configuration file, formulate the satellite ignition (maneuver) plan, and fill in the ignition time, maneuver duration, speed increment, fuel consumption, satellite mass, windward surface and other related information into the configuration file;

[0040] 2. To set the start / end time, click Time Settings.

[0041] Specifically, the start time is set to include the epoch time of the satellite's initial orbit, or it can be directly set to the epoch time of the initial orbit; the end time is set to add three days after the last ignition time as the end time. The purpose of this is that satellite ignition is a process of slowly raising the orbit. Three days is actually the subsequent ephemeris information generated when the orbit is stable after the last ignition of the orbit, and compared with all satellite and debris orbits monitored by the emergency center to see if there will be a collision within the next three days.

[0042] 3. Load the configuration file, and load the satellite configuration file configured according to the plan before using this system into the system.

[0043] 4. Open the scene.

[0044] Use the set start time and end time to generate a simulation scenario. The following operations need to be performed in this scenario.

[0045] 5. Set up a propagation model and generate a propagation model. The propagation model is loaded with daily and future forecast solar activity, such as F10.7 index, AP index and other parameter information. Because solar activity may affect the orbit behind the satellite, the generated ephemeris information (satellite XYZ position speed information), that is, the future forecast, so the accuracy of the forecast still needs to load this model, which is used in the satellite created below.

[0046] 6. Build a satellite.

[0047] Create the corresponding satellite according to the information in the configuration file loaded earlier. The configuration file will contain information such as the satellite name, ignition plan, maneuvering duration, speed increment, initial satellite orbit, fuel consumption, satellite mass, windward surface, etc. The established satellite uses the Astrogator propagation model. The Astrogator propagation model generates a simulated maneuvering process according to the configuration file information, thereby generating a planned satellite propagation process. Specifically, the Astrogator propagation model will load the configuration file information after the satellite is established, and then generate position and speed information and set ignition time according to the speed increment and ignition plan in the configuration file. The propagation of Astrogator corresponds to the XYZ position and speed information of the satellite orbit body coordinate system.

[0048] 7. Set the calculation time interval.

[0049] Set the time interval, which sets the time interval of the satellite ephemeris output below, because the satellite ephemeris is specifically the position of the satellite in space corresponding to a time point (XYZ position speed information). The output can be set to 1s or 60s, that is, the output ephemeris information is the position of the satellite in the previous second and the position of the satellite in the next second, or the position of the satellite in the previous minute and the next minute. In actual use, the output is generally 1 minute.

[0050] 8. Output ephemeris.

[0051] Just click on output. The data given to the collision emergency center are in a fixed format, including the satellite name, number, ephemeris start time and end time, etc.

[0052] 9. Output tracking strategy.

[0053] The tracking strategy is generated by clicking directly, and it also has a fixed format, which includes information such as the control duration and speed increment.

[0054] In a preferred embodiment of the present invention, a first object of the present invention is to provide a method for calculating predicted satellite ephemeris using occultation orbit data, which can calculate satellite ephemeris prediction data.

[0055] The technical solution for achieving the first purpose of the present invention is: the first step is to use a time setting module to set the time period for calculating and forecasting satellite ephemeris data; the second step is to select a satellite configuration file; the third step is to set a propagation model (including an atmospheric model); the fourth step is to establish a satellite according to the satellite configuration file and the propagation model; and the fifth step is to output the ephemeris data.

[0056] In a preferred embodiment of the present invention, the second purpose of the present invention is to provide a fixed ephemeris format that can be automatically converted into the format required by the collision emergency center and sent through the interface with the collision emergency center. The ephemeris data must be converted into the format required by the collision emergency center department before the collision risk forecast can be carried out. The tracking strategy file specified by the collision emergency center must also be output (tracking strategy: including the instantaneous root number corresponding to the planned ignition time in the ephemeris data, ignition time, number of ignitions, fuel consumption and other information, which are all in the satellite configuration file);

[0057] The technical solution for achieving the second object of the present invention is: in the first step, the output ephemeris information is converted into a format recognizable by the collision emergency center; in the second step, the tracking strategy is output using the output tracking strategy.

[0058] Example 1

[0059] Requirement: Calculate the ephemeris data for satellite A at the end of orbit raising on XX / XX / XX and three days after the end. Figure 3 This is a diagram of the satellite configuration file.

[0060] method:

[0061] Step 1: Set the start time and end time. The start time and end time settings need to include the time point of XX year XX month XX day. Click the time setting. If the words "Time setting successful" are displayed, it means the setting is successful. If the start time and end time settings do not include the time point of XX year XX month XX day, click the time setting, and the words "Time setting failed" will be displayed.

[0062] Step 2: Select the satellite configuration file, which is tabular data.

[0063] Step 3: Set up the atmospheric propagation model.

[0064] Step 4: Build the satellite.

[0065] Step 5: Set the time interval for ephemeris data.

[0066] Step 6: Output the ephemeris.

[0067] Step 7: Output tracking strategy.

[0068] The present invention provides a method for calculating satellite ephemeris data. In addition, the present invention also provides a fixed ephemeris format and tracking strategy that are automatically converted into the format required by the collision emergency center.

[0069] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. The occultation ephemeris prediction method based on the Astrogator propagation model is implemented by the occultation ephemeris prediction system based on the Astrogator propagation model, which is characterized by: An occultation ephemeris prediction system based on an Astrogator propagation model comprises a satellite configuration file module, a time setting module, a configuration file loading module, a propagation model setting module, a satellite establishment module and an ephemeris output module, wherein the satellite configuration file module, the time setting module, the configuration file loading module, the propagation model setting module, the satellite establishment module and the ephemeris output module are sequentially connected in communication; The forecasting method includes the following steps: S1. Set the satellite configuration file based on the satellite configuration file module and formulate a satellite ignition plan; S2, setting the start / end time of the occultation orbit data based on the time setting module; S3, select the satellite configuration file based on the configuration file loading module, and generate a simulation scene based on the start time and end time set in step S2; S4. Setting the Astrogator propagation model based on the propagation model setting module; S5, establishing a satellite based on the data of step S3 and step S4 and a satellite establishing module; S6, setting the time interval for calculating satellite ephemeris; S7, outputting the ephemeris based on the ephemeris output module; S8, output tracking strategy based on the ephemeris output in step S7; In step S1, a satellite ignition plan is formulated, and the ignition time, maneuvering time, speed increment, fuel consumption, satellite mass, and windward surface information need to be filled into the configuration file; In step S2, a time setting module is used to set a time period for calculating forecast satellite ephemeris data; In step S2, the start time is set to include the epoch time of the satellite's initial orbit, or directly set to the epoch time of the initial orbit; the end time is set to the last ignition time plus three days as the end time; In step S8, the output tracking strategy based on the ephemeris output in step S7 includes: The first step is to convert the output ephemeris information into a format that can be recognized by the collision emergency center; The second step is to use the output tracking strategy to output the tracking strategy; The tracking strategy includes the instantaneous root number corresponding to the planned ignition time in the ephemeris data, the ignition time, the number of ignitions, and the fuel consumption information.

2. An electronic device, comprising a processor and a memory connected to the processor for storing instructions executable by the processor, characterized in that: The processor is used to execute the occultation ephemeris prediction method based on the Astrogator propagation model as described in claim 1 above.

3. A server, characterized in that: The invention comprises at least one processor and a memory in communication connection with the processor, wherein the memory stores instructions executable by the at least one processor, and the instructions are executed by the processor so that the at least one processor executes the occultation ephemeris prediction method based on the Astrogator propagation model as claimed in claim 1.

4. A computer-readable storage medium storing a computer program, characterized in that: When the computer program is executed by a processor, the occultation ephemeris prediction method based on the Astrogator propagation model described in claim 1 is implemented.

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