CN117745038B - SGP4 algorithm-based occultation daily task planning system and application method thereof - Google Patents
SGP4 algorithm-based occultation daily task planning system and application method thereof Download PDFInfo
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Abstract
The invention provides a star-masking daily task planning system based on an SGP4 algorithm and a use method thereof, wherein the star-masking daily task planning system comprises function modules which are sequentially connected. The invention has the beneficial effects that: the invention uses the occultation orbit, calculates the circle information by calling SGP4 algorithm, is an application to occultation data products; the invention provides the calculated accumulation seconds of the start of transfer, the end of transfer and the execution of the actual data download, the time for storing the transfer duration of the occultation data and the time for downloading the occultation data at different download rates, no special person is required to perform manual calculation, and the burden of operators and the occurrence of calculation errors are reduced.
Description
Technical Field
The invention belongs to the field of occultation task planning, and particularly relates to an occultation daily task planning system based on an SGP4 algorithm and a use method thereof.
Background
With the continuous improvement of aerospace technology, various commercial satellites appear in space to observe earth information. Occultation becomes a popular choice for earth observation, but as more and more occultation runs on orbit, task planning and on-orbit control management of occultation every day become problems. The following problems exist at present:
the manual use of a formula is needed to calculate the circle information, the task time planning task is calculated according to the circle information, the manual use of a table or a text format is used for the instruction source code splicing, the human efficiency is low, and the time is long; if the number of in-orbit satellites is large, more time is spent, and labor cost is increased.
Disclosure of Invention
In view of the above, the present invention aims to provide a occultation daily mission planning system based on SGP4 algorithm and a method for using the same, so as to solve the above-mentioned problems in the prior art.
In order to achieve the above purpose, the technical scheme of the invention is realized as follows:
In a first aspect, the invention provides a occultation daily task planning system based on an SGP4 algorithm, which comprises a time setting module, an orbit type selecting module, an SGP4 algorithm module, a station forecast information storage module, a ground station elevation setting module, a satellite type selecting module, a circle threshold value setting module, a satellite arc segment information display module, a satellite remote control instruction parameter setting module, a satellite remote control instruction parameter calculating module, a satellite service instruction template selecting module and a satellite service instruction generating module, wherein the time setting module is sequentially in communication connection with the orbit type selecting module, the SGP4 algorithm module, the station forecast information storage module, the ground station elevation setting module, the satellite type selecting module, the circle threshold value setting module, the satellite arc segment information display module, the satellite remote control instruction parameter setting module, the satellite remote control instruction parameter calculating module, the satellite service instruction template selecting module and the satellite service instruction generating module.
The invention also provides a method for using the occultation daily mission planning system based on SGP4 algorithm based on the same conception, which comprises the following steps:
s1, providing a occultation orbit for carrying out circle forecasting on a satellite transit ground station;
s2, calculating task execution time based on the circle forecast information of the step S1;
s3, automatically generating a star masking instruction file based on the task execution time in the step S2.
Further, in step S1, providing a occultation orbit for performing a circle forecast of a satellite transit ground station, including:
S11, generating a six-root-number or two-line-number satellite orbit format by using the on-orbit occultation data based on the orbit type selection module;
S12, through the satellite orbit in any one of the two satellite formats in the step S11, the SGP4 algorithm is called based on the SGP4 algorithm module to acquire circle prediction of the occultation ground station, circle prediction information is acquired, a file in a text format is generated by the circle prediction information, and the file is stored in the station prediction information storage module.
Further, in step S11, the generation process of the six-root-number or two-line-root-number satellite orbit format based on the orbit type selection module using the on-orbit mask data includes:
The six numbers are telemetry signals transmitted by the satellite, the baseband equipment in the ground station equipment is used for demodulating the telemetry signals, analog signals are converted into digital signals, the data information of the digital signals contains XYZ axis position and speed information corresponding to each moment of the satellite, and the XYZ axis position and speed information of the satellite is converted into a six-number type satellite orbit format through codes;
The six-root form is converted into the two-line root form through code.
Further, in step S12, the turn forecast information includes satellite name, ground station name, arc start time, arc end time, data transmission start time, data transmission end time, lifting track mark, and entry/exit azimuth information.
Further, in step S2, calculating the task execution time based on the turn forecast information of step S1 includes:
s21, setting time for planning tasks based on a time setting module;
S22, selecting a file in a satellite orbit format based on an orbit type selection module, calling an SGP4 algorithm module, and calculating satellite transit circle information, wherein the satellite transit circle information comprises azimuth angle and pitch angle of a satellite relative to a ground station and longitude and latitude position information of the satellite on a map every second when the satellite passes through the ground station, converting the information into a file in a text format, and placing the file in a main program folder of a station forecast information storage module;
s23, setting a satellite data transmission task elevation angle based on a ground station elevation angle setting module and a satellite arc segment information display module, processing circle information of a text format file, and displaying circle information conforming to elevation angle constraint;
S24, selecting the satellite type of the generated command based on the satellite type selection module, the satellite remote control command parameter setting module and the satellite remote control command parameter calculation module, setting the modulation time of the mask star and the delay constraint condition of the data transmission transmitter, and calculating accumulated seconds of starting the mask star tracking, ending the tracking, starting the transfer, ending the transfer, starting the execution of the data download, the duration of the transfer of the mask star data and the time required by the data download of the mask star at different download rates;
S25, selecting a satellite-based data transmission rate selection module to perform circle task planning according to satellite transit circle time information, on-board stored data quantity and time required by data downloading of a mask satellite under different downloading rates;
S26, selecting a mask command fixed template based on a satellite service command template selection module and a satellite service command generation module, and generating an uploading command based on the mask command fixed template.
Further, in step S3, a occultation instruction file is automatically generated based on the task execution time of step S2, including:
The user confirms the circle number of the execution task and the data transmission code rate of the data to be downloaded, clicks the command making template, and the planning system automatically calculates the time when the data download is finished and automatically generates an execution command file according to the selected circle number of the execution task and the data transmission code rate of the mask download data.
Compared with the prior art, the star-masking daily task planning system based on the SGP4 algorithm and the use method thereof have the following advantages:
(1) The invention relates to a star masking daily task planning system based on an SGP4 algorithm and a use method thereof, wherein the star masking orbit is used, and the circle information is calculated by calling the SGP4 algorithm, so that the star masking daily task planning system is an application to star masking data products; the invention provides the calculated accumulation seconds of the start of transfer, the end of transfer and the execution of the actual data download, the time for storing the transfer duration of the occultation data and the time for downloading the occultation data at different download rates, no special person is required to perform manual calculation, and the burden of operators and the occurrence of calculation errors are reduced.
(2) The SGP4 algorithm-based occultation daily task planning system and the application method thereof automatically generate task execution instructions, can effectively and automatically calculate and convert data errors, and avoid the occurrence of failure of satellite uploading instructions.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the invention. In the drawings:
FIG. 1 is a schematic diagram of a system according to an embodiment of the present invention;
Fig. 2 is a schematic diagram illustrating a detailed principle of the usage method according to an embodiment of the present invention.
Detailed Description
It should be noted that, without conflict, the embodiments of the present invention and features of the embodiments may be combined with each other.
In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, are merely for convenience in describing the present invention and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first", "a second", etc. may explicitly or implicitly include one or more such feature. In the description of the present invention, unless otherwise indicated, the meaning of "a plurality" is two or more.
In the description of the present invention, it should be noted that, unless explicitly specified and limited otherwise, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be either fixedly connected, detachably connected, or integrally connected, for example; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the above terms in the present invention can be understood by those of ordinary skill in the art in a specific case.
The invention will be described in detail below with reference to the drawings in connection with embodiments.
Noun interpretation:
SGP4 algorithm: the TLE orbit report calculates the satellite orbit by using the SGP4/SDP4 model developed by NORAD, the SGP4 model is developed by Ken Cranford in 1970 and is used for near-earth satellites, the model is a simplification of the widely resolved theory of Lane and Cranford (1969), and the model needs to consider the influence of the non-spherical gravitation of the earth, the solar-lunar gravitation, the solar radiation pressure, the atmospheric resistance and other perturbation forces. SGP4 (SIMPLIFIED GENERAL Perturbations), a simplified conventional perturbation model, can be applied to near-earth objects with orbital periods less than 225 minutes. SDP4 (SIMPLIFIED DEEP SPACE Perturbations) is a simplified deep space perturbation model applied to objects that are farther away from the earth or orbit for periods greater than 225 minutes. If TLE track report is substituted into SGP4 model, space target with track period less than 225 minutes can be successfully predicted, and position and speed of target object at any time can be solved.
As shown in fig. 1-2, the occultation daily task planning system based on the SGP4 algorithm comprises a time setting module, an orbit type selecting module, an SGP4 algorithm module, a ground station elevation angle setting module, a station forecast information storage module, a satellite type selecting module, a satellite remote control instruction parameter setting module, a satellite remote control instruction parameter calculating module, a satellite arc section information display module, a satellite service instruction template selecting module and a satellite service instruction generating module, wherein the time setting module is sequentially connected with the orbit type selecting module, the SGP4 algorithm module, the ground station elevation angle setting module, the station forecast information storage module, the satellite type selecting module, the satellite remote control instruction parameter setting module, the satellite remote control instruction parameter calculating module, the satellite arc section information display module, the satellite service instruction template selecting module and the satellite service instruction generating module in a communication manner.
The application method of the star-masking daily task planning system based on the SGP4 algorithm comprises the following steps of:
s1, providing a occultation orbit for carrying out circle forecasting on a satellite transit ground station;
s2, calculating task execution time based on the circle forecast information of the step S1;
s3, automatically generating a star masking instruction file based on the task execution time in the step S2.
According to the invention, the SGP4 algorithm is called to calculate the satellite transit ground station circle number information, the daily occultation task circle number is planned according to the circle number information, the daily occultation task execution time is calculated, and the daily task management is carried out on a plurality of occultation satellites, so that the occultation satellites execute corresponding tasks daily according to the calculated task time, and the satellite task management is facilitated. The star masking task design and the star masking control have the advantages that the task execution time is complex, a great deal of time is required to be spent, a lot of time is required to plan one star, and the time of a plurality of stars is calculated, so that the efficiency is low. The occultation daily task planning system based on the SGP4 algorithm only needs to select corresponding circles for users, the system can automatically calculate task execution time, generate corresponding instruction files, and annotate the corresponding instruction files to the satellite, and the satellite can execute tasks at corresponding moments according to the time in the instruction files.
A first object of the present invention is to provide circle forecasting of satellite transit ground stations by occultation orbits.
The technical scheme for realizing the first purpose of the invention is as follows: and (3) using six-number or two-line satellite orbit formats generated by the on-orbit occultation data, taking the satellite orbit of one (any one) of the two formats, calling an SGP4 algorithm (calling when the system calculates the forecast arc section information of the station, and calling when the SGP4 algorithm module) to acquire the circle forecast of the occultation ground station, obtaining circle forecast information, generating a file of a text format by the circle forecast information, and storing the file into the station forecast information storage module.
In this embodiment, SGP4 corresponds to a prediction model, and inputs two lines of numbers, and outputs position and velocity information of the satellite at any time through the model.
The specific generation process of six numbers and two rows of numbers comprises the following steps: the six numbers are telemetry signals transmitted by the satellite, demodulation is carried out through a baseband device in ground station equipment, namely the so-called analog signals are converted into digital signals, the digital signal data information contains XYZ axis position and speed information corresponding to each moment of the satellite (the centroid of the satellite can be taken as an origin to establish an XYZ vertical coordinate system), the XYZ axis position and speed information of the satellite is converted into orbit information in the form of six numbers through codes (specifically, the six pieces of information are six parameters, namely an orbit semi-long axis, an eccentricity, an orbit inclination angle, an ascending intersection point, a near-site amplitude angle and a near-site amplitude angle, the position of the satellite in space can be determined, and the six numbers can be converted into the form of two lines of numbers through codes). Furthermore, both forms of track information are known in the art. Six numbers and two rows of numbers converted from satellite XYZ position and speed information are selected as input, and the specific calling module is an orbit type selection module and an SGP4 algorithm module.
The purpose of the six-number and two-line satellite orbit format is to call the SGP4 algorithm to calculate the time for the occultation passing through the ground station, and if there is no satellite orbit, that is, six-number and two-line number, there is no way to calculate the visibility information of the ground station to the satellite, this information includes the time when the ground station sees the satellite, and the time when the ground station sees the satellite last time, and the elevation angle and azimuth information of the ground station antenna during this time.
The second purpose of the invention is to calculate task execution time, reduce the burden of operators and reduce the calculation amount.
The station forecast information generated by the first purpose only comprises satellite names, ground station names, arc starting time, arc ending time, data transmission starting time, data transmission ending time, lifting orbit marks and outbound azimuth angle information. The data transmission start and end time is different from the arc start and end time, the arc start and end time is the time period when the satellite can be seen by the ground station, and the data transmission start and end time is the time when the satellite starts transmitting data to the ground and ends transmitting data in the arc start and end time. The second objective calculation is to convert the end time of the data transmission starting time into accumulated seconds, and the reference time is as follows: 1 month 1 day 12 of 2000: 00:00, the accumulated seconds is the second value from the present time to the reference time. The second purpose is to calculate the time required by the satellite to transmit to the ground according to different data transmission code rates and judge whether the time for starting and ending the arc segment in the first purpose is enough to finish data transmission. And the second purpose is to calculate the time for the single occultation machine to transfer data to the star computer, the time is recorded as the transfer time, and the information calculated by the second purpose is finally filled into the instruction template to generate instructions. (the information transfer inside the satellite can be seen in the following figures).
The technical scheme for realizing the second purpose of the invention is as follows: the application method of the star-masking daily mission planning system based on the SGP4 algorithm comprises the following steps of:
1. setting the time of a task to be planned in a time setting module;
2. And selecting a file in a occultation orbit format in the orbit type selection module, the SGP4 algorithm module and the station forecast information storage module, calling the SGP4 algorithm module, and calculating satellite transit circle information, wherein the information comprises azimuth angle, pitch angle and longitude and latitude position information of a satellite on a map every second when the satellite passes through a ground station, converting the information into a file in a text format, and placing the file in a main program folder (station forecast information storage module).
3. And setting satellite data transmission task elevation angles in the ground station elevation angle setting module and the satellite arc segment information display module, processing the circle information in a text format, and displaying the circle information conforming to the elevation angle constraint.
The processing of the circle information in the text format specifically comprises the following steps: and selecting circle arcs conforming to the elevation angle of the ground station according to the starting time and the ending time of each satellite transit ground station calculated by the first target SGP4 and the elevation angle setting of the ground station.
Examples of turn information that meets the elevation constraint:
for example, the elevation angle of the ground station is set to be 0 DEG, which means that the ground station can see the satellite when the ground station keeps 0 DEG with the ground surface horizontally, the corresponding arc period is prolonged, and if the elevation angle of the ground station is set to be 5 DEG, the ground station can see the satellite when the ground station lifts the head to keep 5 DEG with the ground surface, and the arc period is shortened; setting to 5 ° is the start 5 ° and the end 5 °.
4. And in the satellite type selection module, the satellite remote control instruction parameter setting module and the satellite remote control instruction parameter calculation module, the satellite type for generating an instruction is selected, constraint conditions such as the modulation time of a mask star, the delay of a data transmission transmitter and the like are set, and accumulated seconds for starting the tracking, the transfer start, the transfer end and the execution of actual data downloading are calculated, so that the time for transferring the mask star data and the time for downloading the mask star under different downloading speeds are prolonged.
5. And selecting a proper occultation downloading rate to carry out circle task planning according to satellite transit circle time information, on-board stored data quantity and time required by data downloading of occultation under different downloading rates in a satellite data transmission rate selecting module.
6. And selecting a satellite-masking instruction fixed template in the satellite service instruction template selection module to generate an uploading instruction.
The third purpose of the invention is to automatically generate the occultation instruction file, reduce the burden of operators, and avoid time spent for splicing instruction source codes.
The second purpose is to calculate only some parameters needed for generating the instruction, the third purpose is to fill the calculated instruction into the instruction template to generate the actual instruction, and the generated instruction can be sent to the satellite.
The technical scheme for realizing the third object of the invention is as follows: the user confirms the circle of the task to be executed and the data transmission code rate of the data to be downloaded, clicks the command making template, and the system automatically calculates the time of finishing the data downloading and automatically generates an execution command file according to the selected circle of the task to be executed and the data transmission code rate of the data downloaded by the mask (selects the template, clicks the template to generate, the internal code copies the content in the template, fills the calculated parameters, and then generates the command file).
The invention has the advantages that:
(1) The invention uses the occultation orbit, calculates the circle information by calling the SGP4 algorithm, and is an application to occultation data products.
(2) The invention provides the calculated accumulation seconds of the start of transfer, the end of transfer and the execution of the actual data download, the time for storing the transfer duration of the occultation data and the time for downloading the occultation data at different download rates, no special person is required to perform manual calculation, and the burden of operators and the occurrence of calculation errors are reduced.
(3) The invention automatically generates the task execution instruction, can effectively and automatically calculate and convert to avoid the occurrence of the condition of data error and satellite uploading instruction failure.
Example 1
The application method of the star-masking daily mission planning system based on the SGP4 algorithm comprises the following steps of:
1. setting the time for planning tasks: in the frame of step 1, selecting the start time and the end time of the simulation scene, and clicking the time setting key;
2. Selecting a file in a occultation orbit format, calling an SGP4 algorithm module, calculating satellite transit circle information, converting the information into a file in a text format, and placing the file in a main program folder: in the box of step 1, selecting a six-number format (or two lines of numbers), opening a scene, selecting a six-number file, waiting for the loading and updating of a satellite orbit file, clicking SGP4 to start calculation, waiting for calculation, and finishing the display of a calculation window;
3. setting a ground station data transmission elevation angle, and processing the circle information of a text format generated by an SGP4 algorithm: in the frame of step 2, selecting the available circle file path, selecting the folder of the generated file in step 1 (the folder is under the program installation directory);
4. Displaying the circle information processed by the text format in a system window: in the frame of step 3, a magic cube or a cloud remote series is selected, the circle threshold value is set to 300 (the purpose is to call constraint setting of circle arc time length in circle file information calculated by SGP4, specifically, a plurality of ground stations can see circle of satellites in the file calculated by SGP4, but time for each ground station to see satellites is different, when a task is executed, information which can see satellites for more than 300s is generally selected by the least ground stations, the information is displayed in a satellite arc information display module, and therefore, the setting is needed in a circle threshold value setting module), and the circle file of one star generated in step 2 is selected by SGP4 file selection;
5. Setting attitude adjustment time of the occultation, real-time data transmission time delay, data transmission transmitter time delay (set in a satellite telemetry instruction parameter setting module), and the following time conditions of the last circle: calculating accumulated seconds of starting star-masking tracking, ending tracking, starting transfer, ending transfer and executing actual data downloading, and the time for transferring star-masking data and the time for downloading the data of the star-masking at different downloading rates: clicking to start calculation;
6. selecting a proper occultation downloading rate to carry out circle task planning according to satellite transit circle time information, on-board storage data quantity and time required by data downloading of occultation under different downloading rates;
7. and selecting a mask command template to generate an uploading command.
The foregoing description of the preferred embodiments of the invention is not intended to be limiting, but rather is intended to cover all modifications, equivalents, alternatives, and improvements that fall within the spirit and scope of the invention.
Claims (1)
1. The application method of the star-masking daily task planning system based on the SGP4 algorithm is characterized by comprising the following steps of: the use method is realized by a occultation daily task planning system based on an SGP4 algorithm, the occultation daily task planning system based on the SGP4 algorithm comprises a time setting module, an orbit type selecting module, an SGP4 algorithm module, a station forecast information storage module, a ground station elevation setting module, a satellite type selecting module, a circle threshold setting module, a satellite arc information display module, a satellite remote control instruction parameter setting module, a satellite remote control instruction parameter calculation module, a satellite service instruction template selecting module and a satellite service instruction generating module, wherein the time setting module is sequentially connected with the orbit type selecting module, the SGP4 algorithm module, the station forecast information storage module, the ground station elevation setting module, the satellite type selecting module, the circle threshold setting module, the satellite arc information display module, the satellite remote control instruction parameter setting module, the satellite remote control instruction parameter calculation module, the satellite service instruction template selecting module and the satellite service instruction generating module in a communication mode;
the using method comprises the following steps:
s1, providing a occultation orbit for carrying out circle forecasting on a satellite transit ground station;
s2, calculating task execution time based on the circle forecast information of the step S1;
s3, automatically generating a star masking instruction file based on the task execution time of the step S2;
In step S1, providing a occultation orbit for performing a circle forecast of a satellite transit ground station, including:
S11, generating a six-root-number or two-line-number satellite orbit format by using the on-orbit occultation data based on the orbit type selection module;
s12, acquiring circle forecast information by calling an SGP4 algorithm based on an SGP4 algorithm module through a satellite orbit in any one of two satellite formats in the step S11, generating a file in a text format by the circle forecast information, and storing the file in a station forecast information storage module;
In step S11, the on-orbit mask data is used by the orbit type selection module to generate a six-root-form or two-line-root-form satellite orbit format, and the generation process includes:
The six numbers are telemetry signals transmitted by the satellite, the baseband equipment in the ground station equipment is used for demodulating the telemetry signals, analog signals are converted into digital signals, the data information of the digital signals contains XYZ axis position and speed information corresponding to each moment of the satellite, and the XYZ axis position and speed information of the satellite is converted into a six-number type satellite orbit format through codes;
the six-root form is converted into two-row root form through code;
In step S12, the circle forecast information includes satellite name, ground station name, arc start time, arc end time, data transmission start time, data transmission end time, lifting track mark, and entry/exit azimuth information;
In step S2, calculating the task execution time based on the turn forecast information of step S1 includes:
s21, setting time for planning tasks based on a time setting module;
S22, selecting a file in a satellite orbit format based on an orbit type selection module, calling an SGP4 algorithm module, and calculating satellite transit circle information, wherein the satellite transit circle information comprises azimuth angle and pitch angle of a satellite relative to a ground station and longitude and latitude position information of the satellite on a map every second when the satellite passes through the ground station, converting the information into a file in a text format, and placing the file in a main program folder of a station forecast information storage module;
s23, setting a satellite data transmission task elevation angle based on a ground station elevation angle setting module and a satellite arc segment information display module, processing circle information of a text format file, and displaying circle information conforming to elevation angle constraint;
S24, selecting the satellite type of the generated command based on the satellite type selection module, the satellite remote control command parameter setting module and the satellite remote control command parameter calculation module, setting the modulation time of the mask star and the delay constraint condition of the data transmission transmitter, and calculating accumulated seconds of starting the mask star tracking, ending the tracking, starting the transfer, ending the transfer, starting the execution of the data download, the duration of the transfer of the mask star data and the time required by the data download of the mask star at different download rates;
S25, selecting a satellite-based data transmission rate selection module to perform circle task planning according to satellite transit circle time information, on-board stored data quantity and time required by data downloading of a mask satellite under different downloading rates;
S26, selecting a mask command fixed template based on a satellite service command template selection module and a satellite service command generation module, and generating an uploading command based on the mask command fixed template;
in step S3, automatically generating a occultation instruction file based on the task execution time of step S2, including:
The user confirms the circle number of the execution task and the data transmission code rate of the data to be downloaded, clicks the command making template, and the planning system automatically calculates the time when the data download is finished and automatically generates an execution command file according to the selected circle number of the execution task and the data transmission code rate of the mask download data.
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Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB201717138D0 (en) * | 2016-11-28 | 2017-12-06 | National Univ Of Defense Technology | Spark-based imaging satellite task preprocessing parallelization method |
| CN115015974A (en) * | 2021-12-31 | 2022-09-06 | 中国电波传播研究所（中国电子科技集团公司第二十二研究所） | Ionospheric detection performance simulation evaluation method based on GNSS masker and tri-band beacon |
| CN116707613A (en) * | 2023-06-07 | 2023-09-05 | 中国科学院微小卫星创新研究院 | Satellite-ground joint planning method and system for ultra-low orbit satellites |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7856294B2 (en) * | 2007-12-14 | 2010-12-21 | Sra International, Inc. | Intelligent system and method for spacecraft autonomous operations |
-
2024
- 2024-02-19 CN CN202410182332.XA patent/CN117745038B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB201717138D0 (en) * | 2016-11-28 | 2017-12-06 | National Univ Of Defense Technology | Spark-based imaging satellite task preprocessing parallelization method |
| CN115015974A (en) * | 2021-12-31 | 2022-09-06 | 中国电波传播研究所（中国电子科技集团公司第二十二研究所） | Ionospheric detection performance simulation evaluation method based on GNSS masker and tri-band beacon |
| CN116707613A (en) * | 2023-06-07 | 2023-09-05 | 中国科学院微小卫星创新研究院 | Satellite-ground joint planning method and system for ultra-low orbit satellites |
Non-Patent Citations (2)
| Title |
|---|
| Research on the Number and Distribution of GPS Occultation Events for Orbit Selection for Global/Regional Observation;Kai. Tan et al.;《 2007 3rd International Conference on Recent Advances in Space Technologies》;20070616;全文 * |
| 星光掩星探测技术的轨道模拟结果分析;孙明晨;吴小成;胡雄;;光谱学与光谱分析;20200115(第01期);全文 * |
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