Playback task on-satellite autonomous planning method based on special data transmission station

Abstract

A playback task on-satellite autonomous planning method based on a special data transmission station comprises the following steps: calculating a time period in which a spacecraft is visible to the special station in a planning period according to satellite orbit data and ground shielding angles of different orientations of the special station, and notifying a ground operation and control center of time period information for the ground to know and arrange services in advance. And the satellite also autonomously downloads the image data to the special station in the visible section. According to the method, playback task in-orbit autonomous calculation independent of ground calculation and resource coordination is realized, the method can be used for satellite data autonomous downloading planning of various loads, and the satellite-ground coordination efficiency and autonomy are effectively improved.

Description

Technical Field

[0001] The invention relates to an autonomous on-board planning method for a playback mission based on a dedicated data transmission station, belonging to the technical field of autonomous mission planning for remote sensing satellites. Background Art

[0002] The existing autonomous mission planning software on board coordinates the onboard control system, camera payload system, and data transmission system to work together to achieve imaging and image data storage for the target mission. When the satellite passes over an available ground station, the data can be transmitted down through the satellite-to-ground link for use on the ground.

[0003] The use of traditional data transmission stations relies on a series of operations such as ground station extrapolation, ground station arc resource application, and data transmission window annotation, which consumes ground manpower and time, and relies on resource coordination between different ground units.

[0004] In order to improve the operational efficiency and autonomy of satellite-ground mission planning, a ground station specifically used for downlinking mission planning data has been designed, which is called a dedicated data transmission station. For this dedicated station, the onboard software also needs to design a set of usage methods that are highly autonomous and convenient for satellite-ground collaboration. Summary of the invention

[0005] The technical problem to be solved by the present invention is: to overcome the deficiencies of the prior art and provide an on-board autonomous planning method for playback tasks based on a dedicated digital transmission station, which is matched with the dedicated station to improve the autonomy and collaborative efficiency of on-board software.

[0006] The purpose of the present invention is achieved through the following technical solutions:

[0007] A method for autonomous on-board planning of a playback mission based on a dedicated data transmission station, comprising:

[0008] S1. Bind data according to the actual situation of the data transmission dedicated station;

[0009] S2, based on the station addresses bound in S1, roughly search and output the visible arc segment of the satellite to the dedicated station;

[0010] S3, according to the station addresses bound in S1 and the visible arc segments of the satellite to the dedicated station output by the rough search, a fine search is performed to output the visible arc segments of the satellite to the dedicated station;

[0011] S4, according to the S3 precise search output satellite to the dedicated station visible arc segment, arrange the task planning results to be transmitted;

[0012] S5. Arrange the on-board data playback based on the satellite's visible arc segment to the dedicated station output by precise search in S3.

[0013] An electronic device, comprising:

[0014] Processor; and

[0015] a memory for storing computer program instructions;

[0016] When the computer program instructions are loaded and run by the processor, the processor executes the on-board autonomous planning method for the playback mission based on the dedicated data transmission station.

[0017] A computer-readable storage medium stores computer program instructions, which, when loaded and executed by a processor, enable the processor to execute the on-board autonomous planning method for a playback task based on a dedicated data transmission station.

[0018] A computer program product stored on a non-transitory computer-readable medium includes program codes for implementing the on-board autonomous planning method for replaying missions based on a dedicated data transmission station.

[0019] Compared with the prior art, the present invention has the following beneficial effects:

[0020] (1) Satellites can perform subsequent autonomous calculations through the binding of data transmission dedicated stations, avoiding excessive manpower and time consumption by ground-based calculations and resource coordination;

[0021] (2) Satellite search is divided into two parts. The ground station is introduced to calculate the elevation angle of the spacecraft. The entry and exit times of the satellite's visible arc are searched according to the elevation angle information, which can quickly perform a rough screening of the visible arc.

[0022] (3) Based on the rough screening arc segment, the ground station pointing to the spacecraft elevation angle / azimuth angle is calculated. According to the ground shielding angle of the dedicated station of the bound satellite and the shortest transmission time constraint of the dedicated station, the entry and exit time of the satellite visible arc segment is traversed and searched, and the arc segment can be accurately searched quickly;

[0023] (4) Satellites transmit information in the visible range through telemetry, so the ground can know in advance and make business arrangements;

[0024] (5) The satellite autonomously completes data downlink based on the visible arc segment and playback type, effectively improving the efficiency and autonomy of satellite-ground coordination. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Figure 1 The figure is a flow chart of the steps of the method of the present invention. DETAILED DESCRIPTION

[0026] To make the objectives, technical solutions and advantages of the present invention more clear, the embodiments of the present invention will be further described in detail below with reference to the accompanying drawings.

[0027] A method for autonomous on-board planning of playback missions based on a dedicated digital transmission station calculates the time period during which the spacecraft is visible to the dedicated station within a planning cycle based on satellite orbit data and the ground shielding angles of the dedicated station at different orientations, and notifies the ground operation and control center of the time period information so that the ground can know it in advance and arrange business. The satellite will also autonomously download image data to the dedicated station within the visible period. This method realizes autonomous on-orbit calculation of playback missions that is independent of ground calculations and resource coordination, and can be used for autonomous downlink planning of satellite data for various payloads, effectively improving the efficiency and autonomy of satellite-ground collaboration.

[0028] More specifically, Figure 1 As shown, including the following:

[0029] S1. Initialization of the dedicated data transmission station.

[0030] If there is no binding information in the data transmission dedicated station, binding is performed according to the actual situation of each dedicated station. The dedicated station SpecStation parameters are expressed as:

[0031] SpecStation={name,LLA[3],Mu

[360] ,transtmin,datatype,flgTMDT};

[0032] Where name is the name of the dedicated station; LLA[3] is the longitude, latitude and altitude of the dedicated station site; Mu

[360] is the ground shielding angle array of the dedicated station, taking the east direction as zero, and defining the minimum elevation angle with data transmission capability in the corresponding direction of the data transmission station in a counterclockwise direction at intervals of 1 degree; transtmin is the shortest transmission time of the dedicated station; datatype is the playback data type selection of the dedicated station; flgTMDT is the flag of whether the dedicated station is a digital transmission and measurement and control integrated station.

[0033] The S2 data transmission dedicated station roughly calculates the satellite visible arc segment.

[0034] Set the search step length mdt_SearchStep. According to the planning period, the maximum number of searches N1 can be calculated. According to the longitude, latitude and altitude of the dedicated ground station, the position vector of the dedicated station can be calculated. Determine the minimum value θ of the dedicated station ground shielding angle array d,min .

[0035] According to the satellite's orbital parameters, take the planned start time as the search starting point t0 and calculate t k =t0+k*mdt_SearchStep(k=0,1,2,…,N) corresponding to the satellite position vector Then calculate the vector from the ground station to the spacecraft According to the definition,

[0036] At this time, the elevation angle of the ground station pointing to the spacecraft is

[0037]

[0038] After traversal search, if μ is found k-1 Less than θ d,min , and μ k Greater than or equal to θ d,min , then the moment tk is the entry time, recorded as t ds0 ; If μ is found k-1 Greater than or equal to θ d,min , and μ k Less than θ d,min , then at this time t k is the time of going out, recorded as t de0 .

[0039] After the traversal algorithm in step S2, one or more visible arcs can be found. However, the shielding angle thresholds for judging these arcs are the minimum values ​​of the 360 ​​groups, which may not meet the shielding angle thresholds of the corresponding azimuth at the corresponding moment. Therefore, these arcs need to be further judged to ensure that the visibility of the arcs is met.

[0040] S3. The dedicated digital transmission station makes precise calculations of the satellite visible arc segments.

[0041] For the visible arc segment [t ds0 ,t de0 ] Perform the following traversal search:

[0042] (31)Enter time t ds search:

[0043] Let t ds =t ds0 , calculate the spacecraft's position vector at this time Calculate the vector from the ground station to the spacecraft

[0044]

[0045] The elevation angle of the spacecraft can be calculated

[0046]

[0047] Azimuth of the spacecraft

[0048]

[0049] Wherein, if α<0, α=α+360. α=Round(α), Round() represents the rounding function. If α>359, α=0.

[0050] According to the azimuth angle α, find S1 and the dedicated station ground shielding angle array Mu

[360] configured in the data transmission dedicated station initialization step, and obtain the azimuth angle θ d,α , if μ i >θ d,α , then find the entry time t ds Exit the traversal; otherwise, let t ds =t ds +mdt μ .mdt μ To calculate the search step size more precisely, repeat step (31).

[0051] (32) Exit time t de search:

[0052] Let t de =t de0 , calculate the spacecraft's position vector at this time Calculate the vector pointing from the ground station to the spacecraft.

[0053]

[0054] The elevation angle of the spacecraft can be calculated

[0055]

[0056] Azimuth of the spacecraft

[0057]

[0058] Wherein, if α<0, α=α+360. α=Round(α), Round() represents the rounding function. If α>359, α=0.

[0059] According to the azimuth angle α, look up the table S1 and the dedicated station ground shielding angle array Mu

[360] configured in the data transmission dedicated station initialization step to obtain the azimuth angle θ d,α , if μ i >θ d,α , then find the exit time t de Exit the traversal; otherwise, let t de =t de -mdt μ .mdt μ To calculate the search step size more precisely, repeat step (32).

[0060] (33) Judgment of the legitimacy of visible arc segments

[0061] Get t in front ds , t de After that, it is necessary to determine whether the duration meets the minimum transmission duration of the dedicated station, that is, to determine whether

[0062] (t de -t ds ) <transtmin

[0063] Is it satisfied? If so, keep the segment; otherwise, discard the segment.

[0064] S4, visible interval telemetry downlink.

[0065] When the dedicated station data transmission and measurement and control integrated station flag flgTMDT is judged to be TRUE, the mission planning results and the dedicated station visible arc segment telemetry transmission are arranged to be transmitted downward, so that the ground can know the on-board autonomous mission planning results and the planned time of the dedicated station transmission.

[0066] S5. The visible interval data is transmitted.

[0067] When the onboard time enters the visible arc segment [t_ds, t_de] of the dedicated station, the data file to be played back in the window is planned according to the data playback strategy and the data type datatype of the dedicated station.

[0068] The contents not described in detail in the specification of the present invention belong to the common knowledge of those skilled in the art.

[0069] Although the present invention has been disclosed as above in the form of a preferred embodiment, it is not intended to limit the present invention. Any person skilled in the art may make possible changes and modifications to the technical solution of the present invention by using the methods and technical contents disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and modifications made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solution of the present invention shall fall within the protection scope of the technical solution of the present invention.

Claims

1. A method for autonomous on-board planning of a playback mission based on a dedicated data transmission station, characterized in that: include: S1. Bind data according to the actual situation of the data transmission dedicated station; S2, based on the station addresses bound in S1, roughly search and output the visible arc segment of the satellite to the dedicated station; S3, according to the station addresses bound in S1 and the visible arc segments of the satellite to the dedicated station output by the rough search, a fine search is performed to output the visible arc segments of the satellite to the dedicated station; S4, according to the S3 precise search output satellite to the dedicated station visible arc segment, arrange the task planning results to be transmitted; S5. Arrange the on-board data playback based on the satellite's visible arc segment to the dedicated station output by precise search in S3.

2. The on-board autonomous planning method for replay missions according to claim 1, characterized in that: In S1, binding is performed according to the actual situation of each dedicated station, and the dedicated station SpecStation parameters are expressed as: SpecStation={name,LLA[3],Mu[360],transtmin,datatype,flgTMDT}; Where name is the name of the dedicated station; LLA[3] is the longitude, latitude and altitude of the dedicated station site; Mu[360] is the ground shielding angle array of the dedicated station, taking the east direction as zero, and defining the minimum elevation angle with data transmission capability in the corresponding direction of the data transmission station in a counterclockwise direction at intervals of 1 degree; transtmin is the shortest transmission time of the dedicated station; datatype is the playback data type selection of the dedicated station; flgTMDT is the flag of whether the dedicated station is a digital transmission and measurement and control integrated station.

3. The on-board autonomous planning method for replay missions according to claim 1, characterized in that: In S2, the search step length mdt_SearchStep is set, the maximum number of searches N1 is calculated according to the planning cycle, and the position vector of the dedicated ground station is calculated according to the longitude, latitude and altitude of the dedicated ground station. Determine the minimum value θ of the dedicated station ground shielding angle array d,min ; According to the satellite's orbital parameters, take the planned start time as the search starting point t0 and calculate t k =t0+k*mdt_SearchStep(k=0,1,2,…,N) corresponding to the satellite position vector Then calculate the vector from the ground station to the spacecraft According to the definition, At this time, the elevation angle of the ground station pointing to the spacecraft is After traversal search, if μ is found k-1 Less than θ d,min , and μ k Greater than or equal to θ d,min , then the time tk is the entry time, recorded as t ds0 ; If μ is found k-1 Greater than or equal to θ d,min , and μ k Less than θ d,min , then at this time t k is the time of going out, recorded as t de0 .

4. The on-board autonomous planning method for replay missions according to claim 1, characterized in that: For the visible arc segment [t ds0 ,t de0 ], S3 specifically includes: (31) Search entry time t ds ; (32) Search for time t de ; (33) Get t in front ds , t de After that, it is necessary to determine whether the duration meets the minimum transmission duration of the dedicated station, that is, to determine whether (t de -t ds )<transtmin Is it satisfied? If so, keep the segment; otherwise, discard the segment.

5. The on-board autonomous planning method for replaying missions according to claim 4, characterized in that: In step (31), let t ds =t ds0 , calculate the spacecraft's position vector at this time Calculate the vector from the ground station to the spacecraft The elevation angle of the spacecraft can be calculated Azimuth of the spacecraft Wherein, if α<0, α=α+360; α=Round(α), Round() represents the rounding function; if α>359, α=0; According to the azimuth angle α, find S1 and the dedicated station ground shielding angle array Mu[360] configured in the data transmission dedicated station initialization step, and obtain the azimuth angle θ d,α , if μ i >θ d,α , then find the entry time t ds Exit the traversal; otherwise, let t ds =t ds +mdt μ ;mdt μ To calculate the search step size more precisely, repeat step (31).

6. The on-board autonomous planning method for replaying missions according to claim 5, characterized in that: In step (32), let t de =t de0 , calculate the spacecraft's position vector at this time Calculate the vector from the ground station to the spacecraft The elevation angle of the spacecraft can be calculated Azimuth of the spacecraft Wherein, if α<0, α=α+360; α=Round(α), Round() represents the rounding function; if α>359, α=0; According to the azimuth angle α, look up the table S1 and the dedicated station ground shielding angle array Mu[360] configured in the data transmission dedicated station initialization step to obtain the azimuth angle θ d,α , if μ i >θ d,α , then find the exit time t de Exit the traversal; otherwise, let t de =t de -mdt μ ;mdt μ To calculate the search step size more precisely, repeat step (32).

7. The on-board autonomous planning method for replaying missions according to claim 1, characterized in that: In S4, when it is determined that the dedicated station data transmission and measurement and control integrated station flag flgTMDT is TRUE, the mission planning results and the dedicated station visible arc segment telemetry transmission are arranged to be transmitted downward, so that the ground can know the on-board autonomous mission planning results and the planned time of the dedicated station transmission.

8. An electronic device comprising: processor; as well as a memory for storing computer program instructions; When the computer program instructions are loaded and executed by the processor, the processor performs the method according to any one of claims 1 to 7.

9. A computer-readable storage medium having computer program instructions stored thereon, wherein when the computer program instructions are loaded and executed by a processor, the processor is caused to execute the method according to any one of claims 1 to 7.

10. A computer program product stored on a non-transitory computer readable medium, the computer program product comprising a program code for carrying out the method according to any one of claims 1 to 7.

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