Method and system for implementing exo-planet blocking TT&C plan under deep space large delay working condition

Abstract

This invention relates to the field of aerospace telemetry and control technology, specifically disclosing a method and system for implementing telemetry and control plans under deep-space conditions with large time delays due to extraterrestrial celestial body obstruction. This invention determines the time window for extraterrestrial celestial body obstruction and the available ground tracking stations by utilizing precise orbital data from the probe. It calculates the station forecast including data truncation and the one-way optical travel time of uplink and downlink signal transmission. Based on the one-way optical travel time, it pre-sets uplink tracking events and delays downlink tracking events. It merges adjacent telemetry and control arcs with time intervals less than a preset threshold into a single-station continuous tracking arc to set mission preparation events. In deep-space telemetry and control mode, it decouples the uplink and downlink, and controls the transmission of uplink carriers and remote control commands based on the one-way optical travel time. This solves the technical problems of difficult space-ground coordination and poor timeliness of emergency resending during extraterrestrial celestial body obstruction under deep-space conditions with large time delays, improving the reliability and timeliness of deep-space exploration mission telemetry and control plans.

Description

Technical Field

[0001] This invention relates to the field of aerospace telemetry and control technology, and in particular to a method and system for implementing telemetry and control plans for extraterrestrial celestial body obstruction under deep space conditions with large time delay. Background Technology

[0002] With the continuous development of the space program, the first Mars exploration mission has become a significant milestone for spacecraft entering the field of deep space exploration. The boundary of deep space is 2×10⁻⁶ kilometers from Earth. 6 Space beyond 2 million kilometers, while the Moon, at approximately 400,000 kilometers from Earth, remains in near-Earth space. In stark contrast, the farthest distance between Earth and Mars is approximately 400 million kilometers. This means that the distance between the spacecraft and Earth has increased from approximately 400,000 kilometers in the Earth-Moon space to approximately 400 million kilometers in the Earth-Mars space, marking the first truly deep-space exploration mission. This dramatic increase in distance directly leads to a sharp increase in communication transmission latency, with round-trip transmission delays reaching up to approximately 44 minutes, posing a severe challenge to traditional flight control methods.

[0003] In traditional near-Earth spacecraft and lunar probe flight control missions, due to the close proximity between the spacecraft and ground stations, the time delay from the time the ground sends remote control commands or injects data to the time the onboard commands are received and telemetry is applied to determine the status changes. Under these conditions, ground control personnel can promptly monitor and interpret the onboard status using downlink telemetry data, forming a relatively timely control loop and ensuring the safe execution of the flight control mission.

[0004] However, in Mars exploration missions, the vast distance between the spacecraft and the ground results in significant time delays in telemetry and control communications. From the perspective of downlink telemetry data status interpretation, the telemetry data received by the ground reflects the spacecraft's status up to one-way optical travel time (approximately 22 minutes). This means that ground status monitoring and interpretation has a certain lag, especially in cases of spacecraft status anomalies, which are difficult to detect immediately. From the perspective of uplink remote control and data injection implementation, it can take up to 44 minutes from the issuance of a ground remote control command to its arrival at the spacecraft and the subsequent telemetry return of status changes after execution. The ground cannot immediately know the status of command reception and execution on the spacecraft. In cases of abnormal remote control command reception or execution, ground retransmission requires at least two-way optical travel time (approximately 44 minutes), resulting in poor timeliness of emergency retransmission in cases of uplink remote control command anomalies. From the perspective of flight control implementation, the extremely large transmission delay has a significant impact on orbit prediction calculations, station tracking and guidance, telemetry and control plan design, remote control command correction, telemetry status interpretation, and emergency response.

[0005] Especially during the Mars orbiter's orbiting phase, the mission faces even more complex challenges. On one hand, because both Mars and Earth revolve around the Sun, the distance between them varies periodically, resulting in a one-way time delay of approximately 4.5 to 21.9 minutes between the orbiter and Earth during the orbiting phase—a typical case of extremely large time delay. On the other hand, the Mars orbiter periodically enters regions where tracking and control are obstructed by the far side of Mars, fundamentally altering the tracking and control obstruction under these large time delay conditions compared to traditional lunar tracking and control obstruction. Therefore, it is necessary to solve the challenges of coordinating space-ground tracking and control with the mission while mitigating the large time delay. Summary of the Invention

[0006] To address the aforementioned technical problems, this invention provides a method and system for implementing a monitoring and control plan for extraterrestrial celestial body obstruction under deep space conditions with large time delays.

[0007] Firstly, the present invention provides a method for implementing a tracking and control plan for extraterrestrial celestial body obstruction under deep space conditions with large time delays. The technical solution of this method is as follows: Using precise orbital data from probes orbiting extraterrestrial objects, we can determine the time window for extraterrestrial object obscuring and the available ground-based tracking stations before and after the obscuring. Based on the site coordinates of the available ground tracking stations, the precise orbit data of the probe, and the ephemeris data of extraterrestrial objects and Earth, the station forecast of the available ground tracking stations within the time window of the extraterrestrial object obscuring the Earth is calculated, and the station forecast includes data truncation caused by the extraterrestrial object obscuring the Earth. Based on the distance between the detector and the ground station predicted by the station, calculate the unidirectional optical travel time of uplink and downlink signal transmission; Based on the principle that the uplink event precedes the unidirectional optical travel time of the uplink and downlink signal transmissions and the downlink event lags behind the unidirectional optical travel time of the uplink and downlink signal transmissions, the station tracking event is set according to the station forecast. For the data truncation, adjacent telemetry and control arc segments with a time interval less than a preset threshold are merged into a single-station continuous tracking arc segment, and a station task preparation event is set according to the single-station continuous tracking arc segment. In deep space telemetry and control mode, the uplink telemetry and control link is decoupled from the downlink telemetry and control link. When the uplink and downlink signals are transmitted in one direction, the uplink carrier is controlled to be sent when the station is geometrically visible and reaches a preset elevation angle. After the uplink carrier is sent, the uplink remote control command is controlled to be sent.

[0008] The beneficial effects of the present invention regarding the implementation method of extraterrestrial body obstruction measurement and control plan under deep space long time delay conditions are as follows: The method of this invention determines the time window for extraterrestrial celestial body obstruction and the available ground tracking stations by utilizing precise orbital data from the detector. It calculates the station forecast including data truncation and the one-way optical travel time of uplink and downlink signal transmission. Based on the one-way optical travel time, it pre-sets uplink tracking events and delays downlink tracking events. It merges adjacent telemetry and control arcs with time intervals less than a preset threshold into a single-station continuous tracking arc to set mission preparation events. In deep space telemetry and control mode, it decouples the uplink and downlink and controls the transmission of uplink carriers and remote control commands according to the one-way optical travel time. This solves the technical problems of difficult space-ground coordination and poor timeliness of emergency resending during extraterrestrial celestial body obstruction under deep space conditions with large time delays, and improves the reliability and timeliness of deep space exploration mission telemetry and control plan implementation.

[0009] Based on the above scheme, the method for implementing the telemetry and control plan for extraterrestrial celestial body obstruction under the deep space long time delay condition of the present invention can be further improved as follows.

[0010] In one alternative approach, the steps of determining the time window of extraterrestrial object obscuration and the available ground-based tracking stations before and after the obscuration, using precise orbital data from a probe orbiting an extraterrestrial object, include: Based on the precise orbital data of the probe, the times when the probe enters and exits the extraterrestrial body's obscuring region during its flight around the extraterrestrial body are calculated, and the time window for the extraterrestrial body's obscuring is determined. Based on the time window of the extraterrestrial object obscuring the Earth, the ephemeris data of the extraterrestrial object and Earth, and the coordinates of the ground stations, the measurement and control conditions of the ground stations before and after the time window of the extraterrestrial object obscuring the Earth are analyzed to determine the ground stations that are geometrically visible to the detector. Based on the availability of ground-based deep space station network resources and station tracking priorities, the available ground-based tracking stations that are geometrically visible to the probe are selected to participate in tracking before and after extraterrestrial celestial bodies are obscured.

[0011] The advantages of adopting the above-mentioned optional methods are as follows: further accurately determine the occlusion time window through precise orbit data, filter geometrically visible stations by combining ephemeris data and station coordinates, and determine available tracking stations based on resource availability and priority, thereby improving the accuracy of station selection and the rationality of resource utilization before and after occlusion.

[0012] In one optional approach, the step of calculating the station forecast of the available ground-based tracking station within the time window of the extraterrestrial object obscuring the Earth, based on the site coordinates of the available ground-based tracking station, the precise orbit data of the probe, and the ephemeris data of the extraterrestrial object and Earth, includes: Based on the site coordinates of the available ground tracking stations, the precise orbit data of the probe, and the ephemeris data of the extraterrestrial objects and the Earth, the geometric visibility of the available ground tracking stations relative to the probe is calculated within the time window of the extraterrestrial object obscuring the probe. Based on the geometric visibility and the geometric occlusion relationship of the extraterrestrial object on the detector, the tracking arc segment of the available ground tracking stations within the time window of the extraterrestrial object occlusion is calculated. The tracking arc segment is divided by the extraterrestrial object occlusion event into station prediction before entering the extraterrestrial object occlusion and station prediction after exiting the extraterrestrial object occlusion. The station forecasts before the extraterrestrial object enters the Earth's atmosphere and after the extraterrestrial object exits the Earth's atmosphere are used as the station forecasts of the available ground tracking stations within the time window of the extraterrestrial object's atmosphere obscuring the Earth's atmosphere. The station forecasts include the data truncation caused by the extraterrestrial object's obscuring the Earth's atmosphere.

[0013] The beneficial effects of adopting the above-mentioned optional methods are as follows: by further calculating geometric visibility and geometric occlusion relationships, station tracking arc forecasts containing data truncation are generated, and the tracking arcs before and after the occlusion event are integrated into a complete forecast, thereby improving the continuity and completeness of station forecasts during the occlusion period.

[0014] In one alternative approach, the step of calculating the unidirectional optical travel time of uplink and downlink signal transmission based on the distance between the detector and the ground station predicted by the station includes: Extract the probe's position data at each moment within the time window of the extraterrestrial object's obscuring, as well as the ground station position data of the available ground tracking stations, from the station's forecast. Based on the detector location data and the ground station location data, calculate the instantaneous straight-line distance between the detector and the available ground tracking station at each moment; Based on the instantaneous straight-line distance and the speed of light constant at each moment, the unidirectional optical travel time of uplink and downlink signal transmission between the detector and the available ground tracking station at each moment is calculated.

[0015] The advantages of adopting the above-mentioned optional method are: by further extracting the position data of the detector and the ground station to calculate the instantaneous straight-line distance, and combining the light speed constant to accurately calculate the unidirectional optical travel time of uplink and downlink signal transmission, a precise time reference is provided for setting subsequent tracking events.

[0016] In one alternative approach, following the principle that uplink events precede the one-way optical travel time of uplink and downlink signal transmission and downlink events lag behind the one-way optical travel time of uplink and downlink signal transmission, the steps for setting station tracking events based on the station forecast include: Based on the forecast from the monitoring station, determine the entry time of the probe into the extraterrestrial celestial body obscuring region and the exit time from the extraterrestrial celestial body obscuring region; Based on the time of entry into the blockage, the time of exit from the blockage, and the unidirectional optical travel time of uplink and downlink signal transmission between the detector and the available ground tracking station at each time, calculate the time when the detector last transmits the uplink carrier on the ground before entering the blockage, the time when the detector stops receiving downlink telemetry on the ground after entering the blockage, the time when the detector transmits the uplink carrier again on the ground before exiting the blockage, and the time when the detector resumes receiving downlink telemetry on the ground after exiting the blockage. Based on the last uplink carrier transmission time, the downlink telemetry reception termination time, the next uplink carrier transmission time, and the downlink telemetry reception recovery time, and combined with the station tracking arc in the station forecast, the station tracking event containing the uplink event time and the downlink event time is set.

[0017] The advantages of adopting the above optional method are: by further calculating the uplink and downlink carrier transmission and telemetry reception times before and after the entry and exit of the blockage by using the entry and exit of the blockage time, the exit of the blockage time, and the unidirectional optical travel time, and by combining the tracking arc setting with the tracking event including the uplink and downlink event times, the accuracy of the tracking event setting during the blockage period is improved.

[0018] In one alternative approach, for the data truncation, the steps of merging adjacent telemetry and control arc segments with time intervals less than a preset threshold into a single-station continuous tracking arc segment, and setting a station task preparation event based on the single-station continuous tracking arc segment, include: Based on the data truncation in the station forecast, identify the adjacent tracking arc segments of the ground-based available tracking stations within the time window of the extraterrestrial body occlusion event; Calculate the time interval between the departure time of the previous measurement and control arc segment and the arrival time of the next measurement and control arc segment in the adjacent measurement and control arc segments; Determine whether the time interval is less than the preset threshold, and merge adjacent measurement and control arc segments that are less than the preset threshold into a single-station continuous tracking arc segment; Based on the single-station continuous tracking arc segment, set the entry time into the single-station continuous tracking arc segment and the exit time from the single-station continuous tracking arc segment; Based on the continuous tracking arc time of the incoming single station and the continuous tracking arc time of the outgoing single station, the station mission preparation event of the available ground tracking stations is set.

[0019] The advantages of adopting the above optional method are as follows: by further identifying adjacent measurement and control arc segments that are segmented by occlusion and calculating the time interval, arc segments with an interval less than the threshold are merged into single-station continuous tracking arc segments. Based on this, task preparation events are set, reducing frequent entry and exit operations and improving the continuity of station task preparation.

[0020] In one alternative approach, under deep space telemetry and control mode, the uplink telemetry and control link is decoupled from the downlink telemetry and control link. Based on the unidirectional optical transmission of the uplink and downlink signals, when the station is geometrically visible and reaches a preset elevation angle, the uplink carrier is controlled to be transmitted. After transmitting the uplink carrier, the uplink remote control command is controlled to be transmitted. This includes the following steps: Based on the forecast from the monitoring station, determine the starting time when the ground-based available tracking station becomes geometrically visible to the detector and reaches the preset elevation angle; In deep space telemetry and control mode, the uplink telemetry and control link is decoupled from the downlink telemetry and control link, and the ground-based available tracking stations are controlled to send uplink carriers at the starting moment; After sending the uplink carrier, after a preset carrier hold time, the ground-based available tracking station is controlled to send uplink remote control commands; Based on the unidirectional optical transmission of the uplink and downlink signals, determine the arrival time of the uplink remote control command to the detector and the arrival time of the downlink telemetry to the available ground tracking station after the detector executes the command. Without waiting for the telemetry arrival time, based on the station tracking event and the station mission preparation event, the available ground tracking stations are controlled to continue executing subsequent uplink and downlink events.

[0021] The advantages of adopting the above-mentioned optional method are as follows: by further decoupling the uplink and downlink and sending uplink carrier and remote control commands at the geometrically visible start time, the arrival time of commands and telemetry arrival time are determined based on the unidirectional optical travel time, and subsequent events are continued to be executed without waiting for telemetry returns, thereby improving the efficiency of telemetry and control command issuance under the condition of large time delay in deep space.

[0022] Secondly, this invention provides a system for implementing a monitoring and control plan for extraterrestrial celestial body obstruction under deep space conditions with large time delays. The technical solution of this system is as follows: The determination module is used to determine the time window of the extraterrestrial object's obscuration and the available ground tracking stations before and after the obscuration, based on the precise orbital data of the probe flying around the extraterrestrial object. The processing module is used to calculate the station forecast of the ground-based available tracking station within the time window of the extraterrestrial object occlusion based on the station coordinates of the available ground-based tracking station, the precise orbit data of the probe, and the ephemeris data of the extraterrestrial object and the Earth. The station forecast includes data truncation caused by the extraterrestrial object occlusion. The calculation module is used to calculate the unidirectional optical travel time of uplink and downlink signal transmission based on the distance between the detector and the ground station in the station forecast. The setting module is used to set the station tracking event according to the station forecast, based on the principle that the uplink event precedes the unidirectional optical transmission time of the uplink and downlink signals and the downlink event lags behind the unidirectional optical transmission time of the uplink and downlink signals. The generation module is used to truncate the data, merge adjacent telemetry and control arc segments with a time interval less than a preset threshold into a single-station continuous tracking arc segment, and set a station task preparation event according to the single-station continuous tracking arc segment. The control module is used to decouple the uplink and downlink telemetry and control links in deep space telemetry and control mode. When the uplink and downlink signals are transmitted in one direction, the module controls the transmission of the uplink carrier when the station is geometrically visible and reaches a preset elevation angle. After the uplink carrier is transmitted, the module controls the transmission of the uplink remote control command.

[0023] The beneficial effects of the system for implementing a deep-space long-time-delay monitoring and control plan for extraterrestrial celestial body obstruction under the present invention are as follows: The system of this invention determines the time window for extraterrestrial celestial body obstruction and the available ground tracking stations by utilizing precise orbital data from the detector. It calculates the station forecast including data truncation and the one-way optical travel time of uplink and downlink signal transmission. Based on the one-way optical travel time, it pre-sets uplink tracking events and delays downlink tracking events. It merges adjacent tracking arcs with time intervals less than a preset threshold into a single-station continuous tracking arc to set mission preparation events. In deep space tracking and control mode, it decouples the uplink and downlink and controls the transmission of uplink carriers and remote control commands according to the one-way optical travel time. This solves the technical problems of difficult space-ground coordination and poor timeliness of emergency resending during extraterrestrial celestial body obstruction under deep space conditions with large time delays, and improves the reliability and timeliness of deep space exploration mission tracking and control plans.

[0024] Thirdly, the technical solution of an electronic device according to the present invention is as follows: It includes a memory, a processor, and a program stored in the memory and running on the processor. When the processor executes the program, it implements the steps of the method for implementing the deep space long time delay operation condition extraterrestrial body occlusion measurement and control plan as described in this invention.

[0025] Fourthly, the technical solution of a computer-readable storage medium provided by the present invention is as follows: The computer-readable storage medium stores instructions that, when read by the computer-readable storage medium, cause the computer-readable storage medium to execute the steps of the method for implementing the telemetry and control plan for extraterrestrial celestial body obstruction under the deep space long time delay condition of the present invention.

[0026] The above description is merely an overview of the technical solution of the present invention. In order to better understand the technical means of the present invention and to implement it in accordance with the contents of the specification, and in order to make the above and other objects, features and advantages of the present invention more apparent and understandable, specific embodiments of the present invention are described below. Attached Figure Description

[0027] The accompanying drawings are for illustrative purposes only and are not intended to limit the invention. Furthermore, the same reference numerals denote the same parts throughout the drawings. In the drawings: Figure 1 This is a flowchart illustrating an embodiment of a method for implementing a telemetry and control plan for extraterrestrial celestial body obstruction under deep space long-delay conditions according to the present invention. Figure 2 A schematic diagram illustrating the process of determining tracking stations before and after extraterrestrial object obstruction; Figure 3 This is a schematic diagram illustrating the obstruction effect of extraterrestrial objects on deep space probes orbiting them. Figure 4 This is a schematic diagram illustrating the obstruction effect of extraterrestrial objects on deep space probes under conditions of large time delay in deep space. Figure 5 A schematic diagram illustrating the advance arrangement of uplink and the delayed arrangement of downlink events before and after the obscuring of extraterrestrial objects; Figure 6 A schematic diagram of single-station continuous tracking arc segment processing before and after extraterrestrial object obstruction; Figure 7 This is a schematic diagram of the space-ground collaborative workflow in deep space tracking and control mode. Figure 8 A schematic diagram illustrating the principle of the system for implementing the telemetry and control plan for extraterrestrial celestial body obstruction under deep space conditions with large time delays. Figure 9 This is a schematic diagram of an embodiment of a system for implementing a deep-space long-delay telemetry and control plan for extraterrestrial celestial body obstruction under the present invention. Figure 10 This is a schematic diagram of an embodiment of an electronic device according to the present invention. Detailed Implementation

[0028] Exemplary embodiments of the invention will now be described in more detail with reference to the accompanying drawings. While exemplary embodiments of the invention are shown in the drawings, it should be understood that the invention can be implemented in various forms and should not be limited to the embodiments set forth herein.

[0029] Figure 1This diagram illustrates a flowchart of an embodiment of a method for implementing a deep-space, long-time-delay extraterrestrial body obstruction tracking and control plan, as provided by the present invention. This method can be executed by electronic devices such as terminal devices or servers. The terminal device can be any fixed or mobile terminal, such as user equipment (UE), mobile device, user terminal, terminal, cellular phone, cordless phone, personal digital assistant (PDA), handheld device, computing device, vehicle-mounted device, or wearable device. The server can be a single server or a server cluster composed of multiple servers. Any electronic device can implement the deep-space, long-time-delay extraterrestrial body obstruction tracking and control plan by having its processor call computer-readable instructions stored in its memory. Figure 1 As shown, it includes the following steps: S1. Using precise orbital data from probes orbiting extraterrestrial objects, determine the time window for extraterrestrial object obscuring and the available ground tracking stations before and after the obscuring.

[0030] Extraterrestrial object flight refers to the orbital motion of a probe around an extraterrestrial object. For example, probe B orbits celestial body A along a predetermined orbit. Precise orbital data refers to time-series data describing the probe's precise position and velocity in space. For example, the precise orbital data of probe B includes its position coordinates (X=3400km, Y=-1250km, Z=520km) and velocity vectors (Vx=3.2km / s, Vy=-1.5km / s, Vz=0.8km / s) in the fixed coordinate system of celestial body A at 10:00:00 (UTC) on January 1, 2026.

[0031] The "extraterrestrial object obscuring time window" refers to the period from the moment a probe enters the area behind an extraterrestrial object, causing radio signals between the probe and ground stations to be blocked by the object itself. For example, based on the orbital data of probe B, it is predicted that probe B will enter the area behind object A between 10:15:00 and 10:45:00 on January 1, 2026, during which direct communication with the ground will be impossible. This period is the obscuring time window of object A. The "before and after the extraterrestrial object obscuring time window" refers to the period before the probe enters the obscuring region and after it exits the obscuring region, used for scheduling tracking and control tasks. For example, ground stations can track probe B for 30 minutes before and after the obscuring time window of object A (10:15:00 to 10:45:00).

[0032] Among them, a ground-based available tracking station refers to a station that can be seen from the ground and whose equipment is in normal working order at the moment when an extraterrestrial object obscures the probe. For example, for probe B, during the time window when object A obscures the probe, station C cannot communicate due to the obscuration of object A, but stations D and E are geometrically visible and their equipment is usable. Therefore, stations D and E are ground-based available tracking stations.

[0033] S2. Based on the site coordinates of the available ground tracking stations, the precise orbit data of the probe, and the ephemeris data of extraterrestrial objects and Earth, calculate the station forecast of the available ground tracking stations within the time window of the extraterrestrial object obscuring the Earth. The station forecast includes data truncation caused by the extraterrestrial object obscuring the Earth.

[0034] Among these, station coordinates refer to the geographical location, latitude, longitude, and elevation data of the ground station. For example, the station coordinates of station D are 130.77 degrees east longitude, 46.48 degrees north latitude, and an altitude of 142 meters. Ephemeris data refers to a table of parameters describing the position and motion of celestial bodies (such as Earth and celestial body A) in space over time. For example, the ephemeris data for Earth and celestial body A on January 1, 2026, can be obtained from standard ephemeris files and used to calculate their relative positions. Station forecasts refer to a list of time arcs during which the station is visible to the probe, calculated based on the probe's orbit, celestial ephemeris data, and station coordinates. For example, for probe B, the station forecast for station D shows visibility from 10:00:00 to 10:14:30 and from 10:45:30 to 11:30:00, with an interruption due to obstruction by celestial body A.

[0035] Data truncation refers to the phenomenon where, during the period of celestial obscuration, a previously continuous tracking arc in a station's forecast is split into two segments by the obscuration event. For example, if station D's forecast has no data between 10:14:30 and 10:45:30 due to celestial body A obscuring the data, the forecast data will be truncated into two segments.

[0036] S3. Calculate the unidirectional optical travel time of uplink and downlink signal transmission based on the distance between the detector and the ground station predicted by the station.

[0037] In this context, "probe" refers to a spacecraft performing deep space exploration missions, such as orbiters and landers. For example, probe B is an orbiter orbiting celestial body A. "Ground station" refers to a facility located on Earth used for radio communication with the probe, including antennas, transmitters, and receivers. For example, station D is a ground station with an antenna of 66m in diameter. "One-way optical travel time" for uplink and downlink signal transmission refers to the one-way time required for a radio signal to travel from the ground station to the probe (uplink) or from the probe to the ground station (downlink). For example, when probe B is 3 × 10⁻⁶ meters from Earth... 8 At km, the unidirectional light travel time Δt is approximately 1000 s.

[0038] S4. In accordance with the principle that the uplink event precedes the unidirectional optical transmission time of the uplink and downlink signals and the downlink event lags behind the unidirectional optical transmission time of the uplink and downlink signals, set the station tracking event based on the station forecast.

[0039] Among them, station tracking events refer to the actions or operations that a ground station needs to perform during the tracking of a detector, such as starting to transmit a carrier wave, stopping to transmit a carrier wave, and starting to receive telemetry data. For example, if station D plans to start transmitting an uplink carrier wave at 10:00:00, stop transmitting at 10:14:30, and start transmitting again at 10:45:30, these are all considered station tracking events.

[0040] S5. For the data truncation, adjacent measurement and control arc segments with a time interval less than a preset threshold are merged into a single-station continuous tracking arc segment, and a station task preparation event is set according to the single-station continuous tracking arc segment.

[0041] The preset threshold refers to a pre-defined time interval value used to determine whether two adjacent tracking arc segments need to be merged into a continuous tracking arc segment. For example, if the preset threshold is set to 30 minutes, two arc segments with an interval of less than 30 minutes are considered as the same continuous arc segment. Adjacent tracking arc segments refer to two visible arc segments that are consecutive in time when the same station tracks the same detector. For example, the tracking arc segments of station D for detector B are divided into 10:00:00 to 10:14:30 and 10:45:30 to 11:30:00; these two arc segments are adjacent tracking arc segments. A single-station continuous tracking arc segment refers to a complete tracking arc segment formed by merging adjacent tracking arc segments with an interval of less than the preset threshold. During this period, the station can perform one continuous task preparation. For example, if the interval between two arc segments of station D is 30 minutes, and the preset threshold is 40 minutes, they are merged into a single-station continuous tracking arc segment from 10:00:00 to 11:30:00.

[0042] Among them, the station mission preparation events refer to a series of preparatory work that the ground station needs to perform before starting to track the detector, such as powering on the equipment, switching on the channel, and sending guidance data. For example, at the start time of the single-station continuous tracking arc at 10:00:00, station D needs to perform mission preparation events such as powering on, opening the channel, and sending guidance data.

[0043] S6. In deep space telemetry and control mode, decouple the uplink telemetry and control link from the downlink telemetry and control link. When the uplink and downlink signal transmission is unidirectional optical, control the transmission of the uplink carrier when the station is geometrically visible and reaches a preset elevation angle. After transmitting the uplink carrier, control the transmission of the uplink remote control command.

[0044] The deep space telemetry and control mode refers to a telemetry and control operating mode designed to address the large latency characteristics of deep space communication. It allows the uplink and downlink telemetry and control links to operate independently, enabling uplink commands to be sent without waiting for bidirectional confirmation. For example, in deep space telemetry and control mode, station D sends uplink carrier waves and commands immediately after becoming geometrically visible, without waiting for downlink telemetry confirmation. The uplink telemetry and control link is the uplink communication channel from the ground station to the probe, sending commands and data. For example, station D sends remote control commands to probe B via the uplink telemetry and control link. The downlink telemetry and control link is the downlink communication channel from the probe to the ground station, sending telemetry and scientific data. For example, probe B sends status telemetry data to the ground transmitter via the downlink telemetry and control link. Geometric visibility of the station refers to the state where, from the ground station's perspective, the probe appears above the horizon and meets the minimum elevation angle requirement (usually 10 degrees). For example, when the elevation angle of station D to probe B reaches 10 degrees, the station is considered geometrically visible.

[0045] Uplink carrier refers to the unmodulated radio carrier signal transmitted by the ground station to the detector to establish a communication link. For example, station D starts transmitting uplink carrier at 10:00:00 so that detector B can lock onto the frequency. Uplink remote control command refers to the control command or injected data sent by the ground station to the detector through the uplink. For example, after transmitting uplink carrier, station D sends a "flywheel start" remote control command at 10:01:00.

[0046] The technical solution of this embodiment determines the time window for extraterrestrial celestial body obstruction and the available ground tracking stations by utilizing the precise orbital data of the detector. It calculates the station forecast including data truncation and the one-way optical travel time of uplink and downlink signal transmission. Based on the one-way optical travel time, it pre-sets uplink tracking events and delays downlink tracking events. It merges adjacent telemetry and control arcs with time intervals less than a preset threshold into a single-station continuous tracking arc to set mission preparation events. In deep space telemetry and control mode, it decouples the uplink and downlink and controls the transmission of uplink carriers and remote control commands according to the one-way optical travel time. This solves the technical problems of difficult space-ground coordination and poor timeliness of emergency resending during extraterrestrial celestial body obstruction under the condition of large time delay in deep space, and improves the reliability and timeliness of deep space exploration mission telemetry and control plan implementation.

[0047] In one alternative approach, S1 specifically includes: Based on the precise orbital data of the probe, the times when the probe enters and exits the extraterrestrial body's obscuring region during its flight around the extraterrestrial body are calculated, thus determining the extraterrestrial body's obscuring time window.

[0048] The moment of entering the region obscured by an extraterrestrial object refers to the instant when the probe moves to the back of the extraterrestrial object and communication between the ground and the probe is blocked by the object. For example, probe B enters the region obscured by the back of object A at 10:14:30, at which point communication between the ground and the probe is interrupted. The moment of exiting the region obscured by an extraterrestrial object refers to the instant when the probe moves from the back of the extraterrestrial object into the visible region and communication is restored. For example, probe B exits the region obscured by the back of object A at 10:45:30, and communication between the ground and the probe is restored.

[0049] Based on the time window of the extraterrestrial object obscuring the Earth, the ephemeris data of the extraterrestrial object and Earth, and the coordinates of the ground stations, the measurement and control conditions of the ground stations before and after the time window of the extraterrestrial object obscuring the Earth are analyzed to determine the ground stations that are geometrically visible to the detector.

[0050] The telemetry, tracking, and command (TT&C) condition analysis refers to the process of comprehensively considering factors such as the probe's orbit, celestial obstruction, and the distribution of tracking stations to assess the visibility and communication quality of the probe. For example, a TT&C condition analysis of probe B reveals that station C is invisible during obstruction, while station D is visible but at a low elevation angle. Ground tracking stations refer to all fixed or mobile stations on Earth used for space tracking and control. For example, the deep space tracking and control network includes three ground tracking stations: station C, station D, and station E.

[0051] Based on the availability of ground-based deep space station network resources and station tracking priorities, the available ground-based tracking stations that are geometrically visible to the probe are selected to participate in tracking before and after extraterrestrial celestial bodies are obscured.

[0052] The availability of ground-based deep space station resources refers to resource information such as equipment status, mission schedules, and communication windows of globally distributed deep space tracking and control stations. For example, on January 1, 2026, station C is unavailable due to equipment maintenance, while stations D and E are available. Station tracking priority refers to the order in which stations are used when multiple stations are available, determined by factors such as station capabilities and mission requirements. For example, for probe B, station C has the highest priority, followed by station D and then station E.

[0053] Among the above-mentioned optional methods, the occlusion time window can be further accurately determined by using precise orbital data, geometrically visible stations can be selected by combining ephemeris data and station coordinates, and available tracking stations can be determined based on resource availability and priority, thereby improving the accuracy of station selection and the rationality of resource utilization before and after occlusion.

[0054] In one alternative approach, S2 specifically includes: Based on the site coordinates of the available ground tracking stations, the precise orbit data of the probe, and the ephemeris data of the extraterrestrial object and Earth, the geometric visibility of the available ground tracking stations relative to the probe is calculated within the time window of the extraterrestrial object's obscuring effect.

[0055] Geometric visibility refers to the geometric conditions under which the probe is above the horizon and not obscured by celestial bodies, as observed from a ground station. For example, calculations show that station D is geometrically visible to probe B from 10:00 to 10:14 and from 10:45 to 11:30.

[0056] Based on the geometric visibility and the geometric occlusion relationship between the extraterrestrial object and the detector, the tracking arc segment of the available ground tracking stations within the time window of the extraterrestrial object occlusion is calculated. The tracking arc segment is divided by the extraterrestrial object occlusion event into station prediction before entering the extraterrestrial object occlusion and station prediction after exiting the extraterrestrial object occlusion.

[0057] In this context, geometric occlusion refers to the geometric condition where an extraterrestrial object blocks the line-of-sight between a ground station and a probe. For example, if celestial object A is located between probe B and Earth, it will block the communication signal. The tracking arc of a station refers to the period of continuous visibility of the probe from the ground station. For example, the tracking arc of station D for probe B is from 10:00:00 to 10:14:30 and from 10:45:30 to 11:30:00.

[0058] The term "pre-entry obstruction by an extraterrestrial object" refers to the station's prediction of the visible arc of the probe before it enters the obstruction zone. For example, the station's prediction before entering the obstruction zone of object A is 10:00:00 to 10:14:30. The term "post-exit obstruction by an extraterrestrial object" refers to the station's prediction of the visible arc of the probe after it exits the obstruction zone. For example, the station's prediction after exiting the obstruction zone of object A is 10:45:30 to 11:30:00.

[0059] The station forecasts before the extraterrestrial object enters the Earth's atmosphere and after the extraterrestrial object exits the Earth's atmosphere are used as the station forecasts of the available ground tracking stations within the time window of the extraterrestrial object's atmosphere obscuring the Earth's atmosphere. The station forecasts include the data truncation caused by the extraterrestrial object's obscuring the Earth's atmosphere.

[0060] In the above-mentioned optional methods, by further calculating geometric visibility and geometric occlusion relationship, a station tracking arc forecast containing data truncation is generated, and the tracking arcs before and after the occlusion event are integrated into a complete forecast, thereby improving the continuity and completeness of the station forecast during the occlusion period.

[0061] In one alternative approach, S3 specifically includes: Extract the probe's position data at various times within the time window of the extraterrestrial object's obscuring, as well as the ground station position data of the available ground tracking stations, from the station forecast.

[0062] The detector position data refers to the detector's three-dimensional spatial coordinates at a specific moment. For example, the position of detector B in the geocentric fixed coordinate system of celestial body A at 10:00:00 is (3390km, -1200km, 500km). The ground station position data refers to the ground station's three-dimensional spatial coordinates at a specific moment (usually converted to a geocentric fixed coordinate system). For example, the position of station D in the geocentric fixed coordinate system is (-2830km, 4680km, 3900km).

[0063] Based on the detector location data and the ground station location data, the instantaneous straight-line distance between the detector and the available ground tracking station at each moment is calculated.

[0064] The instantaneous straight-line distance refers to the spatial straight-line distance between the detector and the ground station at a specific moment. For example, at 10:00:00, the instantaneous straight-line distance between detector B and station D is 3.2 × 10⁻⁶. 8 m.

[0065] Based on the instantaneous straight-line distance and the speed of light constant at each moment, the unidirectional optical travel time of uplink and downlink signal transmission between the detector and the available ground tracking station at each moment is calculated.

[0066] The speed of light constant refers to the speed at which electromagnetic waves propagate in a vacuum, and is usually taken as 299,792,458 m / s.

[0067] In the above-mentioned optional methods, the instantaneous straight-line distance is further calculated by extracting the position data of the detector and the ground station, and the unidirectional optical travel time of uplink and downlink signal transmission is accurately calculated by combining the speed of light constant, so as to provide an accurate time reference for subsequent tracking events.

[0068] In one alternative approach, S4 specifically includes: Based on the forecast from the monitoring station, the entry time of the probe into the extraterrestrial celestial body obscuring region and the exit time from the extraterrestrial celestial body obscuring region are determined.

[0069] The entry time of obstruction refers to the moment when the probe enters the region obstructed by the extraterrestrial object. For example, the entry time TIS for probe B is 10:14:30. The exit time of obstruction refers to the moment when the probe exits the region obstructed by the extraterrestrial object. For example, the exit time TOS for probe B is 10:45:30.

[0070] Based on the time of entry into the obstruction, the time of exit from the obstruction, and the unidirectional optical travel time of uplink and downlink signal transmission between the detector and the available ground tracking station at each time, the following are calculated: the time when the detector last transmits an uplink carrier on the ground before entering the obstruction, the time when the detector stops receiving downlink telemetry on the ground after entering the obstruction, the time when the detector transmits an uplink carrier again on the ground before exiting the obstruction, and the time when the detector resumes receiving downlink telemetry on the ground after exiting the obstruction.

[0071] The last uplink carrier transmission time refers to the time when the ground station last transmitted the uplink carrier before the detector was blocked, ensuring that the carrier reached the detector before the blockage. For example, based on the unidirectional optical travel time Δt = 1000s for uplink and downlink signal transmission, the last uplink carrier transmission time is TIS - Δt, which is 10:14:30 minus 1000s, equaling 9:57:50. The downlink telemetry reception interruption time refers to the time when the ground station last received telemetry data due to the interruption of downlink telemetry signals caused by the blockage. For example, the downlink telemetry reception interruption time is TIS + Δt, which is 10:14:30 plus 1000s, equaling 10:31:20.

[0072] The retransmission time of the uplink carrier from the ground refers to the time when the ground station begins to retransmit the uplink carrier before the detector emerges from the obstruction, ensuring that the carrier reaches the detector as soon as the obstruction is resolved. For example, the retransmission time of the uplink carrier from the ground is TOS-Δt, which is 10:45:30 minus 1000s, equaling 10:28:50. The recovery time of downlink telemetry reception from the ground refers to the time when the ground station resumes receiving downlink telemetry data after the obstruction is resolved. For example, the recovery time of downlink telemetry reception from the ground is TOS+Δt, which is 10:45:30 plus 1000s, equaling 11:02:20.

[0073] Based on the last uplink carrier transmission time, the downlink telemetry reception termination time, the next uplink carrier transmission time, and the downlink telemetry reception recovery time, and combined with the station tracking arc in the station forecast, the station tracking event containing the uplink event time and the downlink event time is set.

[0074] Uplink event timestamps refer to the points in time when events related to uplink communication occur, such as transmitting a carrier wave or sending commands. For example, the uplink event timestamps for station D include 9:57:50 (the moment the last uplink carrier wave was transmitted from the ground) and 10:28:50 (the moment the uplink carrier wave was transmitted again from the ground). Downlink event timestamps refer to the points in time when events related to downlink communication occur, such as the start of telemetry reception or the cessation of reception. For example, the downlink event timestamps for station D include 10:31:20 (the moment downlink telemetry reception on the ground was terminated) and 11:02:20 (the moment downlink telemetry reception on the ground was resumed).

[0075] In the above-mentioned optional methods, the uplink and downlink carrier transmission and telemetry reception times before and after the entry and exit of the blockage are further calculated by using the entry and exit of the blockage time, the exit of the blockage time, and the unidirectional optical travel time. The tracking event is set in combination with the tracking arc setting to include the uplink and downlink event times, thereby improving the accuracy of the tracking event setting during the blockage period.

[0076] In one alternative approach, S5 specifically includes: Based on the data truncation in the forecast from the aforementioned station, the adjacent tracking arc segments of the ground-based available tracking stations are identified within the time window of the extraterrestrial object occlusion event.

[0077] Calculate the time interval between the departure time of the previous measurement and control arc segment and the arrival time of the next measurement and control arc segment in the adjacent measurement and control arc segments.

[0078] The preceding tracking arc segment refers to the earlier of two adjacent arc segments at the same station. For example, in the two arc segments of station D, 10:00:00 to 10:14:30 is the preceding tracking arc segment. The departure time refers to the time when the station finishes tracking an arc segment. For example, the departure time of the preceding tracking arc segment is 10:14:30.

[0079] The latter tracking and control arc segment refers to the later of two adjacent arc segments at the same station. For example, 10:45:30 to 11:30:00 is the latter tracking and control arc segment. The arrival time refers to the moment when the station begins tracking an arc segment. For example, the arrival time for the latter tracking and control arc segment is 10:45:30.

[0080] If the time interval is less than the preset threshold, adjacent tracking arc segments that are less than the preset threshold are merged into a single-station continuous tracking arc segment.

[0081] Based on the single-station continuous tracking arc segment, the entry time and exit time of the single-station continuous tracking arc segment are set.

[0082] The entry time of a single-station continuous tracking arc refers to the start time of that arc. For example, the entry time of the merged single-station continuous tracking arc is 10:00:00. The exit time of a single-station continuous tracking arc refers to the end time of that arc. For example, the exit time of the merged single-station continuous tracking arc is 11:30:00.

[0083] Based on the continuous tracking arc time of the incoming single station and the continuous tracking arc time of the outgoing single station, the station mission preparation event of the available ground tracking stations is set.

[0084] In the above-mentioned optional methods, by further identifying adjacent telemetry and control arc segments that are segmented by occlusion and calculating the time interval, arc segments with an interval less than a threshold are merged into single-station continuous tracking arc segments. Based on this, task preparation events are set to reduce frequent entry and exit operations and improve the continuity of station task preparation.

[0085] In one alternative approach, S6 specifically includes: Based on the forecast from the monitoring station, the starting time when the ground-based available tracking station becomes geometrically visible to the detector and reaches the preset elevation angle is determined.

[0086] The starting time refers to the initial time point at which the station becomes geometrically visible to the detector. For example, the starting time for station D to become geometrically visible to detector B and reach the preset elevation angle is 10:00:00.

[0087] In deep space telemetry and control mode, the uplink telemetry and control link is decoupled from the downlink telemetry and control link, and the ground-based available tracking stations are controlled to send uplink carriers at the starting moment.

[0088] After sending the uplink carrier, and after a preset carrier hold time, the ground-based available tracking station is controlled to send uplink remote control commands.

[0089] The carrier hold duration refers to the length of time that the ground station needs to continuously transmit after sending the uplink carrier to ensure that the detector locks onto the carrier. For example, in deep space telemetry and control mode, the carrier hold duration is set to 60 seconds, meaning that after sending the uplink carrier at 10:00:00, it needs to hold for 60 seconds.

[0090] Based on the unidirectional optical transmission of the uplink and downlink signals, the arrival time of the uplink remote control command arriving at the detector and the arrival time of the downlink telemetry reaching the available ground tracking station after the detector executes the command are determined.

[0091] The command arrival time refers to the time when the uplink remote control command arrives at the detector after propagating through the unidirectional optical travel time of the uplink and downlink signal transmission. For example, if an uplink remote control command is sent at 10:01:00, and the unidirectional optical travel time of the uplink and downlink signal transmission is Δt = 1000s, the command arrival time is 10:01:00 + 1000s, which equals 10:17:40. The telemetry arrival time refers to the time when the downlink telemetry signal arrives at the ground station after the detector executes the command, after propagating through the unidirectional optical travel time of the uplink and downlink signal transmission. For example, if the detector executes the command at 10:17:40, and the downlink telemetry signal arrives at the ground after 1000s, the telemetry arrival time is 10:34:20.

[0092] Without waiting for the telemetry arrival time, based on the station tracking event and the station mission preparation event, the available ground tracking stations are controlled to continue executing subsequent uplink and downlink events.

[0093] In this context, subsequent uplink and downlink events refer to the next uplink or downlink operation scheduled without waiting for the telemetry return of the current command in deep space telemetry and control mode. For example, after sending an uplink remote control command at 10:01:00, station D, without waiting for the telemetry to arrive at 10:34:20, continues to send the next uplink remote control command at 10:02:00, while simultaneously continuing to receive downlink data.

[0094] In the above-mentioned optional methods, the uplink and downlink are further decoupled and the uplink carrier and remote control command are sent at the geometrically visible start time. The arrival time of the command and the arrival time of the telemetry are determined based on the unidirectional optical travel time. Subsequent events are executed without waiting for the telemetry return, thereby improving the efficiency of telemetry and control command issuance under the condition of large time delay in deep space.

[0095] Regarding the technical solution of this embodiment, it should be noted that: like Figure 2 As shown, the process for determining tracking stations before and after extraterrestrial object obstruction includes the following steps: Based on the probe's precise orbit data and ground station coordinates, and using ephemeris data from both the extraterrestrial object and Earth, an analysis of ground tracking and control conditions before and after the obstruction is conducted. This analysis comprehensively considers factors such as the probe's orbit, extraterrestrial object obstruction, and station distribution, assessing the visibility of ground stations to the probe and communication quality. Based on the analysis results, a set of available stations that are geometrically visible to the probe before and after the extraterrestrial object obstruction is determined. Based on the availability of deep-space ground station network resources, the final list of available ground tracking stations participating in tracking before and after the extraterrestrial object obstruction is determined, and their tracking priorities are clarified. The availability of deep-space ground station network resources includes resource information such as equipment status, mission schedules, and communication windows of globally distributed deep-space tracking and control stations. Station tracking priority refers to the order in which multiple ground stations are used, determined based on factors such as station capabilities and mission requirements.

[0096] During the orbital flight of a probe around an extraterrestrial object, under certain orbital design conditions, the probe will periodically enter the area behind the extraterrestrial object, rendering it invisible to ground-based telemetry and control. Under conditions of large time delay, the telemetry and control obstruction effect of the extraterrestrial object will undergo a qualitative change, correspondingly posing new functional requirements that fundamentally alter the functions of the flight control mission system's planning software.

[0097] like Figure 3 As shown, extraterrestrial objects have an obstruction effect on deep space probes orbiting them. When a probe orbits an extraterrestrial object and the object is positioned between the probe and Earth, the object itself blocks the line-of-sight between the ground station and the probe, creating a geometric obstruction relationship.

[0098] When calculating tracking forecasts for ground-based deep space stations, in addition to considering the Earth's rotation and the revolutions of the Earth and extraterrestrial objects around the Sun, the geometric obstruction effects of extraterrestrial objects on the probe must also be taken into account. Under these circumstances, the calculated tracking forecasts will exhibit significant data truncation. In actual calculations, the forecast for the same ground station is divided into two segments: the first segment is the forecast before the extraterrestrial object obstructs the probe, and the second segment is the forecast after the extraterrestrial object obstructs the probe. Data truncation refers to the phenomenon where, during the period of extraterrestrial object obstruction, the originally continuous tracking arc in the tracking forecast is divided into two segments by the obstruction event.

[0099] like Figure 4 As shown, the signal transmission delay needs to be considered due to the obstruction effect of extraterrestrial objects under large time-delay conditions. Based on the straight-line distance *d* between the detector and the ground-based deep space station, the one-way optical travel time Δt for uplink and downlink signal transmission is calculated using the formula Δt = d / C, where C is the speed of light constant. In practice, since extraterrestrial objects are relatively far from Earth, the straight-line distance between the extraterrestrial object and Earth can be used to represent the straight-line distance between the detector and the ground-based deep space station.

[0100] Under conditions of large time delay, the implementation of telemetry and control (TT&C) plans for extraterrestrial object obstruction needs to fully consider the time delay effect. The main principle is to schedule uplink events in advance and downlink events in a delayed manner. Assume the one-way optical travel time of uplink and downlink signal transmission before and after the detector enters or exits the extraterrestrial object TT&C obstruction is Δt. For the downlink TT&C link, the time when the detector enters the extraterrestrial object TT&C obstruction is denoted as TIS, and the actual arrival time of the last telemetry frame before the obstruction time is TIS + Δt; the time when the detector exits the extraterrestrial object TT&C obstruction is denoted as TOS, and the actual arrival time of the first telemetry frame after the exit time is TOS + Δt. Therefore, downlink telemetry-related events in the station events should lag behind the one-way optical travel time of uplink and downlink signal transmission. Regarding the uplink telemetry and control link, the actual time when the uplink carrier received before the probe enters the extraterrestrial celestial body telemetry and control blockage is TIS-Δt; the actual time when the uplink carrier received immediately after the probe leaves the extraterrestrial celestial body telemetry and control blockage is TOS-Δt. Therefore, in the station event, the uplink remote control related events should be scheduled in advance for the unidirectional optical timing of uplink and downlink signal transmission.

[0101] like Figure 5 As shown, the events of the stations before and after the obscuration by extraterrestrial objects are set according to the principle of advance arrangement for uplink and delay arrangement for downlink. Figure 5 The document demonstrates key milestones such as the start of telemetry and control, obstruction by extraterrestrial objects, and the end of telemetry and control, as well as the time correspondence between events such as the start of uplink telemetry and control, the start of downlink telemetry and control, the end of uplink telemetry and control, and the end of downlink telemetry and control.

[0102] Due to the obstruction caused by extraterrestrial objects, the tracking forecasts calculated by ground stations are truncated. In actual calculations, continuous tracking arcs of the same ground station are divided into two segments: the first segment is the forecast before entering the obstruction phase, and the second segment is the forecast after exiting the obstruction phase. To address this, a single-station continuous tracking arc is defined in flight control implementation. If the time interval between adjacent tracking arcs of a ground station (the interval between the departure time of the previous tracking arc and the arrival time of the next tracking arc) is less than a preset threshold, it is considered to belong to the same single-station continuous arc. A ground station within the same single-station continuous tracking arc only performs one mission preparation operation, i.e., only one channel switching and guidance data transmission event is scheduled, avoiding frequent mission preparation operations by the ground station.

[0103] Single-station continuous tracking arc constraints are primarily used to schedule events constrained on relatively continuous tracking arcs of ground stations. The main application scenario is when the tracking arc of a single ground station is divided into several relatively continuous sub-arcs due to obstruction by the extraterrestrial body during its orbital flight phase. Deep space station entry-related events are scheduled only before the start of the first sub-arc of the single-station continuous tracking arc, and exit-related events are scheduled only after the end of the last sub-arc of the single-station continuous tracking arc. The corresponding feature points for single-station continuous tracking arc constraints include: the time TISCT for entering the entire single-station continuous tracking arc, the time TOSCT for exiting the entire single-station continuous tracking arc, the time TICT for each sub-arc of entering the single-station continuous tracking arc, and the time TOCT for each sub-arc of exiting the single-station continuous tracking arc.

[0104] like Figure 6 As shown, the single-station continuous tracking arc processing process before and after extraterrestrial object obstruction includes the following characteristic points. Ground control station A starts uplink carrier modulation at time TIC, stops uplink carrier transmission at time TIS-Δt, stops downlink telemetry reception at time TIS, resumes uplink carrier modulation at time TIS+Δt, resumes downlink telemetry reception at time TOS-Δt, and resumes downlink reception at time TOS. The figure illustrates the uplink and downlink telemetry timing coordination workflow of the ground control station entering and exiting the extraterrestrial object obstruction area, with the one-way signal transmission delay Δt reflected in multiple stages.

[0105] In the conventional mode, when the ground deep space station telemetry and control equipment starts scanning or directly sends uplink carriers at a station elevation angle of 10 degrees (calculated based on geometric visibility), after a one-way ground-to-ground transmission delay, the uplink carriers arrive at the detector and complete carrier lock. After another one-way ground-to-ground transmission delay, the ground determines that dual acquisition is complete by scanning back to zero or satellite lock information before sending uplink remote control commands and injecting data to the detector.

[0106] In deep space telemetry and control mode, considering the impact of optical travel time (one-way ground-to-device transmission delay), when the geometric elevation angle of the deep space station's observation probe is above 10 degrees, the ground telemetry and control equipment sends an uplink carrier. After the carrier hold-up time meets the probe's uplink carrier lock requirements, uplink remote control commands or injected data can begin to be sent. After the one-way ground-to-device transmission delay, the uplink carrier arrives at the probe first and completes carrier lock-up. Then, the uplink remote control commands or injected data arrive at the probe. After another one-way ground-to-device transmission delay, the ground receives the probe's telemetry data of onboard lock-up and the telemetry data of command execution results. In emergencies, the deep space station increases the uplink carrier. After the carrier hold-up time meets the corresponding requirements, uplink remote control commands can then be sent. Compared to the conventional mode, in deep space telemetry and control mode, the ground does not need to wait for two-way optical travel time to send remote control commands, greatly improving the utilization efficiency of the effective telemetry and control tracking arc.

[0107] like Figure 7As shown, the deep space telemetry and control (STDC) collaborative workflow includes the following steps: On the ground station timeline, starting at a geometrically visible elevation angle of 10 degrees, the ground sends an uplink carrier wave. After a space transmission delay, the carrier wave arrives at the detector and carrier lock is established. After holding the carrier wave for a specified duration, the ground sends uplink remote control commands. After a space transmission delay, the remote control commands arrive at the detector. On the detector timeline, carrier lock is established at the carrier arrival time, and commands are executed at the command arrival time. Relevant telemetry changes on the detector reach the ground after a space transmission delay. The ground receives the locked telemetry center satellite lock at the receiving time and obtains the command execution results telemetry after a space transmission delay. The figure illustrates the relationship between the geometrically visible uplink arc and the actual uplink arc on the ground.

[0108] like Figure 8 As shown, the system used in the deep-space long-time-delay condition extraterrestrial body obstruction tracking and control plan implementation method of this embodiment includes the following components: Tracking and control resource requirements are input into the tracking and control resource planning tool, which outputs available tracking stations. Available tracking station information is input into the extraterrestrial body obstruction tracking and control calculation module, which performs calculations based on orbit predictions provided by the orbit software and optical travel time provided by the optical travel time calculation and processing module. Tracking and control arc segment information from the processing results is input into the single-station continuous tracking arc segment processing module, which processes the tracking and control arc segments. The optical travel time calculation and processing module performs calculations based on the optical travel time provided by the orbit software, and the processing results are input into the command plan generation tool. The command plan generation tool generates a nominal plan based on the processing results output by the single-station continuous tracking arc segment processing module and the optical travel time output by the optical travel time calculation and processing module. The remote control software corrects the remote control command requirements based on the optical travel time, and generates a remote control command plan by combining the remote control command source code and the platform software. The entire system enables collaborative work throughout the entire process, from requesting measurement and control resources to generating instruction plans.

[0109] Figure 9 This diagram illustrates a structural schematic of an embodiment of a system 200 for implementing a deep-space long-delay telemetry and control plan for extraterrestrial body obstruction, provided by the present invention. Figure 9 As shown, the system 200 for the deep space long-time-delay extraterrestrial body obstruction measurement and control plan includes: The determination module 201 is used to determine the time window of the extraterrestrial object's obscuration and the available ground tracking stations before and after the extraterrestrial object's obscuration by using the precise orbital data of the probe flying around the extraterrestrial object. Processing module 202 is used to calculate the station forecast of the ground-based available tracking station within the time window of the extraterrestrial object occlusion based on the station coordinates of the available ground tracking station, the precise orbit data of the probe, and the ephemeris data of the extraterrestrial object and the Earth. The station forecast includes data truncation caused by the extraterrestrial object occlusion. Calculation module 203 is used to calculate the unidirectional optical travel time of uplink and downlink signal transmission based on the distance between the detector and the ground station in the station forecast. Setting module 204 is used to set station tracking events according to the station forecast, based on the principle that the uplink event precedes the unidirectional optical transmission time of the uplink and downlink signals and the downlink event lags behind the unidirectional optical transmission time of the uplink and downlink signals. The generation module 205 is used to truncate the data, merge adjacent telemetry and control arc segments with a time interval less than a preset threshold into a single-station continuous tracking arc segment, and set a station task preparation event according to the single-station continuous tracking arc segment. The control module 206 is used to decouple the uplink telemetry and control link from the downlink telemetry and control link in the deep space telemetry and control mode. When the uplink and downlink signal transmission is unidirectional optical, the module controls the transmission of the uplink carrier when the station is geometrically visible and reaches a preset elevation angle. After the uplink carrier is transmitted, the module controls the transmission of the uplink remote control command.

[0110] In an alternative embodiment, the determining module 201 is specifically used for: Based on the precise orbital data of the probe, the times when the probe enters and exits the extraterrestrial body's obscuring region during its flight around the extraterrestrial body are calculated, and the time window for the extraterrestrial body's obscuring is determined. Based on the time window of the extraterrestrial object obscuring the Earth, the ephemeris data of the extraterrestrial object and Earth, and the coordinates of the ground stations, the measurement and control conditions of the ground stations before and after the time window of the extraterrestrial object obscuring the Earth are analyzed to determine the ground stations that are geometrically visible to the detector. Based on the availability of ground-based deep space station network resources and station tracking priorities, the available ground-based tracking stations that are geometrically visible to the probe are selected to participate in tracking before and after extraterrestrial celestial bodies are obscured.

[0111] In an alternative embodiment, the processing module 202 is specifically used for: Based on the site coordinates of the available ground tracking stations, the precise orbit data of the probe, and the ephemeris data of the extraterrestrial objects and the Earth, the geometric visibility of the available ground tracking stations relative to the probe is calculated within the time window of the extraterrestrial object obscuring the probe. Based on the geometric visibility and the geometric occlusion relationship of the extraterrestrial object on the detector, the tracking arc segment of the available ground tracking stations within the time window of the extraterrestrial object occlusion is calculated. The tracking arc segment is divided by the extraterrestrial object occlusion event into station prediction before entering the extraterrestrial object occlusion and station prediction after exiting the extraterrestrial object occlusion. The station forecasts before the extraterrestrial object enters the Earth's atmosphere and after the extraterrestrial object exits the Earth's atmosphere are used as the station forecasts of the available ground tracking stations within the time window of the extraterrestrial object's atmosphere obscuring the Earth's atmosphere. The station forecasts include the data truncation caused by the extraterrestrial object's obscuring the Earth's atmosphere.

[0112] In an alternative embodiment, the computing module 203 is specifically used for: Extract the probe's position data at each moment within the time window of the extraterrestrial object's obscuring, as well as the ground station position data of the available ground tracking stations, from the station's forecast. Based on the detector location data and the ground station location data, calculate the instantaneous straight-line distance between the detector and the available ground tracking station at each moment; Based on the instantaneous straight-line distance and the speed of light constant at each moment, the unidirectional optical travel time of uplink and downlink signal transmission between the detector and the available ground tracking station at each moment is calculated.

[0113] In an alternative embodiment, the setting module 204 is specifically used for: Based on the forecast from the monitoring station, determine the entry time of the probe into the extraterrestrial celestial body obscuring region and the exit time from the extraterrestrial celestial body obscuring region; Based on the time of entry into the blockage, the time of exit from the blockage, and the unidirectional optical travel time of uplink and downlink signal transmission between the detector and the available ground tracking station at each time, calculate the time when the detector last transmits the uplink carrier on the ground before entering the blockage, the time when the detector stops receiving downlink telemetry on the ground after entering the blockage, the time when the detector transmits the uplink carrier again on the ground before exiting the blockage, and the time when the detector resumes receiving downlink telemetry on the ground after exiting the blockage. Based on the last uplink carrier transmission time, the downlink telemetry reception termination time, the next uplink carrier transmission time, and the downlink telemetry reception recovery time, and combined with the station tracking arc in the station forecast, the station tracking event containing the uplink event time and the downlink event time is set.

[0114] In an alternative embodiment, the generation module 205 is specifically used for: Based on the data truncation in the station forecast, identify the adjacent tracking arc segments of the ground-based available tracking stations within the time window of the extraterrestrial body occlusion event; Calculate the time interval between the departure time of the previous measurement and control arc segment and the arrival time of the next measurement and control arc segment in the adjacent measurement and control arc segments; Determine whether the time interval is less than the preset threshold, and merge adjacent measurement and control arc segments that are less than the preset threshold into a single-station continuous tracking arc segment; Based on the single-station continuous tracking arc segment, set the entry time into the single-station continuous tracking arc segment and the exit time from the single-station continuous tracking arc segment; Based on the continuous tracking arc time of the incoming single station and the continuous tracking arc time of the outgoing single station, the station mission preparation event of the available ground tracking stations is set.

[0115] In an alternative embodiment, the control module 206 is specifically used for: Based on the forecast from the monitoring station, determine the starting time when the ground-based available tracking station becomes geometrically visible to the detector and reaches a preset elevation angle; In deep space telemetry and control mode, the uplink telemetry and control link is decoupled from the downlink telemetry and control link, and the ground-based available tracking stations are controlled to send uplink carriers at the starting moment; After sending the uplink carrier, after a preset carrier hold time, the ground-based available tracking station is controlled to send uplink remote control commands; Based on the unidirectional optical transmission of the uplink and downlink signals, determine the arrival time of the uplink remote control command to the detector and the arrival time of the downlink telemetry to the available ground tracking station after the detector executes the command. Without waiting for the telemetry arrival time, based on the station tracking event and the station mission preparation event, the available ground tracking stations are controlled to continue executing subsequent uplink and downlink events.

[0116] It should be noted that the beneficial effects of the system 200 for implementing the deep-space long-time-delay telemetry and control plan for extraterrestrial body obstruction are the same as those of the method for implementing the deep-space long-time-delay telemetry and control plan for extraterrestrial body obstruction, and will not be repeated here. Furthermore, the system provided in the above embodiments is only illustrated by the division of the above functional modules. In practical applications, the above functions can be assigned to different functional modules as needed, that is, the system can be divided into different functional modules according to the actual situation to complete all or part of the functions described above. In addition, the system and method embodiments provided in the above embodiments belong to the same concept, and their specific implementation process is detailed in the method embodiments, and will not be repeated here.

[0117] The system 200 for implementing the deep space long-time-delay extraterrestrial body obstruction measurement and control plan of the present invention can be a computer program (including program code) running on a computer device. For example, the system 200 for implementing the deep space long-time-delay extraterrestrial body obstruction measurement and control plan of the present invention is an application software that can be used to execute the corresponding steps in the method for implementing the deep space long-time-delay extraterrestrial body obstruction measurement and control plan of the present invention.

[0118] In some embodiments, the deep-space long-delay extraterrestrial body obstruction measurement and control plan implementation system 200 of the present invention can be implemented in a combination of hardware and software. As an example, the deep-space long-delay extraterrestrial body obstruction measurement and control plan implementation system 200 of the present invention can be a processor in the form of a hardware decoding processor, which is programmed to execute the deep-space long-delay extraterrestrial body obstruction measurement and control plan implementation method of the present invention. For example, the processor in the form of a hardware decoding processor can adopt one or more application-specific integrated circuits (ASICs), DSPs, programmable logic devices (PLDs), complex programmable logic devices (CPLDs), field-programmable gate arrays (FPGAs), or other electronic components.

[0119] The modules described in the embodiments of this invention can be implemented in software or hardware. The names of the modules are not, in some cases, limiting the scope of the module itself.

[0120] An electronic device according to an embodiment of the present invention includes a memory, a processor, and a computer program stored in the memory and executable on the processor. When the processor executes the computer program, it implements any of the above-mentioned methods for implementing the deep space long-time-delay telemetry and control plan for extraterrestrial celestial body obstruction. That is, an electronic device according to an embodiment of the present invention may include, but is not limited to: a processor and a memory; the memory is used to store the computer program; the processor is used to execute the method for implementing the deep space long-time-delay telemetry and control plan for extraterrestrial celestial body obstruction as shown in any embodiment of the present invention by calling the computer program.

[0121] In one alternative embodiment, an electronic device is provided, such as Figure 10 As shown, Figure 10 The illustrated electronic device 4000 includes a processor 4001 and a memory 4003. The processor 4001 and the memory 4003 are connected, for example, via a bus 4002. Optionally, the electronic device 4000 may further include a transceiver 4004, which can be used for data interaction between the electronic device and other electronic devices, such as sending and / or receiving data. It should be noted that in practical applications, the transceiver 4004 is not limited to one type, and the structure of the electronic device 4000 does not constitute a limitation on the embodiments of the present invention.

[0122] Processor 4001 may be a CPU (Central Processing Unit), a general-purpose processor, a DSP (Digital Signal Processor), an ASIC (Application Specific Integrated Circuit), an FPGA (Field Programmable Gate Array), or other programmable logic devices, transistor logic devices, hardware components, or any combination thereof. It can implement or execute the various exemplary logic blocks, modules, and circuits described in conjunction with the disclosure of this invention. Processor 4001 may also be a combination that implements computational functions, such as including one or more microprocessor combinations, a combination of a DSP and a microprocessor, etc.

[0123] Bus 4002 may include a path for transmitting information between the aforementioned components. Bus 4002 may be a PCI (Peripheral Component Interconnect) bus or an EISA (Extended Industry Standard Architecture) bus, etc. Bus 4002 can be divided into address bus, data bus, control bus, etc. For ease of representation, Figure 10 The bus 4002 is represented by only one thick line, but this does not mean that there is only one bus or one type of bus.

[0124] The memory 4003 may be ROM (Read Only Memory) or other types of static storage devices capable of storing static information and instructions, RAM (Random Access Memory) or other types of dynamic storage devices capable of storing information and instructions, or EEPROM (Electrically Erasable Programmable Read Only Memory), CD-ROM (Compact Disc Read Only Memory) or other optical disc storage, optical disc storage (including compressed optical discs, laser discs, optical discs, digital universal optical discs, Blu-ray discs, etc.), magnetic disk storage media or other magnetic storage devices, or any other medium capable of carrying or storing desired program code in the form of instructions or data structures and accessible by a computer, but not limited thereto.

[0125] The memory 4003 stores application code (computer program) for executing the present invention, and its execution is controlled by the processor 4001. The processor 4001 executes the application code stored in the memory 4003 to implement the content shown in the foregoing method embodiments.

[0126] Among them, electronic devices can also be terminal devices. A terminal device can be any terminal device that can install applications and access web pages through applications, including at least one of smartphones, tablets, laptops, desktop computers, smart speakers, smartwatches, smart TVs, and smart in-vehicle devices.

[0127] It should be noted that, Figure 10 The electronic device shown is merely an example and should not be construed as limiting the functionality and scope of use of the embodiments of the present invention.

[0128] An embodiment of the present invention provides a computer-readable storage medium storing a computer program, which, when executed by a processor, implements any of the above-mentioned methods for implementing the telemetry and control plan for extraterrestrial celestial body obstruction under deep space long-delay conditions.

[0129] Alternatively, the computer-readable storage medium may be a read-only memory (ROM), a random access memory (RAM), a compact disc read-only memory (CD-ROM), magnetic tape, a floppy disk, and an optical data storage device, etc.

[0130] In an exemplary embodiment, a computer program product or computer program is also provided, which includes computer instructions stored in a computer-readable storage medium. The processor of an electronic device reads the computer instructions from the computer-readable storage medium and executes the computer instructions, causing the electronic device to perform the aforementioned method for implementing the telemetry and control plan for extraterrestrial celestial body obstruction under conditions of large time delay in deep space.

[0131] Computer program code for performing the operations of this invention can be written in one or more programming languages ​​or a combination thereof, including object-oriented programming languages ​​such as Java, Smalltalk, and C++, and conventional procedural programming languages ​​such as C or similar languages. The program code can be executed entirely on the user's computer, partially on the user's computer, as a standalone software package, partially on the user's computer and partially on a remote computer, or entirely on a remote computer or server. In cases involving remote computers, the remote computer can be connected to the user's computer via any type of network—including a local area network (LAN) or a wide area network (WAN)—or can be connected to an external computer (e.g., via the Internet using an Internet service provider).

[0132] It should be understood that the flowcharts and block diagrams in the accompanying drawings illustrate the architecture, functionality, and operation of possible implementations of methods and computer program products according to various embodiments of the present invention. In this regard, each block in a flowchart or block diagram may represent a module, segment, or portion of code containing one or more executable instructions for implementing the specified logical function. It should also be noted that in some alternative implementations, the functions indicated in the blocks may occur in a different order than those indicated in the drawings. For example, two consecutively indicated blocks may actually be executed substantially in parallel, and they may sometimes be executed in reverse order, depending on the functions involved. It should also be noted that each block in the block diagrams and / or flowcharts, and combinations of blocks in the block diagrams and / or flowcharts, may be implemented using a dedicated hardware-based system that performs the specified function or operation, or using a combination of dedicated hardware and computer instructions.

[0133] The computer-readable storage medium provided in this invention can be, but is not limited to, an electrical, magnetic, optical, electromagnetic, infrared, or semiconductor system, apparatus, or device, or any combination thereof. More specific examples of a computer-readable storage medium may include, but are not limited to: an electrical connection having one or more wires, a portable computer disk, a hard disk, random access memory (RAM), read-only memory (ROM), erasable programmable read-only memory (EPROM or flash memory), optical fiber, portable compact disk read-only memory (CD-ROM), optical storage device, magnetic storage device, or any suitable combination thereof. In this invention, a computer-readable storage medium can be any tangible medium containing or storing a program that can be used by or in conjunction with an instruction execution system, apparatus, or device.

[0134] The aforementioned computer-readable storage medium carries one or more programs, which, when executed by the electronic device, cause the electronic device to perform the method shown in the above embodiments.

[0135] The above description is merely a preferred embodiment of the present invention and an explanation of the technical principles employed. Those skilled in the art should understand that the scope of disclosure in this invention is not limited to technical solutions formed by specific combinations of the above-described technical features, but should also cover other technical solutions formed by arbitrary combinations of the above-described technical features or their equivalents without departing from the above-disclosed concept. For example, technical solutions formed by substituting the above features with (but not limited to) technical features with similar functions disclosed in this invention.

[0136] It should be noted that the terms "first," "second," etc., used in the specification and claims of this application are used to distinguish similar objects and represent a limitation on a specific order or sequence. Where appropriate, the order of use for similar objects can be interchanged so that the embodiments of this application described herein can be implemented in an order other than that shown or described.

[0137] Those skilled in the art will recognize that this invention can be implemented as a system, method, or computer program product. Therefore, this invention can be specifically implemented in the following forms: it can be entirely hardware, entirely software (including firmware, resident software, microcode, etc.), or a combination of hardware and software, generally referred to herein as a "circuit," "module," or "system." Furthermore, in some embodiments, this invention can also be implemented as a computer program product contained in one or more computer-readable media, which includes computer-readable program code.

[0138] Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention. Those skilled in the art can make changes, modifications, substitutions and variations to the above embodiments within the scope of the present invention.

Claims

1. A method for implementing an extraterrestrial object blocking TT&C plan under a deep space large time delay condition, characterized in that, include: Using precise orbital data from probes orbiting extraterrestrial objects, we can determine the time window for extraterrestrial object obscuring and the available ground-based tracking stations before and after the obscuring. Based on the site coordinates of the available ground tracking stations, the precise orbit data of the probe, and the ephemeris data of extraterrestrial objects and Earth, the station forecast of the available ground tracking stations within the time window of the extraterrestrial object obscuring the Earth is calculated, and the station forecast includes data truncation caused by the extraterrestrial object obscuring the Earth. Based on the distance between the detector and the ground station predicted by the station, calculate the unidirectional optical travel time of uplink and downlink signal transmission; Based on the principle that the uplink event precedes the unidirectional optical transmission time of the uplink and downlink signals and the downlink event lags behind the unidirectional optical transmission time of the uplink and downlink signals, the station tracking event is set according to the station forecast. For the data truncation, adjacent telemetry and control arc segments with a time interval less than a preset threshold are merged into a single-station continuous tracking arc segment, and a station task preparation event is set according to the single-station continuous tracking arc segment. In deep space telemetry and control mode, the uplink telemetry and control link is decoupled from the downlink telemetry and control link. When the uplink and downlink signals are transmitted in one direction, the uplink carrier is controlled to be sent when the station is geometrically visible and reaches a preset elevation angle. After the uplink carrier is sent, the uplink remote control command is controlled to be sent.

2. The method of claim 1, wherein the method is implemented in a deep space large delay extraterrestrial object occultation TT&C plan. The steps for determining the time window of extraterrestrial object obscuring and the available ground-based tracking stations before and after the obscuring, using precise orbital data from a probe orbiting an extraterrestrial object, include: Based on the precise orbital data of the probe, the times when the probe enters and exits the extraterrestrial body's obscuring region during its flight around the extraterrestrial body are calculated, and the time window for the extraterrestrial body's obscuring is determined. Based on the time window of the extraterrestrial object obscuring the Earth, the ephemeris data of the extraterrestrial object and Earth, and the coordinates of the ground stations, the measurement and control conditions of the ground stations before and after the time window of the extraterrestrial object obscuring the Earth are analyzed to determine the ground stations that are geometrically visible to the detector. Based on the availability of ground-based deep space station network resources and station tracking priorities, the available ground-based tracking stations that are geometrically visible to the probe are selected to participate in tracking before and after extraterrestrial celestial bodies are obscured.

3. The method of claim 1, wherein the method further comprises: determining a time delay between the ground station and the extraterrestrial object; and determining a time delay between the ground station and the deep space probe. The steps for calculating the station forecast of the available ground-based tracking stations within the time window of the extraterrestrial object's obscuration, based on the site coordinates of the available ground-based tracking stations, the precise orbit data of the probe, and the ephemeris data of the extraterrestrial object and Earth, include: Based on the site coordinates of the available ground tracking stations, the precise orbit data of the probe, and the ephemeris data of the extraterrestrial objects and the Earth, the geometric visibility of the available ground tracking stations relative to the probe is calculated within the time window of the extraterrestrial object obscuring the probe. Based on the geometric visibility and the geometric occlusion relationship of the extraterrestrial object on the detector, the tracking arc segment of the available ground tracking stations within the time window of the extraterrestrial object occlusion is calculated. The tracking arc segment is divided by the extraterrestrial object occlusion event into station prediction before entering the extraterrestrial object occlusion and station prediction after exiting the extraterrestrial object occlusion. The station forecasts before the extraterrestrial object enters the Earth's atmosphere and after the extraterrestrial object exits the Earth's atmosphere are used as the station forecasts of the available ground tracking stations within the time window of the extraterrestrial object's atmosphere obscuring the Earth's atmosphere. The station forecasts include the data truncation caused by the extraterrestrial object's obscuring the Earth's atmosphere.

4. The method of claim 3, wherein the method further comprises: The steps for calculating the unidirectional optical travel time of uplink and downlink signal transmission based on the distance between the detector and the ground station predicted by the station include: Extract the probe's position data at each moment within the time window of the extraterrestrial object's obscuring, as well as the ground station position data of the available ground tracking stations, from the station's forecast. Based on the detector location data and the ground station location data, calculate the instantaneous straight-line distance between the detector and the available ground tracking station at each moment; Based on the instantaneous straight-line distance and the speed of light constant at each moment, the unidirectional optical travel time of uplink and downlink signal transmission between the detector and the available ground tracking station at each moment is calculated.

5. The method of claim 4, wherein the method further comprises: determining a time delay between the first time and the second time; and determining a time delay between the third time and the fourth time. Following the principle that uplink events precede the unidirectional optical travel time of uplink and downlink signal transmission, and downlink events lag behind the unidirectional optical travel time of uplink and downlink signal transmission, the steps for setting station tracking events based on the station forecast include: Based on the forecast from the monitoring station, determine the entry time of the probe into the extraterrestrial celestial body obscuring region and the exit time from the extraterrestrial celestial body obscuring region; Based on the time of entry into the blockage, the time of exit from the blockage, and the unidirectional optical travel time of uplink and downlink signal transmission between the detector and the available ground tracking station at each time, calculate the time when the detector last transmits the uplink carrier on the ground before entering the blockage, the time when the detector stops receiving downlink telemetry on the ground after entering the blockage, the time when the detector transmits the uplink carrier again on the ground before exiting the blockage, and the time when the detector resumes receiving downlink telemetry on the ground after exiting the blockage. Based on the last uplink carrier transmission time, the downlink telemetry reception termination time, the next uplink carrier transmission time, and the downlink telemetry reception recovery time, and combined with the station tracking arc in the station forecast, the station tracking event containing the uplink event time and the downlink event time is set.

6. The method of claim 5, wherein the method further comprises: For the data truncation, the steps of merging adjacent telemetry and control arc segments with a time interval less than a preset threshold into a single-station continuous tracking arc segment, and setting a station task preparation event based on the single-station continuous tracking arc segment, include: Based on the data truncation in the station forecast, identify the adjacent tracking arc segments of the ground-based available tracking stations within the time window of the extraterrestrial body occlusion event; Calculate the time interval between the departure time of the previous measurement and control arc segment and the arrival time of the next measurement and control arc segment in the adjacent measurement and control arc segments; Determine whether the time interval is less than the preset threshold, and merge adjacent measurement and control arc segments that are less than the preset threshold into a single-station continuous tracking arc segment; Based on the single-station continuous tracking arc segment, set the entry time into the single-station continuous tracking arc segment and the exit time from the single-station continuous tracking arc segment; Based on the continuous tracking arc time of the incoming single station and the continuous tracking arc time of the outgoing single station, the station mission preparation event of the available ground tracking stations is set.

7. The method of claim 6, wherein the method further comprises: determining a time delay between the first time and the second time; and determining a time delay between the third time and the fourth time. In deep space telemetry and control mode, the uplink telemetry and control link is decoupled from the downlink telemetry and control link. Based on the unidirectional optical transmission of the uplink and downlink signals, the uplink carrier is controlled to be transmitted when the station is geometrically visible and reaches a preset elevation angle. After transmitting the uplink carrier, the uplink remote control command is transmitted. This includes the following steps: Based on the forecast from the monitoring station, determine the starting time when the ground-based available tracking station becomes geometrically visible to the detector and reaches the preset elevation angle; In deep space telemetry and control mode, the uplink telemetry and control link is decoupled from the downlink telemetry and control link, and the ground-based available tracking stations are controlled to send uplink carriers at the starting moment; After sending the uplink carrier, after a preset carrier hold time, the ground-based available tracking station is controlled to send uplink remote control commands; Based on the unidirectional optical transmission of the uplink and downlink signals, determine the arrival time of the uplink remote control command to the detector and the arrival time of the downlink telemetry to the available ground tracking station after the detector executes the command. Without waiting for the telemetry arrival time, based on the station tracking event and the station mission preparation event, the available ground tracking stations are controlled to continue executing subsequent uplink and downlink events.

8. An extraterrestrial object blocking TT&C plan implementation system under deep space large time delay working conditions, characterized in that, include: The determination module is used to determine the time window of extraterrestrial object obscuring and the available ground tracking stations before and after the extraterrestrial object obscuring, using precise orbital data of the probe flying around the extraterrestrial object. The processing module is used to calculate the station forecast of the ground-based available tracking station within the time window of the extraterrestrial object occlusion based on the station coordinates of the available ground-based tracking station, the precise orbit data of the probe, and the ephemeris data of the extraterrestrial object and the Earth. The station forecast includes data truncation caused by the extraterrestrial object occlusion. The calculation module is used to calculate the unidirectional optical travel time of uplink and downlink signal transmission based on the distance between the detector and the ground station in the station forecast. The setting module is used to set the station tracking event according to the station forecast, based on the principle that the uplink event precedes the unidirectional optical transmission time of the uplink and downlink signals and the downlink event lags behind the unidirectional optical transmission time of the uplink and downlink signals. The generation module is used to truncate the data, merge adjacent telemetry and control arc segments with a time interval less than a preset threshold into a single-station continuous tracking arc segment, and set a station task preparation event according to the single-station continuous tracking arc segment. The control module is used to decouple the uplink and downlink telemetry and control links in deep space telemetry and control mode. When the uplink and downlink signals are transmitted in one direction, the module controls the transmission of the uplink carrier when the station is geometrically visible and reaches a preset elevation angle. After the uplink carrier is transmitted, the module controls the transmission of the uplink remote control command.

9. An electronic device, comprising: The electronic device includes a processor coupled to a memory, the memory storing at least one computer program, which is loaded and executed by the processor to enable the electronic device to implement the method for implementing the deep space long time delay measurement and control plan for extraterrestrial celestial body obstruction as described in any one of claims 1 to 7.

10. A computer-readable storage medium, characterized in that, The computer-readable storage medium stores at least one computer program, which, when executed by a processor, implements the method for implementing the deep space long-time-delay operation condition extraterrestrial body occlusion measurement and control plan as described in any one of claims 1 to 7.

Images