Measurement and control responder autonomous reset method and system suitable for low earth orbit satellite

Abstract

The invention provides a measurement and control responder autonomous reset method suitable for a low-orbit satellite, and the method comprises the steps: obtaining the latitude and longitude data of a sub-satellite point of a satellite in real time under the enabling condition of an autonomous reset function, continuously comparing the latitude and longitude data with a pre-stored boundary threshold value of a measurement and control arc section of a management area, and judging whether the measurement and control arc section is entered or not; if entering the boundary is confirmed, the satellite service sends a reset instruction to the measurement and control responder, equipment reset action is triggered, meanwhile, an automatic reset function is automatically forbidden, and a working time counter is reset after the responder is reset; when the reset working time reaches a preset autonomous reset enabling time threshold value, the autonomous reset function is reactivated; and if the preset maximum waiting time threshold value is exceeded, forcibly triggering reset operation by the satellite service system. In addition, the invention further provides a measurement and control responder autonomous reset system suitable for the low-orbit satellite, a storage medium and electronic equipment. Therefore, the problem that the satellite-borne measurement and control responder is abnormal due to the influence of the space environment can be solved.

Description

Technical Field

[0001] The present invention relates to the technical field of satellite TT&C, and in particular to a method, system, storage medium and electronic device for autonomous reset of a TT&C transponder suitable for low-earth orbit satellites. Background Art

[0002] The TT&C transponder mainly cooperates with the ground TT&C station to realize satellite remote control, telemetry and ranging functions, and is one of the key components of the satellite. At present, the TT&C transponder generally adopts a design based on large-scale integrated circuits. The near-earth orbit space where the satellite operates has a complex radiation environment, which may cause abnormal phenomena such as single-event upset and single-event latch-up in the integrated circuit, and then lead to TT&C transponder failures. Especially when the integrated circuit used is a low-grade device, since its anti-space environment design performance is not as good as that of aerospace-grade devices, the abnormal problems caused by the space environment are particularly prominent. The TT&C transponder is related to the safety of the satellite-ground TT&C link. Once a failure occurs, it may cause the satellite to get out of control and needs to be restored in time. The current mainstream autonomous anomaly handling method for the TT&C transponder is to perform an autonomous reset on the TT&C transponder, which mainly includes the following two forms: one is that the on-board management directly sends a reset instruction to the TT&C transponder, and the TT&C transponder triggers a software reset or a hardware reset according to the instruction; the other is that the on-board management first sends a power-off instruction to the TT&C transponder and then sends a power-on instruction to the TT&C transponder, that is, powers off and restarts the TT&C transponder. The above two forms are both called autonomous reset.

[0003] Currently, the main autonomous reset methods for TT&C transponders are mainly divided into three categories:

[0004] 1) Diagnose the working state parameters of the TT&C transponder. When the parameters exceed the normal range, the TT&C transponder resets itself autonomously. The patent "A Method for Realizing On-Orbit Autonomous Recovery of a Single TT&C Transponder by Using AGC Value" with the publication number CN103869732A proposes a method for realizing TT&C anomaly diagnosis by monitoring the AGC value and then autonomously resetting and recovering. The patent "A Method for On-Orbit Autonomous Recovery of a Spaceborne All-Digital USB Transponder" with the publication number CN112688729B proposes a method for realizing TT&C anomaly diagnosis by monitoring the frequency offset and the carrier lock state of the machine and then autonomously resetting and recovering. The patent "A Method and System for Recovering the On-Orbit Latch of a Spaceborne Transponder" with the publication number CN109831242A proposes a method for realizing TT&C anomaly diagnosis by monitoring whether the uplink remote control command is responded or whether the downlink telemetry is normal and then autonomously resetting and recovering. The patent "A Method for a Satellite Spread-Spectrum Transponder to Autonomously Resist Single Event Upset Faults in Space" with the publication number CN104898477A proposes a joint diagnosis of working state parameters such as AGC, carrier lock, pseudo-code lock, and bit synchronization. When the parameters exceed the normal range, it resets and recovers autonomously. These types of methods can only handle anomalies related to the diagnostic parameters. When the anomaly type is not related to the diagnostic parameters or when the anomaly type does not belong to any of the parameter state tables, it cannot be processed and recovered. For example, in the patent CN104898477A, when AGC, carrier lock, pseudo-code lock, bit synchronization, etc. are all unlocked, this technical solution cannot diagnose whether the transponder is in an abnormal state or the ground station has not given an uplink signal.

[0005] 2) Autonomously reset the TT&C transponder regularly, for example, reset it once every 24 hours. This method does not require diagnosing the working parameters of the TT&C transponder and is simple and easy to operate, but it also has deficiencies: Since it is a periodic reset, the autonomous reset time of the TT&C may coincide with the normal satellite TT&C time, resulting in an unexpected TT&C interruption during normal satellite TT&C.

[0006] 3) The satellite autonomously identifies the TT&C entry and performs an autonomous reset. The patent "A Method and System for Autonomous Reset Control of a TT&C Transponder" with the publication number CN113114186B proposes a method for updating the TT&C reset time window by monitoring the uplink lock state to determine whether the satellite has entered the country and selecting to perform an autonomous reset within the reset time window. This method relies on the uplink lock state of the ground station to determine whether the satellite has entered the country. Once the TT&C transponder is in an abnormal state where the uplink cannot be locked, or the ground station fails to give an uplink signal in a timely manner due to various reasons, the autonomous reset cannot be performed.

[0007] In summary, it is obvious that the existing technologies have inconveniences and defects in actual use, so it is necessary to improve them. Summary of the Invention

[0008] In view of the above deficiencies, the purpose of the present invention is to provide a method, system, storage medium and electronic device for autonomous reset of a TT&C transponder applicable to low-earth orbit satellites, which are used to solve the problems in the prior art that when an anomaly is not related to diagnostic parameters, it cannot be processed and restored, and the technical problem of causing unexpected TT&C interruptions during normal satellite TT&C.

[0009] To solve the above technical problems, in the first aspect, the present invention provides a method for autonomous reset of a TT&C transponder applicable to low-earth orbit satellites, including the steps of:

[0010] Under the condition that the autonomous reset function is enabled, continuously obtain the sub-satellite point longitude and latitude information of the satellite through the on-board system, and compare it with the pre-stored longitude and latitude thresholds of the TT&C arc boundary of the management area to determine whether the satellite enters the TT&C arc boundary of the management area;

[0011] When it is determined that the satellite enters the TT&C arc boundary of the management area, send a reset command to the TT&C transponder through the on-board system to trigger the reset of the TT&C transponder, simultaneously disable the autonomous reset function, and clear the post-reset working time of the TT&C transponder to start timing again;

[0012] When the post-reset working time reaches the preset autonomous reset enable time threshold, re-enable the autonomous reset function;

[0013] If the post-reset working time reaches the preset maximum reset waiting time threshold, forcibly trigger the reset of the TT&C transponder through the on-board system.

[0014] Optionally, before continuously obtaining the sub-satellite point longitude and latitude information of the satellite through the on-board system and comparing it with the pre-stored longitude and latitude thresholds of the TT&C arc boundary of the management area, it further includes:

[0015] Select four ground TT&C stations at the westernmost, easternmost, southernmost and northernmost points of the management area. According to the longitude and latitude of the four ground TT&C stations and the minimum working elevation angle of the TT&C antenna, use satellite orbit simulation software to calculate the sub-satellite point longitude and latitude ranges corresponding to the visible arcs of each TT&C station, and expand the time margin to form the boundary range of the combined TT&C arc;

[0016] Based on the boundary range of the combined TT&C arc, determine the longitude and latitude thresholds of the TT&C arc boundary of the management area and pre-store them in the on-board system.

[0017] Optionally, the value of the autonomous reset enable time threshold is restricted by the following formula:

[0018] t f +n×T<t th <(n+1)×T;

[0019] Wherein, tth is the autonomous reset enable time threshold, T is the satellite orbit period, and t f is the time for the satellite to pass through the measurement and control arc section of the management area; n is an adjustable non - negative integer used to control the frequency of autonomous reset.

[0020] Optionally, under the condition that the autonomous reset function is enabled, the on - satellite point longitude and latitude information of the satellite is continuously obtained through the on - board system, and compared with the pre - stored longitude and latitude thresholds of the measurement and control arc section boundary of the management area to determine whether the satellite enters the measurement and control arc section boundary of the management area, including:

[0021] Judge whether the autonomous reset function is enabled; if it is enabled, continuously obtain the on - satellite point longitude and latitude information of the satellite through the on - board system, and judge whether the GNSS positioning information and the on - satellite point longitude and latitude information are valid;

[0022] If it is valid, compare the on - satellite point longitude and latitude information with the pre - stored longitude and latitude thresholds of the measurement and control arc section boundary of the management area. If the on - satellite point longitude and latitude information falls within the range of the longitude and latitude thresholds, it is determined that the satellite enters the measurement and control arc section boundary of the management area.

[0023] Optionally, when it is determined that the satellite enters the measurement and control arc section boundary of the management area, send a reset command to the measurement and control transponder through the on - board system to trigger the reset of the measurement and control transponder, simultaneously prohibit the autonomous reset function, and clear the post - reset working time of the measurement and control transponder to start a new timing, including:

[0024] When it is determined that the satellite enters the measurement and control arc section boundary of the management area, send a reset command to the measurement and control transponder through the on - board system;

[0025] Based on the reset command, trigger the measurement and control transponder to reset, and simultaneously prohibit the autonomous reset function of the measurement and control transponder;

[0026] After detecting the reset of the measurement and control transponder, control the post - reset working time of the measurement and control transponder to be cleared and start a new timing.

[0027] Optionally, the measurement and control arc section boundary of the management area is the measurement and control arc section boundary of the national territory area or the arc section boundary of the joint coverage area of multiple national measurement and control stations.

[0028] Optionally, the priority of the on - board system forcibly triggering the reset of the measurement and control transponder is higher than the triggering condition of the autonomous reset function.

[0029] Based on the same inventive concept, the present invention also provides a measurement and control transponder autonomous reset system applicable to low - earth orbit satellites, including:

[0030] Satellite operations are used to continuously obtain the sub-satellite point longitude and latitude information of the satellite under the condition that the autonomous reset function is enabled, and compare it with the pre-stored longitude and latitude thresholds of the measurement and control arc segment boundaries of the management area to determine whether the satellite enters the measurement and control arc segment boundaries of the management area;

[0031] The satellite operations are also used to, when it is determined that the satellite enters the measurement and control arc segment boundaries of the management area, trigger the reset of the measurement and control transponder by sending a reset command to the measurement and control transponder, simultaneously disable the autonomous reset function, and clear the post-reset working time of the measurement and control transponder to restart the timing;

[0032] The measurement and control transponder is used to re-enable the autonomous reset function when the post-reset working time reaches a preset autonomous reset enable time threshold;

[0033] The satellite operations are also used to forcibly trigger the reset of the measurement and control transponder if the post-reset working time reaches a preset maximum reset waiting time threshold.

[0034] In a third aspect, an embodiment of the present invention provides a storage medium for storing a computer program for executing the autonomous reset method of the measurement and control transponder applicable to low-earth orbit satellites described in any one of the above.

[0035] In a fourth aspect, an embodiment of the present invention provides an electronic device, including a storage medium, a processor, and a computer program stored on the memory and executable on the processor, wherein the processor implements the autonomous reset method of the measurement and control transponder applicable to low-earth orbit satellites described above when executing the computer program.

[0036] The present invention solves the abnormal problems of the on-board measurement and control transponder caused by the space environment through autonomous reset, and restores it to a normal state; it also judges whether the satellite enters the measurement and control arc segment boundaries of the national territory area by detecting the sub-satellite point longitude and latitude of the satellite, and performs autonomous reset on the measurement and control transponder before the measurement and control enters the territory, avoiding the interruption of normal satellite measurement and control due to autonomous reset. In addition, the present invention does not rely on the diagnostic parameters of the transponder itself, and solves the problem in the prior art that it cannot be processed and restored when the abnormality is irrelevant to the diagnostic parameters. BRIEF DESCRIPTION OF THE DRAWINGS

[0037] Figure 1 is a schematic flowchart of the autonomous reset method of the measurement and control transponder applicable to low-earth orbit satellites provided in Embodiment 1 of the present invention;

[0038] Figure 2 is a step flowchart of the reset operation of the autonomous reset method of the measurement and control transponder applicable to low-earth orbit satellites provided in Embodiment 1 of the present invention;

[0039] Figure 3Schematic structural diagram of the autonomous reset system of the TT&C transponder applicable to low-Earth orbit satellites provided in the second embodiment of the present invention;

[0040] Figure 4 Schematic hardware structure diagram of the electronic device provided in the embodiment of the present invention. Specific embodiments

[0041] In order to make the objectives, technical solutions and advantages of the present invention clearer and more understandable, the present invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not used to limit the present invention.

[0042] It should be noted that the references to "one embodiment", "embodiment", "example embodiment", etc. in this specification mean that the described embodiment may include specific features, structures or characteristics, but not every embodiment must include these specific features, structures or characteristics. In addition, such expressions do not refer to the same embodiment. Further, when combining embodiments to describe specific features, structures or characteristics, whether or not there is an explicit description, it has been shown that it is within the knowledge of those skilled in the art to combine such features, structures or characteristics into other embodiments.

[0043] In addition, in the specification and subsequent claims, certain terms are used to refer to specific components or parts. Those of ordinary skill in the art should understand that manufacturers may use different nouns or terms to refer to the same component or part. The specification and subsequent claims do not use the difference in name as a way to distinguish components or parts, but use the difference in function of components or parts as the criterion for distinction. The terms "including" and "comprising" mentioned throughout the specification and subsequent claims are open-ended terms, so they should be interpreted as "including but not limited to". In addition, the term "connected" herein includes any direct and indirect electrical connection means. Indirect electrical connection means include connection through other devices.

[0044] Before describing the embodiments of the present application in detail, the technical concept of the present application is briefly described first: Based on the longitude and latitude information of the satellite's sub-satellite point, it dynamically determines whether it enters the boundary of the management area's measurement and control arc segment, triggers autonomous reset before entry, and avoids interfering with normal measurement and control. The technical solution includes two parallel processes: First, when the reset function is enabled, it determines the entry condition by verifying the valid longitude and latitude. If the condition is met, it executes the reset and disables the function, and at the same time clears the timer. Second, the independent timer module accumulates the working time after the reset. If the autonomous reset enable threshold is reached, the function is reopened. If the maximum waiting time threshold is exceeded, a forced reset is performed. This method does not rely on measurement and control parameter diagnosis. Through the geographical trigger and timing coordination mechanism, it solves the problem of abnormal recovery of space radiation, while avoiding the risk of measurement and control interruption, and supports dynamic adjustment of the threshold to adapt to different orbital periods and mission requirements.

[0045] The following describes the specific principle of the autonomous reset method of the measurement and control transponder applicable to low-earth orbit satellites of the present application in combination with specific embodiments.

[0046] Figure 1 The autonomous reset method of the measurement and control transponder applicable to low-earth orbit satellites provided in Embodiment 1 of the present invention is shown, including the following steps:

[0047] S101: Under the condition that the autonomous reset function is enabled, continuously obtain the longitude and latitude information of the satellite's sub-satellite point through the on-board management system, and compare it with the longitude and latitude threshold of the pre-stored boundary of the management area's measurement and control arc segment to determine whether the satellite enters the boundary of the management area's measurement and control arc segment. That is, it judges whether the satellite is in the critical area that needs to be reset through the geographical fence logic; wherein, the boundary of the management area's measurement and control arc segment is the boundary of the measurement and control arc segment of the national territory area or the boundary of the arc segment jointly covered by multiple national measurement and control stations; this embodiment will specifically take the boundary of the measurement and control arc segment of the national territory area as an example for illustration.

[0048] Specifically, when implementing, step S101 includes: judging whether the autonomous reset function is enabled; if it is enabled, continuously obtain the longitude and latitude information of the satellite's sub-satellite point through the on-board management system, and judge whether the GNSS positioning information and the longitude and latitude information of the sub-satellite point are valid; if they are valid, compare the longitude and latitude information of the sub-satellite point with the longitude and latitude threshold of the pre-stored boundary of the management area's measurement and control arc segment. If the longitude and latitude information of the sub-satellite point falls within the longitude and latitude threshold range, it is determined that the satellite enters the boundary of the management area's measurement and control arc segment.

[0049] In an optional implementation manner, before step S101, it further includes: selecting four ground measurement and control stations at the westernmost, easternmost, southernmost, and northernmost positions of the management area, and based on the longitude and latitude of the four ground measurement and control stations and the minimum working elevation angle of the measurement and control antenna, using satellite orbit simulation software to calculate the longitude and latitude range of the sub-satellite point corresponding to the visible arc segment of each measurement and control station, and expanding the time margin to form the boundary range of the combined measurement and control arc segment; based on the boundary range of the combined measurement and control arc segment, determining the longitude and latitude threshold of the measurement and control arc segment boundary of the management area, and pre-storing it in the satellite mission system.

[0050] Specifically, the satellite mission system stores the longitude and latitude threshold of the measurement and control arc segment boundary of the national territory area, and this longitude and latitude threshold can be modified by instructions in orbit. The specific design is as follows:

[0051] a) First, select 4 ground measurement and control stations G 1 , G 2 , G 3 , G 4 at the westernmost, easternmost, southernmost, and northernmost positions of the national territory area respectively. The boundary of the measurement and control arc segments of these 4 measurement and control stations constitutes the boundary of the measurement and control arc segment of the entire national territory area.

[0052] b) According to the longitude and latitude information of these 4 measurement and control stations and the minimum working elevation angle α (generally between 3 degrees and 10 degrees) of the ground measurement and control antenna, use STK (satellite orbit simulation software) software to calculate the maximum longitude and latitude range of the sub-satellite point corresponding to the visible arc segment of the 4 measurement and control stations respectively: G 1 longitude range (α 11 ~α 12 ), latitude range (β 1,1 ~β 1,2 ). Considering the longitude range (α ε ~α ε ) of the t 1,0 -minute margin (t 1,3 is generally preferably selected as 3 to 5 minutes, the same below) for the measurement and control arc segment; G 2 longitude range (α 2,1 ~α 2,2 ), latitude range (β 2,1 ~β 2,2 ). Considering the longitude range (α ε ~α 2,0 ~α 2,3 ) of the t 3 -minute margin; G 3,1 longitude range (α 3,2 ~α 3,1 ), latitude range (β 3,2 ~β ε ). Considering the latitude range (β 3,0 ~β 3,3 ) of the t 4 longitude range (α4,1 to α 4,2 ), the latitude range (β 4,1 to β 4,2 ), considering the latitude range (β ε with a time margin of t minutes 4,0 to β 4,3 ).

[0053] c) The combined area of the four stations is: the longitude range (α 1,0 to α 2,3 ), the latitude range (β 3,0 to β 4,3 ). This area is equivalent to a slight outward expansion on the basis of the actual measurement and control arc boundary in the national territory area. An autonomous reset is triggered at the outer expansion boundary, so that the reset time avoids the normal satellite measurement and control time period, thereby avoiding unexpected measurement and control interruptions during normal satellite measurement and control; then the corresponding longitude and latitude thresholds are bound in the on-board software.

[0054] That is, the determination of the longitude and latitude thresholds in this embodiment needs to be combined with the layout of ground measurement and control stations (such as the four stations in the west, east, south, and north) and orbital simulation calculations. The outward expansion time margin (t ε ) ensures that the reset action avoids the normal measurement and control period.

[0055] The on-board system receives the orbit determination information output by the satellite GNSS subsystem every second, and calculates the longitude and latitude information of the satellite's sub-satellite point (longitude α i , latitude β i ); then compares it with the pre-stored longitude and latitude thresholds, so as to judge whether the current longitude and latitude of the satellite's sub-satellite point are within the range corresponding to the longitude and latitude thresholds based on the comparison result, so as to determine whether the satellite enters the boundary of the measurement and control arc in the national territory area.

[0056] S102: When it is determined that the satellite enters the boundary of the measurement and control arc in the management area, send a reset instruction to the measurement and control transponder through the on-board system to trigger the reset of the measurement and control transponder, simultaneously prohibit the autonomous reset function, and clear the working time after the reset of the measurement and control transponder to restart the timing. In this embodiment, when it is determined that the satellite enters the boundary of the measurement and control arc in the national territory area, send a reset instruction to the measurement and control transponder through the on-board system for reset, then prohibit the autonomous reset function, simultaneously clear the working time t after the reset of the measurement and control transponder and start timing, and then monitor the specific value of the working time t after the reset.

[0057] Specifically, step S102 includes: when it is determined that the satellite enters the boundary of the measurement and control arc in the management area, send a reset instruction to the measurement and control transponder through the on-board system; based on the reset instruction, trigger the measurement and control transponder to reset, and simultaneously prohibit the autonomous reset function of the measurement and control transponder; after detecting that the measurement and control transponder is reset, control the working time after the reset of the measurement and control transponder to be cleared and restart the timing.

[0058] S103: When the working time after reset reaches the preset autonomous reset enabling time threshold, re-enable the autonomous reset function. That is, when t is greater than or equal to the autonomous reset enabling threshold t stored in the on-board management system th then enable the autonomous reset function again.

[0059] The value of the autonomous reset enabling time threshold in this embodiment is restricted by the following formula:

[0060] t f +n×T < t th <(n + 1)×T;

[0061] wherein, t th is the autonomous reset enabling time threshold, T is the satellite orbital period, t f is the time for the satellite to pass through the measurement and control arc section of the management area; n is an adjustable non-negative integer used to control the frequency of autonomous reset.

[0062] S104: If the working time after reset reaches the preset maximum reset waiting time threshold, forcibly trigger the reset of the measurement and control transponder through the on-board management system. That is, when t is greater than or equal to the maximum reset waiting time threshold t stored in the on-board management system max then, regardless of whether the autonomous reset function is enabled or disabled at this time, forcibly reset the measurement and control transponder.

[0063] The priority of the on-board management system forcibly triggering the reset of the measurement and control transponder is higher than the triggering condition of the autonomous reset function.

[0064] Refer to Figure 2 , the specific process of this embodiment has a cycle period of 1 second; after a cycle starts, the process points to two branches. One of the branches is to determine whether the autonomous reset function of the measurement and control transponder is enabled: if the autonomous reset function is in the enabled state, first determine whether the GNSS positioning information and the sub-satellite point longitude and latitude information are valid; secondly, determine whether the satellite sub-satellite point longitude and latitude information (longitude α i , latitude β i ) satisfies the following conditions: α 1,0 ≤α i ≤α 2,3 and α 3,0 ≤β i ≤α 4,3 When (satisfying this condition means that the satellite enters the boundary of the measurement and control arc section of the national territory area), if the condition is satisfied, trigger the autonomous reset logic, and the on-board management system immediately sends a reset instruction to reset the measurement and control transponder, then disable the autonomous reset function, and clear the working time t after the reset of the measurement and control transponder. One cycle ends, and then enter the next cycle.

[0065] In another branch, after reset, the working time t is counted. Each time this branch is entered, the value of t is incremented by 1 (equivalent to an increase of 1 s), and the value of t is judged: when t < t th , no processing is performed; when t ≥ t th , the autonomous reset function is set to enabled again. t th is the autonomous reset enable threshold for on-board storage and can be modified by instructions in orbit. The design is as follows: Assume the satellite orbit period is T, and the time for the satellite to pass through the measurement and control arc segment over the national territory is t f , then the value of t th is taken such that t f + n×T < t th < (n + 1)×T, where n = 0, 1, 2, 3......

[0066] Furthermore, the selection of n is as follows: When n = 0 is set, t f < t th < T, which means that the satellite will perform an autonomous reset every time it passes through the national territory. The orbit period of a low-earth orbit satellite is relatively short. The time for the satellite to orbit the earth once generally ranges from 1 hour to 4 hours depending on the orbit altitude, that is, the satellite orbits the earth several times to more than a dozen times within 24 hours a day. This means that the measurement and control transponder will perform an autonomous reset multiple times when passing through the national territory within a day. Therefore, by reasonably setting n, the frequency of autonomous reset can be reduced. For example, when n = 1 is set, t f

[0067] + T < t th < 2T, which means that after the satellite performs an autonomous reset for the first time when passing through the national territory, the autonomous reset function is in the prohibited state when passing through the national territory for the second time, and the measurement and control transponder will not be reset, and will only perform an autonomous reset again when passing through the national territory for the third time. When n = 2, and so on.

[0068] When t ≥ t max , regardless of whether the autonomous reset function is enabled or prohibited at this time, the measurement and control transponder is forcibly reset. t max is the maximum waiting time threshold for resetting the on-board storage and can be modified by instructions in orbit (usually set to a relatively large value such as 24 hours or 48 hours). The purpose of this function is to ensure that when the on-board software cannot trigger the autonomous reset logic for a long time under unexpected circumstances (such as the autonomous reset function being prohibited abnormally for a long time or the sub-satellite point longitude and latitude values being invalid for a long time), the measurement and control transponder can still be reset. When t < t max , a loop ends, and then the next loop is entered.

[0069] Figure 3The autonomous reset system of the TT&C transponder applicable to low-Earth orbit satellites provided in the second embodiment of the present invention is shown. This system includes the satellite bus 1, the TT&C transponder 2, and the GNSS subsystem 3. The satellite bus 1 is a system for handling the working affairs of the satellite. The TT&C transponder 2 includes a TT&C baseband 21 and a reset module 22. Specifically:

[0070] The satellite bus 1 is used to continuously obtain the sub-satellite point longitude and latitude information of the satellite under the condition that the autonomous reset function is enabled, and compare it with the pre-stored longitude and latitude thresholds of the management area TT&C arc segment boundary to determine whether the satellite enters the management area TT&C arc segment boundary. The satellite bus 1 is also used to, when it is determined that the satellite enters the management area TT&C arc segment boundary, trigger the reset of the TT&C transponder by sending a reset instruction to the TT&C transponder, prohibit the autonomous reset function at the same time, and clear the post-reset working time of the TT&C transponder to start re-timing. The satellite bus 1 specifically obtains the position information and orbit information of the satellite through the GNSS subsystem 3 to calculate the sub-satellite point longitude and latitude accordingly. The TT&C transponder 2 is used to re-enable the autonomous reset function when the post-reset working time reaches the preset autonomous reset enable time threshold. The satellite bus system 1 is also used to forcibly trigger the reset of the TT&C transponder 2 if the post-reset working time reaches the preset maximum reset waiting time threshold.

[0071] The autonomous reset system of the TT&C transponder applicable to low-Earth orbit satellites provided in this second embodiment has the same or similar technical effects as those in the first embodiment above. Its specific technical principle is the same as that in the first embodiment above and will not be elaborated here.

[0072] In summary, the present invention solves the abnormal problems of the spaceborne TT&C transponder caused by the space environment through autonomous reset, and makes it return to the normal state. It also judges whether the satellite enters the national territory area TT&C arc segment boundary by detecting the sub-satellite point longitude and latitude of the satellite, and performs autonomous reset on the TT&C transponder before TT&C entry to avoid interruption of normal satellite TT&C due to autonomous reset. In addition, the present invention does not rely on the diagnostic parameters of the transponder itself, and solves the problem in the prior art that when the abnormality has nothing to do with the diagnostic parameters, it cannot be processed and restored.

[0073] The present invention also provides a storage medium for storing a computer program of any one of the Figures 1 to 2 autonomous reset methods of the TT&C transponder applicable to low-Earth orbit satellites. For example, computer program instructions, when executed by a computer, can call or provide the methods and / or technical solutions according to the present invention through the operations of this computer, and can achieve the same technical effects. To avoid repetition, it will not be elaborated here. The program instructions for calling the methods of the present invention may be stored in a fixed or removable storage medium, and / or be transmitted through a data stream in a broadcast or other signal-bearing medium and / or be stored in the storage medium of a computer device running according to the program instructions.

[0074] According to an embodiment of the present invention, the present invention further provides an electronic device 400 as Figure 4 shown. The electronic device 400 may optionally include a storage medium 200 for storing a computer program and a processor 300 for executing the computer program. When the computer program is executed by the processor 300, the autonomous reset method for the TT&C transponder applicable to low-earth orbit satellites described in any one of the above is implemented, triggering the electronic device 300 to execute the methods and / or technical solutions based on the foregoing multiple embodiments, and the same technical effects can be achieved. To avoid repetition, it will not be elaborated here. It should be noted that the electronic devices in the embodiments of the present invention include mobile electronic devices and non-mobile electronic devices.

[0075] It should be noted that the present invention can be implemented in software and / or a combination of software and hardware. For example, it can be implemented using an application-specific integrated circuit (ASIC), a general-purpose computer, or any other similar hardware device. In one embodiment, the software program of the present invention can be executed by a processor to implement the above steps or functions. Similarly, the software program of the present invention (including related data structures) can be stored in a computer-readable recording medium, such as a RAM memory, a magnetic or optical drive, or a floppy disk and the like. In addition, some steps or functions of the present invention can be implemented using hardware, for example, as a circuit that cooperates with the processor to execute each step or function.

[0076] The present invention can be implemented on a computer as a computer-implemented method, or in dedicated hardware, or in a combination of both. The executable code or a part thereof for the method according to the present invention can be stored on a computer program product. Examples of computer program products include memory devices, optical storage devices, integrated circuits, servers, online software, etc. Optionally, the computer program product includes non-temporary program code components stored on a computer-readable medium for executing the method according to the present invention when the program product is executed on a computer.

[0077] In an alternative embodiment, the computer program includes computer program code components suitable for executing all the steps of the method according to the present invention when the computer program runs on a computer. Optionally, the computer program is embodied on a computer-readable medium.

[0078] It should be noted that in this text, the term "comprising", "including" or any other variant thereof is intended to cover non-exclusive inclusion, such that a process, method, article or device comprising a series of elements not only includes those elements but also includes other elements not expressly listed, or further includes elements inherent to such process, method, article or device. Without further limitation, an element defined by the statement "comprising one..." does not exclude the presence of additional identical elements in the process, method, article or device comprising that element. In addition, it should be pointed out that the scope of the methods and devices in the embodiments of the present invention is not limited to performing functions in the order shown or discussed, but may also include performing functions in a substantially simultaneous manner or in the reverse order according to the functions involved. For example, the described methods may be performed in an order different from that described, and various steps may be added, omitted, or combined. Additionally, features described with reference to certain examples may be combined in other examples.

[0079] Of course, the present invention may have many other embodiments. Without departing from the spirit and essence of the present invention, those skilled in the art can make various corresponding changes and modifications according to the present invention, but these corresponding changes and modifications should all fall within the protection scope of the appended claims of the present invention.

Claims

1. A method for autonomously resetting a telemetry and control transponder for a low-orbit satellite, characterized in that: Includes steps: When the autonomous reset function is enabled, the satellite's sub-satellite point longitude and latitude information is continuously obtained through the satellite service system, and compared with the pre-stored longitude and latitude thresholds of the measurement and control arc boundary of the management area to determine whether the satellite has entered the measurement and control arc boundary of the management area; If it is determined that the satellite enters the boundary of the tracking and control arc of the management area, a reset instruction is sent to the tracking and control transponder through the satellite service system to trigger the resetting of the tracking and control transponder, and the autonomous resetting function is disabled at the same time, and the post-reset working time of the tracking and control transponder is reset to zero to restart the timing; When the post-reset working time reaches a preset autonomous reset enabling time threshold, re-enabling the autonomous reset function; If the working time after resetting reaches a preset maximum reset waiting time threshold, the telemetry and control transponder is forcibly triggered to reset through the satellite service system.

2. The autonomous resetting method of the tracking and control transponder applicable to low-orbit satellites according to claim 1 is characterized in that: Before the satellite service system is used to continuously obtain the latitude and longitude information of the sub-satellite point of the satellite and compare it with the pre-stored latitude and longitude thresholds of the measurement and control arc segment boundary of the management area, the method further includes: Select the four most western, eastern, southern and northern ground tracking and control stations in the management area, and use satellite orbit simulation software to calculate the longitude and latitude range of the sub-satellite point corresponding to the visible arc segment of each of the four ground tracking and control stations based on the longitude and latitude of the four ground tracking and control stations and the lowest working elevation angle of the tracking and control antenna, and expand the time margin to form the boundary range of the joint tracking and control arc segment; Based on the boundary range of the joint measurement and control arc segment, the longitude and latitude thresholds of the measurement and control arc segment boundary of the management area are determined and pre-stored in the satellite service system.

3. The autonomous resetting method of the tracking and control transponder applicable to low-orbit satellites according to claim 1 is characterized in that: The value of the autonomous reset enable time threshold is subject to the following formula: t f +n×T<t th <(n+1)×T; Among them, t th is the autonomous reset enabling time threshold, T is the satellite orbit period, t f is the time it takes for the satellite to cross the tracking and control arc of the management area; n is an adjustable non-negative integer used to control the frequency of autonomous reset.

4. The autonomous resetting method of the tracking and control transponder applicable to a low-orbit satellite according to claim 1, characterized in that: The method of continuously acquiring the latitude and longitude information of the sub-satellite point of the satellite through the satellite service system under the condition that the autonomous reset function is enabled, and comparing it with the latitude and longitude thresholds of the measurement and control arc segment boundary of the pre-stored management area to determine whether the satellite enters the measurement and control arc segment boundary of the management area includes: Determine whether the autonomous reset function is enabled; if enabled, continuously obtain the longitude and latitude information of the sub-satellite point of the satellite through the satellite service system, and determine whether the GNSS positioning information and the longitude and latitude information of the sub-satellite point are valid; If valid, the longitude and latitude information of the sub-satellite point will be compared with the longitude and latitude thresholds of the pre-stored management area measurement and control arc boundary. If the longitude and latitude information of the sub-satellite point falls within the longitude and latitude threshold range, it is determined that the satellite enters the management area measurement and control arc boundary.

5. The autonomous resetting method of the tracking and control transponder applicable to low-orbit satellites according to claim 1, characterized in that: If it is determined that the satellite enters the boundary of the tracking and control arc of the management area, sending a reset instruction to the tracking and control transponder through the satellite service system to trigger the resetting of the tracking and control transponder, while disabling the autonomous resetting function, and clearing the post-reset working time of the tracking and control transponder to restart the timing, including: If it is determined that the satellite enters the boundary of the tracking and control arc of the management area, a reset command is sent to the tracking and control transponder through the satellite service system; Based on the reset instruction, trigger the measurement and control transponder to reset, and at the same time disable the autonomous reset function of the measurement and control transponder; After detecting that the measurement and control transponder is reset, the post-reset working time of the measurement and control transponder is controlled to be cleared and restarted.

6. The autonomous resetting method of the tracking and control transponder applicable to low-orbit satellites according to claim 1, characterized in that: The measurement and control arc boundary of the management area is the measurement and control arc boundary of the national land area or the arc boundary of the area jointly covered by measurement and control stations of multiple countries.

7. The autonomous resetting method of the tracking and control transponder applicable to a low-orbit satellite according to claim 1, characterized in that: The priority of the satellite service system forcibly triggering the reset of the tracking and control transponder is higher than the triggering condition of the autonomous reset function.

8. An autonomous reset system for a telemetry and control transponder of a low-orbit satellite, characterized in that: Included are: Satellite service, used to continuously obtain the longitude and latitude information of the sub-satellite point of the satellite under the condition that the autonomous reset function is enabled, and compare it with the longitude and latitude thresholds of the measurement and control arc segment boundary of the pre-stored management area to determine whether the satellite enters the measurement and control arc segment boundary of the management area; The satellite service is further used to trigger the resetting of the tracking and control transponder by sending a reset instruction to the tracking and control transponder when it is determined that the satellite enters the tracking and control arc boundary of the management area, and at the same time prohibit the autonomous reset function, and clear the post-reset working time of the tracking and control transponder to restart the timing; The measurement and control transponder is used to re-enable the autonomous reset function when the working time after the reset reaches a preset autonomous reset enabling time threshold; The satellite service is also used to forcibly trigger the reset of the measurement and control transponder if the working time after the reset reaches a preset reset maximum waiting time threshold.

9. A storage medium, characterized in that: Used to store a computer program for executing the autonomous resetting method of a tracking and control transponder applicable to a low-orbit satellite as described in any one of claims 1 to 7.

10. An electronic device comprising a storage medium, a processor, and a computer program stored in the storage medium and executable on the processor, characterized in that: When the processor executes the computer program, the autonomous resetting method of the tracking and control transponder applicable to a low-orbit satellite according to any one of claims 1 to 7 is implemented.

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