Autonomous Management Method and System for Mars Orbiter without Up-link Fault in Orbit

Abstract

The present invention provides an autonomous management method and system for a Mars orbiter without uplink failures in orbit, including: resetting or powering off and restarting the remote control terminal; resetting or powering off and restarting the transponder; switching the cross-backup channels of the transponder and the receiving antenna; performing main-backup switching processing on the crystal oscillator; autonomously switching the TT&C to the low-gain or medium-gain antenna mode, and at the same time, the spacecraft is in the +X sun-pointing mode and rotates 180° around the +X axis; in the +X sun-pointing mode, switching the receiving antenna back to the omnidirectional low-gain receiving mode; in the omnidirectional low-gain receiving mode, the spacecraft slowly rotates around the +X axis facing the sun; after the above-mentioned processing, if the long-term uplink-free autonomous management process still does not jump out on the spacecraft, power on the UHF relay communication machine to the single-carrier transmission mode; use the locked state of other Mars orbiters or Mars rovers to determine the life and death of the orbiter. The present invention can solve the problem that it is impossible to process through the ground when a failure occurs in the uplink channel.

Description

Technical Field

[0001] The present invention relates to the technical field of autonomous management of detectors, and in particular, to an autonomous management method for a Mars orbiter without uplink failures during long-term operation in orbit, and more particularly, to an autonomous management method and system for a Mars orbiter without uplink failures in orbit. Background Art

[0002] Affected by the ultra-long distance of deep space exploration, it often takes a long time to detect and handle failures of detectors in orbit, especially for TT&C uplink failures, which cannot be processed in time when they occur. In extreme cases, if two uplinks fail simultaneously, the detector cannot receive any instructions from the ground, and the detector will be in an out-of-control state. At this time, the detector needs to autonomously process and recover from the failure according to each possible link where the failure may occur.

[0003] Currently, deep space exploration in China has just started, and there is not much experience to draw on. Near-Earth satellites are not restricted by weight and energy. TT&C and data transmission are designed as independent channels. TT&C only works in one mode. Regular resetting of the receiving channel can timely solve the failures caused by software and space environment of the transponder without changing any current working state of the current transponder. However, Mars detectors are limited by weight and power consumption. TT&C and data transmission usually adopt an integrated design mode. At the same time, TT&C adopts a design mode of multiple encodings, multiple debuggings, and multiple code rates. In the normal working state, it is not possible to regularly reset it to change its current working state.

[0004] The invention patent with the publication number CN106547516A discloses a method and device for controlling the uplink of spacecraft remote control instructions, including: obtaining the input script language; the script language contains keywords corresponding to the types of remote control instructions; identifying the type of remote control instruction corresponding to the script language according to the keywords of the script language; wherein, each type of the remote control instruction corresponds to a keyword, and the types of the remote control instructions include direct instructions, indirect instructions, and data injection; combining the identified type of remote control instruction, parsing the script language according to the preset language rules and performing corresponding operations. This invention does not involve the on-board autonomous management method when there is no uplink failure in orbit.

[0005] The invention patent with the publication number CN107769838B discloses a satellite remote control monitoring system, which includes a hierarchical remote control information format system, a hierarchical transmission and real-time downlink monitoring system of in-satellite remote control information, and a confirmation system for the end of remote control execution. The hierarchical remote control information format system is connected to the hierarchical transmission and real-time downlink monitoring system of in-satellite remote control information, and is used for the gradual transmission of remote control information in the satellite to facilitate the monitoring of the transmission process of monitoring information. And direct instructions and remote control injection numbers can both use this format system, etc. This invention does not involve the on-board autonomous management method when there is no uplink failure in orbit.

[0006] The invention patent with the publication number CN102487343B discloses a method for diagnosing and predicting hidden faults in a satellite communication system. It normalizes heterogeneous data in communication records. For the hidden faults of earth stations in the satellite communication system, SOM is applied to perform clustering analysis on communication record data, classify communication states to form a communication state set, and analyze each communication state set by summarizing fault patterns. By comparing the relationships between different communication state parameters and fault phenomena, meaningful decision rules are summarized through an incremental decision tree algorithm to form a fault rule set. The communication state set and the fault rule set are presented in an interpretable result form, and a prototype system for diagnosing and predicting hidden faults in the satellite communication system is implemented. This invention does not involve the on-orbit autonomous management method of the satellite when there is no uplink fault.

[0007] The invention patent with the publication number CN111319798A discloses an autonomous management method applicable to the propulsion system in Mars exploration. The faults of the propulsion system are divided into attitude control thruster leakage, orbit control pipeline overpressure, pressure reducing valve static pressure overpressure, propulsion system underpressure, and attitude control pipeline overpressure. Among them, the fault handling of attitude control thruster leakage has the highest priority, and the other four fault handling priorities are the same and are processed in sequence according to the time sequence of fault occurrence. The autonomous management method for attitude control thruster leakage is to switch the current thruster to other thrusters; the autonomous management method for orbit control pipeline overpressure is to perform opening and closing actions on the valves on the orbit control pipeline; the autonomous management method for pressure reducing valve static pressure overpressure is to reduce the static pressure of the pressure reducing valve through gas path pressure balance; the autonomous management method for propulsion system underpressure is to pressurize the storage tank; the autonomous management method for attitude control pipeline overpressure is to relieve the pressure of the attitude control pipeline. Summary of the Invention

[0008] Aiming at the defects in the prior art, the present invention provides an on-orbit autonomous management method and system for a Mars orbiter without uplink faults.

[0009] According to the on-orbit autonomous management method and system for a Mars orbiter without uplink faults provided by the present invention, the solution is as follows:

[0010] In a first aspect, an on-orbit autonomous management method for a Mars orbiter without uplink faults is provided. The method includes:

[0011] Step S1: Reset or power off and restart the remote control terminal, and determine whether the uplink is restored. If it is restored, exit; otherwise, proceed to the next step;

[0012] Step S2: Reset or power off and restart the transponder, and determine whether the uplink is restored. If it is restored, exit; otherwise, proceed to the next step;

[0013] Step S3: Switch the cross-backup channel of the answering machine and the receiving antenna, and determine whether the uplink is restored. If it is restored, exit; otherwise, proceed to the next step;

[0014] Step S4: Perform main-backup switching processing on the crystal oscillator, and determine whether the uplink is restored. If it is restored, exit; otherwise, proceed to the next step;

[0015] Step S5: The measurement and control autonomously switches to the low-gain or medium-gain antenna mode. At the same time, the integrator performs the +X sun-pointing mode and rotates 180° around +X, and determine whether the uplink is restored. If it is restored, exit; otherwise, proceed to the next step;

[0016] Step S6: In the +X sun-pointing mode, switch the receiving antenna back to the omnidirectional low-gain receiving mode, and determine whether the uplink is restored. If it is restored, exit; otherwise, proceed to the next step;

[0017] Step S7: In the omnidirectional low-gain receiving mode, the integrator slowly rotates around +X to face the sun, and determine whether the uplink is restored. If it is restored, exit; otherwise, proceed to the next step;

[0018] Step S8: After all the above-mentioned steps of processing, if the long-time no uplink autonomous management process still does not jump out on the spacecraft, turn on the UHF relay communication machine to the single-carrier transmission mode;

[0019] Step S9: Use the locked state of other Mars orbiters or rovers to determine the life and death of the orbiter.

[0020] Preferably, the processing flow of autonomous management follows the principle of first soft then hard, and first processes relatively high-probability events and then processes low-probability events.

[0021] Preferably, after any link of autonomous management processing on the spacecraft, wait for T hours and then perform the autonomous processing of the next link.

[0022] Preferably, the waiting time of T hours is dynamically adjusted according to the communication delay between the spacecraft and the ground.

[0023] Preferably, during the autonomous processing of the no uplink fault, the ground continuously sends test commands. After the spacecraft stably receives the test commands, the long-time no uplink fault autonomous management process will jump out.

[0024] In a second aspect, a Mars orbiter on-orbit no uplink fault autonomous management system is provided, and the system includes:

[0025] Module M1: Reset or power cycle restart the remote control terminal, and determine whether the uplink is restored. If it is restored, exit; otherwise, proceed to the next step;

[0026] Module M2: Reset or power cycle restart the answering machine, and determine whether the uplink is restored. If it is restored, exit; otherwise, proceed to the next step;

[0027] Module M3: Switch the cross-backup channel of the responder and the receiving antenna, determine whether the uplink is restored. If restored, exit. Otherwise, proceed to the next step;

[0028] Module M4: Perform the main-backup switching process on the crystal oscillator, determine whether the uplink is restored. If restored, exit. Otherwise, proceed to the next step;

[0029] Module M5: The measurement and control independently switches to the low-gain or medium-gain antenna mode. At the same time, the integrator performs the +X sun-pointing mode and rotates 180° around +X, determine whether the uplink is restored. If restored, exit. Otherwise, proceed to the next step;

[0030] Module M6: In the +X sun-pointing mode, switch the receiving antenna back to the omnidirectional low-gain receiving mode, determine whether the uplink is restored. If restored, exit. Otherwise, proceed to the next step;

[0031] Module M7: In the omnidirectional low-gain receiving mode, the integrator slowly rotates around +X towards the sun, determine whether the uplink is restored. If restored, exit. Otherwise, proceed to the next step;

[0032] Module M8: After all the above steps of processing, if the long-time no uplink autonomous management process still has not been exited on the spacecraft, turn on the UHF relay communication machine to the single-carrier transmission mode;

[0033] Module M9: Use the locked states of other Mars orbiters or rovers to determine the life and death of the orbiter.

[0034] Preferably, the processing flow of autonomous management follows the principle of first soft then hard, and processes relatively high-probability events first and then low-probability events.

[0035] Preferably, after any link of autonomous management processing on the spacecraft, wait for T hours and then perform the autonomous processing of the next link.

[0036] Preferably, the waiting time of T hours is dynamically adjusted according to the communication delay between the spacecraft and the ground.

[0037] Preferably, during the autonomous processing of the no uplink fault, the ground continuously sends test commands. After the spacecraft stably receives the test commands, the long-time no uplink fault autonomous management process is exited.

[0038] Compared with the prior art, the present invention has the following beneficial effects:

[0039] 1. According to the probability of the occurrence of the fault and the principle of first soft then hard, the present invention performs the autonomous processing and recovery of the possible fault links on the spacecraft in sequence, solves the problem that the ground cannot handle the uplink fault, and thus restores the uplink remote control channel;

[0040] 2. The present invention is not only applicable to the autonomous management design of long-term non-uplink failures of Mars probes, but can also be applied to the design of subsequent deeper space probes. BRIEF DESCRIPTION OF THE DRAWINGS

[0041] Other features, objects, and advantages of the present invention will become more apparent by reading the following detailed description of non-limiting embodiments with reference to the accompanying drawings:

[0042] Figure 1 Schematic diagram of the measurement and control uplink receiving channel for the Mars orbiter;

[0043] Figure 2 Schematic diagram of the autonomous management method for faults. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0044] The present invention will be described in detail below with reference to specific embodiments. The following embodiments will help those skilled in the art to further understand the present invention, but do not limit the present invention in any form. It should be noted that for those of ordinary skill in the art, without departing from the concept of the present invention, several changes and improvements can still be made. These all fall within the protection scope of the present invention.

[0045] An embodiment of the present invention provides an autonomous management method for non-uplink failures of a Mars orbiter in orbit. According to the probability of failure and the principle of soft-first and hard-second processing, autonomous processing and recovery of possible failure links are sequentially performed on the spacecraft, and at the same time, the ground continuously sends test commands. After any link is processed, wait for a period of time. If a valid signal is received by the uplink channel, the autonomous processing of the failure is stopped. Refer to Figure 1 as shown Figure 1 is a schematic diagram of the uplink channel, and the method can perform fault processing on each link affecting the uplink channel.

[0046] Specifically, referring to Figure 2 as shown, for the failure of the Mars orbiter without uplink during the long-term flight stage, in order to prevent the orbiter from being out of control when the uplink fails, an autonomous management method for long-term non-uplink failures is designed. According to the probability of failure and the principle of soft-first and hard-second processing, autonomous processing and recovery of the failure links are performed in sequence, and at the same time, the ground continuously sends test commands. After any link is processed, wait for a period of time. If the remote control terminal modules A and B receive a valid signal, the autonomous management program for long-term non-uplink failures will automatically exit, and the orbiter will maintain the current state and receive ground commands. The method includes the following steps:

[0047] Step S1: For the failure of the remote control terminal, reset or power off and restart the remote control terminal;

[0048] Reset or power off and restart the remote control terminal, and determine whether the uplink is restored. If it is restored, exit; otherwise, execute the next step.

[0049] Step S2: For the fault of the transponder receiving channel, reset the transponder or power it off and restart it.

[0050] Reset the transponder or power it off and restart it, and determine whether the uplink is restored. If it is restored, exit; otherwise, proceed to the next step.

[0051] Step S3: For the fault of the entire RF receiving channel, switch the cross-backup channels of the transponder and the receiving antenna.

[0052] Switch the cross-backup channels of the transponder and the receiving antenna, and determine whether the uplink is restored. If it is restored, exit; otherwise, proceed to the next step.

[0053] Step S4: For the fault of the transponder crystal oscillator, perform the main-backup switching process on the crystal oscillator.

[0054] Perform the main-backup switching process on the crystal oscillator, and determine whether the uplink is restored. If it is restored, exit; otherwise, proceed to the next step.

[0055] Step S5: For the fault of the entire spacecraft attitude, the TT&C autonomously switches to the low-gain or medium-gain antenna mode. At the same time, the spacecraft performs the +X sun-pointing mode and rotates 180° around the +X axis, and determine whether the uplink is restored. If it is restored, exit; otherwise, proceed to the next step.

[0056] Step S6: In the +X sun-pointing mode, switch the receiving antenna back to the omnidirectional low-gain receiving mode, and determine whether the uplink is restored. If it is restored, exit; otherwise, proceed to the next step.

[0057] Step S7: In the omnidirectional low-gain receiving mode, the spacecraft slowly rotates around the +X axis towards the sun, and determine whether the uplink is restored. If it is restored, exit; otherwise, proceed to the next step.

[0058] Step S8: After all the above steps of processing, if the long-term no-uplink autonomous management process still does not jump out on the spacecraft, power on the UHF relay communication machine to the single-carrier transmission mode.

[0059] Step S9: Carry out international cooperation and use the locked state of the Mars orbiter or Mars rover of other countries to determine the life and death of the orbiter.

[0060] Among them, the processing flow of autonomous management follows the principle of first soft then hard, that is, first perform software reset and then perform hardware switching. And according to the probability of the occurrence of the fault, first handle the relatively high-probability events and then handle the low-probability events. After any link of autonomous management processing on the spacecraft, wait for T hours (dynamically adjusted according to the spacecraft-ground communication delay), and then perform the autonomous processing of the next link.

[0061] During the autonomous processing of the uplink fault, the ground continuously sends test commands. After the spacecraft stably receives the test commands, it exits the long-term uplink fault-free autonomous management process.

[0062] Working principle: After a long time without uplink on the spacecraft, it autonomously conducts fault autonomous management. In the case of not receiving uplink commands, it successively performs the following fault handling operations:

[0063] Operation 1: Reset the remote control terminal or power it off and restart.

[0064] Operation 2: Reset the transponder or power it off and restart.

[0065] Operation 3: Switch the cross-backup channels of the transponder and the receiving antenna.

[0066] Operation 4: Perform the main-backup switching process on the crystal oscillator.

[0067] Operation 5: The TT&C autonomously switches to the low-gain or medium-gain antenna mode, and at the same time, the entire spacecraft enters the +X sun-pointing mode and rotates 180° around +X.

[0068] Operation 6: In the +X sun-pointing mode, switch the receiving antenna back to the omnidirectional low-gain receiving mode.

[0069] Operation 7: In the omnidirectional low-gain receiving mode, the spacecraft slowly rotates around +X towards the sun; after all the above steps of processing, if the spacecraft still does not exit the long-term uplink fault-free autonomous management process, turn on the UHF relay communication machine to the single-carrier transmission mode, and use the locked state of other Mars orbiters or Mars rovers to determine the life and death of the orbiter.

[0070] The embodiment of the present invention provides a method and system for autonomous management of in-orbit uplink faults of a Mars orbiter. By autonomously processing and troubleshooting each fault point in all links affecting the uplink channel one by one, it solves the problem that the ground cannot handle the uplink channel fault. The present invention is not only applicable to Mars exploration missions, but also more applicable to subsequent deep space exploration missions beyond.

[0071] Those skilled in the art know that, in addition to implementing the system and its various devices, modules, and units provided by the present invention in the form of pure computer-readable program code, it is entirely possible to achieve the same functions by logically programming the method steps so that the system and its various devices, modules, and units provided by the present invention are implemented in the form of logic gates, switches, application-specific integrated circuits, programmable logic controllers, and embedded microcontrollers, etc. Therefore, the system and its various devices, modules, and units provided by the present invention can be considered as a kind of hardware component, and the devices, modules, and units included therein for implementing various functions can also be regarded as the structures within the hardware component; it can also be considered that the devices, modules, and units for implementing various functions are both software modules for implementing the method and the structures within the hardware component.

[0072] The specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the above specific embodiments, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Without conflict, the embodiments of the present application and the features in the embodiments can be combined with each other arbitrarily.

Claims

1. An autonomous management method for a Mars orbiter without uplink failures in orbit, characterized in that, Including: Step S1: Reset the remote control terminal or power it off and restart it, and determine whether the uplink is restored. If it is restored, exit; otherwise, proceed to the next step. Step S2: Reset the transponder or power it off and restart it, and determine whether the uplink is restored. If it is restored, exit; otherwise, proceed to the next step. Step S3: Switch the cross-backup channel of the transponder and the receiving antenna, and determine whether the uplink is restored. If it is restored, exit; otherwise, proceed to the next step. Step S4: Perform the main-backup switching process on the crystal oscillator, and determine whether the uplink is restored. If it is restored, exit; otherwise, proceed to the next step. Step S5: The TT&C autonomously switches to the low-gain or medium-gain antenna mode, and at the same time, the integrator performs the +X sun-pointing mode and rotates 180° around +X, and determine whether the uplink is restored. If it is restored, exit; otherwise, proceed to the next step. Step S6: In the +X sun-pointing mode, switch the receiving antenna back to the omnidirectional low-gain receiving mode, and determine whether the uplink is restored. If it is restored, exit; otherwise, proceed to the next step. Step S7: In the omnidirectional low-gain receiving mode, the integrator slowly rotates around +X for sun-pointing, and determine whether the uplink is restored. If it is restored, exit; otherwise, proceed to the next step. Step S8: After all the above-mentioned steps of processing, if the long-time no uplink autonomous management process still does not jump out on the spacecraft, turn on the UHF relay communication machine to the single-carrier transmission mode. Step S9: Use the locked states of other Mars orbiters or rovers to determine the life and death of the orbiter.

2. The autonomous management method for on-orbit no-uplink-failure of the Mars orbiter according to claim 1, wherein The processing flow of autonomous management follows the principle of first soft then hard, and first processes relatively high-probability events and then processes low-probability events.

3. The on-orbit autonomous management method for the Mars orbiter without uplink failures according to claim 1, characterized in that, After any link of autonomous management processing on the spacecraft, wait for T hours and then perform the autonomous processing of the next link.

4. The on-orbit autonomous management method for a Mars orbiter without uplink failures according to claim 3, wherein, The waiting time of T hours is dynamically adjusted according to the spacecraft-ground communication delay.

5. The autonomous management method for on-orbit no-uplink-failure of the Mars orbiter according to claim 1, characterized in that, During the autonomous processing of the no uplink fault, the ground continuously sends test commands. After the spacecraft stably receives the test commands, the long-time no uplink fault autonomous management process will jump out.

6. An autonomous management system for on-orbit non-uplink failures of a Mars orbiter, characterized in that, Including: Module M1: Reset the remote control terminal or power it off and restart it, and determine whether the uplink is restored. If it is restored, exit; otherwise, proceed to the next step. Module M2: Reset the transponder or power it off and restart it, and determine whether the uplink is restored. If it is restored, exit; otherwise, proceed to the next step. Module M3: Switch the cross-backup channel of the transponder and the receiving antenna, and determine whether the uplink is restored. If it is restored, exit; otherwise, proceed to the next step. Module M4: Perform the main-backup switching process on the crystal oscillator, and determine whether the uplink is restored. If it is restored, exit; otherwise, proceed to the next step. Module M5: The TT&C autonomously switches to the low-gain or medium-gain antenna mode, and at the same time, the integrator performs the +X sun-pointing mode and rotates 180° around +X, and determine whether the uplink is restored. If it is restored, exit; otherwise, proceed to the next step. Module M6: In the +X sun-pointing mode, switch the receiving antenna back to the omnidirectional low-gain receiving mode, and determine whether the uplink is restored. If it is restored, exit; otherwise, proceed to the next step. Module M7: In the omnidirectional low-gain receiving mode, the integrator slowly rotates around +X for sun-pointing, and determine whether the uplink is restored. If it is restored, exit; otherwise, proceed to the next step. Module M8: After all the above-mentioned steps of processing, if there is still no long-term no-uplink autonomous management process on the vehicle, turn on the UHF relay communication machine to the single-carrier transmission mode; Module M9: Use the locked states of other Mars orbiters or rovers to determine the life or death of the orbiter.

7. The autonomous management system for on-orbit no-uplink failure of the Mars orbiter according to claim 6, wherein The processing flow of autonomous management follows the principle of first soft then hard, that is, dealing with relatively high-probability events first and then small-probability events.

8. The autonomous management system for on-orbit no-uplink failure of the Mars orbiter according to claim 6, characterized in that After any link of the vehicle is autonomously managed and processed, wait for T hours and then perform the autonomous processing of the next link.

9. The on-orbit autonomous management system for the Mars orbiter without uplink failures according to claim 8, characterized in that, The waiting time of T hours is dynamically adjusted according to the communication delay between the vehicle and the ground.

10. The autonomous management system for on-orbit no-uplink-failure of the Mars orbiter according to claim 6, characterized in that, During the autonomous processing of no-uplink faults, the ground continuously sends test commands. After the vehicle stably receives the test commands, it will jump out of the long-term no-uplink fault autonomous management process.

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