CN-122009529-A - Quick restarting space electric propulsion method and system based on hardware layering protection

Abstract

The invention provides a quick restarting space electric propulsion method and a system based on hardware layering protection, comprising the steps of monitoring the running state of an electric thruster, and acquiring abnormal information if the running state is abnormal; and performing the corresponding processing based on the grading of the overcurrent protection. The invention solves the technical problems of lag in protection response, low restarting efficiency and manual troubleshooting when the electric thruster generates transient high-current pulse in the prior art.

Inventors

• CHEN XING
• ZHANG BO
• ZHU XIAOYU
• JIN YIZHOU
• ZHOU JI
• SUN JIANGHONG
• LIU RAN

Assignees

• 上海空间推进研究所

Dates

Publication Date

20260512

Application Date

20260109

Claims (10)

1. 1. The quick restart space electric propulsion method based on hardware layering protection is characterized by comprising the following steps of: step S1, monitoring the operation state of the electric thruster, if the operation state is normal, continuously maintaining monitoring, and if the operation state is abnormal, acquiring abnormal information; step S2, based on the abnormal information, performing hierarchical overcurrent protection; And step S3, based on the grading of the overcurrent protection, carrying out corresponding processing.
2. 2. The method according to claim 1, wherein in the step S1, the operation state includes an operation current, and the abnormality information includes the operation current exceeding a preset threshold.
3. 3. The method according to claim 2, wherein the step S2 comprises: s2.1, if the primary side working current exceeds a preset threshold value, cutting off the primary side power supply to flameout the electric thruster; and S2.2, if the working current of the secondary side exceeds a preset threshold value, cutting off the power supply of the secondary side, and extinguishing the electric thruster.
4. 4. A method according to claim 3, wherein said step S3 comprises: step S3.1, if the primary side power supply is detected to be disconnected, executing shutdown; And S3.2, if the secondary side power supply is detected to be disconnected, further detection is carried out, if the detection is normal, the electric thruster is restarted, and if the detection is abnormal, shutdown is carried out.
5. 5. The method of claim 4, wherein the substep S3.2 further comprises determining whether the number of firings at the current operation exceeds a predetermined threshold, and determining whether the pressure of the propellant in the propellant supply exceeds the predetermined threshold.
6. 6. The method of claim 4, wherein restarting the electric thruster comprises: And recovering the power supply of the secondary side, setting the cathode heating power supply current, the contact electrode power supply voltage, the anode power supply voltage and the like of the electric thruster as quick starting parameter values, starting the power supply, and restarting the electric thruster.
7. 7. A hardware layered protection based fast restart spatial electric propulsion system, comprising: The module M1 is used for monitoring the running state of the electric thruster, if the running state is normal, continuing to monitor, and if the running state is abnormal, acquiring abnormal information; a module M2 for performing hierarchical overcurrent protection based on the abnormality information; And a module M3, carrying out corresponding processing based on the grading of the overcurrent protection.
8. 8. The system according to claim 1, wherein in the module M1, the operation state includes an operation current, and the abnormality information includes the operation current exceeding a preset threshold.
9. 9. The system according to claim 2, wherein the module M2 comprises: if the primary side working current exceeds a preset threshold value, the primary side power supply is disconnected, and the electric thruster is flameout; and the sub-module M2.2 is used for disconnecting the secondary side power supply and extinguishing the electric thruster if the secondary side working current exceeds a preset threshold value.
10. 10. A system according to claim 3, wherein the module M3 comprises: if the primary side power supply is detected to be disconnected, the sub-module M3.1 executes shutdown; And the sub-module M3.2 is used for further detecting if the secondary side power supply is disconnected, restarting the electric thruster if the secondary side power supply is detected to be normal, and executing shutdown if the secondary side power supply is detected to be abnormal.

Description

Quick restarting space electric propulsion method and system based on hardware layering protection Technical Field The invention relates to the technical field of spacecraft electric propulsion systems, in particular to a quick restarting space electric propulsion method and system based on hardware layering protection. Background In the field of space propulsion, compared with a traditional propulsion system taking chemical energy as a core, an electric propulsion system accelerates propulsion particles by utilizing electric energy, so that the limitation of the energy density of the propellant is broken through, and the electric propulsion system has the characteristics of high specific impulse, long service life, smaller thrust and high control precision, and has become an important means for a spacecraft to execute long-life and fine orbit control tasks. However, after a long-term cumulative ignition of the electric thruster, it may exhibit sporadic discharge disturbances during operation, which appear as short and large-magnitude current drastic changes, possibly accompanied by the generation of red-hot splatters. The pulse appears in a probability way, the amplitude and the pulse width of the pulse are uncertain, if the pulse is too severe, the abnormal flameout of the thruster is caused, the unexpected stopping control of the electric propulsion system is caused, the orbit control efficiency of the spacecraft is reduced, and the stability of the primary power supply of the spacecraft is possibly influenced when the pulse is severe. As a key power supply device of an electric propulsion system, a power processing unit is generally provided with a plurality of safety mechanisms such as fuse protection, limited power protection, primary overcurrent protection and the like. The response time of these protection measures has significant limitations in that fuse protection typically requires large currents lasting tens of seconds, power limited protection is on the order of seconds in time scale, and transient high current pulses occurring on the order of microseconds are difficult to suppress in time. Although the primary overcurrent protection can act on transient pulses, feedback information is limited, and specific fault types and trigger reasons are difficult to reflect. In order to avoid abnormal rail control caused by misjudgment, the conventional electric propulsion system generally needs to manually carry out fault diagnosis after overcurrent protection is triggered, and the fault diagnosis comprises state inspection of a storage and supply unit, circuit state self-inspection, power processing unit passage self-inspection and the like. The process takes a long time, only a self-checking process needs a few minutes, the restarting of the thrusters is delayed, the cathode temperature is reduced, the ignition time is prolonged, and the rail control efficiency is reduced. Thus, in most cases, the rail control process is passively terminated by the triggering of the over-current protection. The existing spacecraft uses an electric propulsion system to execute the track control process generally comprises the links of instruction issuing, system preparation, ignition, state monitoring and the like. The track control is completed smoothly when the system state is normal continuously, and the ignition is terminated immediately if the system state is abnormal, as shown in fig. 4. Because the abnormal state can be confirmed only after the ground analysis and telemetry, fault identification is delayed, track compensation time and an ignition window need to be repeatedly calculated, and then the machine selection is performed again to execute track control, so that the task efficiency is affected. The Chinese patent application number CN202411431244.5 provides a secondary autonomous restarting method of an ion electric propulsion system, by monitoring screen grid current or accelerating current, single flickering, hardware autonomous restarting or software autonomous restarting processes are sequentially executed, beam reconstruction is realized, whether restarting is successful or not is judged, but the scheme is mainly based on flow control, and quick countermeasure on a hardware level is not provided for the problem of protection response lag brought by microsecond transient pulse. In summary, the prior art has significant drawbacks in coping with the rapid abnormal response of the electric propulsion system, shortening the restarting time and reducing the burden of manual troubleshooting, and an improved scheme capable of realizing rapid protection and rapid restarting at the hardware level is needed. Disclosure of Invention Aiming at the defects in the prior art, the invention aims to provide a quick restarting space electric propulsion method and system based on hardware layering protection. According to the method for quickly restarting space electric propulsion based on hardware layered protection, th