Real-time finding method for abnormal conditions of in-orbit satellite thruster ignition period

Abstract

The invention provides a real-time finding method for abnormal conditions of the in-orbit satellite thruster ignition period. A temperature relative difference model is built by means of in-orbit satellite historical telemeasuring data, and real-time, automatic and accurate monitoring of the thrust ignition process can be achieved by driving and discriminating real-time satellite telemeasuring data. The method comprises the specific steps of firstly, determining whether a satellite is in the position keeping working condition or not, determining two thrusters adopted by the current position keeping working condition, then, building the temperature relative difference model for building and setting an alarm threshold, finally, utilizing data obtained through the temperature relative difference model of the real-time in-orbit telemeasuring data for real-time comparison with the alarm threshold, and performing real-time alarming when the threshold is exceeded. According to the method, thein-orbit monitoring threshold obtained through the relative difference model can find the thrust in-orbit abnormities of the thrusts in real time, precious time is fought for emergency processing ofabnormities, and reliable guarantees are provided for long-term in-orbit stable operation of satellites.

Description

Technical field [0001] The invention relates to a method for real-time discovery of abnormal working conditions, in particular to a method for real-time discovery of abnormal conditions during thruster ignition. Background technique [0002] At present, my country's high-orbit satellite propulsion system adopts a two-component unified propulsion system, and the 10N thruster is the only actuator in the propulsion system that provides thrust. Its normal operation directly determines the success or failure of satellite orbit control and the service life of the satellite in orbit. . The use of 10N thrusters for my country's high-orbit satellites in the synchronous orbit phase is only reflected in two aspects: (1) Position maintenance (2) Momentum wheel unloading. The 10N thruster is not involved in the work at other times. Because it is not working, the performance and status of the 10N thruster on orbit cannot be monitored. At the same time, during the unloading process of the mome...

AI Technical Summary

Problems solved by technology

[0004] There are deficiencies in the above two methods: (1) Generally, the thrust of the paired 10N thrusters used by the satellite in the process of maintaining the position is different, and the installation angle also has deviations. Attitude fluctuations are caused, and if the momentum device of the satellite participates in attitude control during the ignition process of the thruster, the disturbance moment generated by the jet of the thruster will be gradually absorbed by the momentum device, and the abnormal working conditions of the 10N thruster cannot be fully reflected in the attitude fluctuation. The attitude angle change monitoring method cannot find the abnormal working condition of the thruster

(2) Although the evaluation of the orbit measurement results after adopting the position holding control can find the abnormal situation of the 10N thruster, it lacks real-time performance

However, it is still relying on manual interpretation of the temperature trend of the 10N thruster. This interpretation method has the following problems: first, in the face of hundreds of satellites in orbit, it is impossible to complete real-time interpretation manually; second, the conclusion of trend interpretation is heavily dependent on The experience of on-orbit monitoring personnel is not conducive to early detection of failures or performance degradation of 10N thrusters

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