Engine performance parameter correction method based on in-orbit data

Abstract

The invention proposes an engine performance parameter correction method based on on-orbit data, and the method comprises the steps: correcting the performance parameters of the engine through the on-orbit actual performance data, thereby facilitating the improving of the analysis level of the on-orbit data, and deepening the understanding of the working performance of an engine. According to the method, the engine performance parameters can be corrected without redundant hardware, the estimation precision of the on-orbit residual propellant can be improved, the prediction precision and orbital transfer efficiency of the on-orbit thrust can be further improved, waste of the propellant can be avoided, and the method has great significance on long-term on-orbit management of subsequent satellites.

Description

technical field [0001] The invention relates to a method for revising engine performance parameters. Background technique [0002] my country's geostationary orbit satellites generally adopt a dual-component unified propulsion system, and are equipped with remote engines and attitude control thrusters. The apogee engine is mainly used to provide thrust for the orbit maneuver of the spacecraft. [0003] During satellite orbital maneuvering, parameters such as the mass of the entire star, the specific impulse of the engine, and thrust are required to formulate an orbit change strategy. Among them, the specific impulse of the engine can be obtained through the engine ground heat scale test, and the engine thrust and the whole star mass need to be introduced into the small deviation equation of the engine. Therefore, the orbit change control effect of the whole satellite and the long-term on-orbit management are closely related to the accuracy of the engine parameters. If the...

AI Technical Summary

Problems solved by technology

If the actual performance of the engine deviates too much, it will not only affect the number of orbit changes, consume unnecessary manpower and material resources, but also cause waste of propellant, which will reduce the life of the satellite and bring inevitable losses

[0004] Since the engine performance parameters are generally given by the small deviation equation near the rated point, there is a certain systematic error in the parameter processing method itself, and the use is limited.

In addition, the working conditions of the engine on orbit are not the same as those of the thermal calibration on the ground, and the accuracy of the thermal calibration on the ground needs to be improved, and there are certain method errors in the parameter conversion between the cold test and the hot test.

Therefore, there are often non-negligible differences between the actual on-orbit performance of the engine and the ground

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