Control method for VIENNA rectifier of aviation multi-electric engine

Abstract

The invention discloses a control method for a VIENNA rectifier of an aviation multi-electric engine. The control method comprises the following steps: establishing a stationary coordinate system of the VIENNA rectifier and obtaining a mathematical model under a two-phase rotating coordinate system by coordinate transformation; taking a DC side voltage as a control variable, and designing a sliding mode surface based on a global terminal sliding mode theory to design a voltage external loop controller; and taking the DC side voltage and a derivative thereof as input of fuzzy reasoning, and adjusting the sliding mode reaching law in real time according to the output sliding mode in a system state so as to control the DC side voltage. According to the control method disclosed by the invention, the robustness of the system can be improved by virtue of the global terminal sliding mode theory and an error is restrained to be zero within a definite time; the sliding mode reaching law is controlled in real time according to the experience of an expert by virtue of a fuzzy reasoning theory, so that not only is the quickness of system response improved, but also buffeting is effectively weakened.

Description

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AI Technical Summary

Benefits of technology

This patented describes an improved way for regulating voltages used by aircraft engines (VME). By combining certain techniques such as linearity analysis or fuzziness arguments into a new algorithmic framework called VENNINOX®, these technical improvements can improve performance without sacrificing responsiveness. Additionally, the proposed solution uses advanced technology like fuzicing logic and gamma regression to achieve better accuracy over longer periods of operation compared to previous methods. Overall, the current approach provides more efficient ways to manage power systems within modern airplanes.

Problems solved by technology

This patented describes two technical problem addressed in this patents: firstly, there needs to enhance the fastest speed and reliable operation of aircraft gas turbine generators while minimizing their overall weight and volume; secondly, they must have better space allocation within them without adding extra weight or making heavier components than usual ones like lighter airplanes.

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