A DC power supply system stability device and method based on virtual resistance compensation

Abstract

A DC power supply system stability compensation device and method based on virtual resistance comprise a three-stage synchronous motor, a rectifier and a rectifier control unit; The three-stage synchronous motor is connected with a rectifier, and the alternating current emitted by the three-stage synchronous motor is changed into direct current after passing through the rectifier and is loaded onboth ends of the load to supply power for the load. The rectifier control unit is connected with the rectifier, and the rectifier control unit includes a compensation signal module, and the compensation signal module generates a dummy resistance equivalent compensation AC voltage signal to be compensated to the rectifier control unit. The device and the method can maintain the stability of the power supply system when the load of the DC power supply system is suddenly increased, and the instability phenomenon does not occur.

Description

technical field [0001] The invention relates to the field of aviation electrical systems, in particular to a device and method for compensating the stability of a DC power supply system based on virtual resistance. Background technique [0002] Power system stability analysis is a necessary part of the overall design of aircraft power system. At present, with the increase of aircraft on-board electrical equipment, especially the extensive use of power electronic converters and motor-driven equipment, the electrical load capacity, type, and grid complexity of multi-electric aircraft are greatly improved compared with traditional aircraft power systems. In multi-electric aircraft, a large number of new electrical loads, such as electric environmental control, electric actuation, and electric anti-icing, are essentially motors controlled by power electronic converters or resistive loads controlled by power electronic converters. The load of a single power electronic converter ...

AI Technical Summary

Problems solved by technology

[0005] In the design of the power system of traditional aircraft, only the voltage, current, capacity, power quality and other performance indicators of the equipment are considered. In order to prevent the occurrence of oscillation instability, generators and converters with large redundancy are used as primary and secondary power sources. , which makes the design margin of the multi-electric aircraft power system equipment too large, resulting in a larger weight and volume of the equipment and a lower power density

Traditional aircraft start from a single device in the design of the power system, and select components according to the performance requirements of the sub-equipment, so the system stability is not considered in terms of requirements

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