Simulator for permanent magnet alternating-current generator

Abstract

The invention relates to a simulator for a permanent magnet alternating-current generator. The simulator is used for testing hardware of an aero-engine in a loop, and comprises a permanent magnet alternating-current generator model machine module, a permanent magnet alternating-current generator controller module, and a permanent magnet alternating-current generator actuator module. The permanent magnet alternating-current generator model machine module is provided with a permanent magnet alternating-current generator model and a fault model, wherein the permanent magnet alternating-current generator model and the fault model are real-time mathematical models, and the module outputs a first output signal after processing a first input signal. The first output signal and a second input signal serve as the input signals of the permanent magnet alternating-current generator controller module, and the permanent magnet alternating-current generator controller module outputs a first control signal after processing the input signals. The permanent magnet alternating-current generator actuator module outputs a corresponding second output signal according to the first control signal and outputs a feedback signal used for closed-loop control of the permanent magnet alternating-current generator controller module. The second output signal is the output signal, simulated by the simulator for the permanent magnet alternating-current generator, of the permanent magnet alternating-current generator.

Description

technical field [0001] The invention relates to a permanent magnet alternator simulator, in particular to a permanent magnet alternator simulator used for hardware-in-loop simulation tests of full-authority digital electronic control of aeroengines. Background technique [0002] Modern aero-engine full authority digital electronic control (Full Authority Digital Engine Control: FADEC) has realized electric regulation, that is, the control function of the engine body and the task of cooperating with the aircraft are completed through the electronic controller. In order to meet the power supply requirements of the electronic controller in the airworthiness requirements of the aero-engine, the power supply of the electronic controller must be redundant. The redundancy mainly comes from two aspects: one is the 28V regulated DC power provided by the aircraft; the other is Alternating current provided by a low-power alternator mounted on the engine and driven by a high-voltage sha...

AI Technical Summary

Problems solved by technology

However, this method has the following disadvantages in application: the AC / DC module verification under the fault state of the permanent magnet alternator cannot be carried out due to the lack of short-circuit and disconnection devices; in addition, due to the device limitation of the existing programmable current source, the limit frequency is low , cannot cover all frequency ranges in which permanent magnet alternators operate

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