A power supply control system for aircraft generator power failure test

Abstract

The present invention provides a power control system for an aircraft generator power failure test; the power control box includes a power control box, a control module, and a relay module. The power control box includes an acquisition control card, and the input ports of the acquisition control card are respectively connected to a frequency measurement module, a voltage sensor, and a current sensor. The test system of the present invention adopts an acquisition card with integrated control output and parameter acquisition input, which can reduce the deployment of test resources. In particular, the device can acquire engine speed and synchronize data acquisition with the issuance of control signals, thereby ensuring that the engine completes power supply conversion control in a timely manner during acceleration and deceleration. A fast-response semiconductor field-effect transistor low-voltage drop DC solid-state relay is selected as an actuator for power supply conversion control, which can ensure that the power supply conversion interval control error is ≤1ms, thereby significantly improving the accuracy of power supply conversion interval control.

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