Power Supply Redundancy Design of Aircraft's Electric Braking Electro-Mechanical Actuation System

Abstract

In this paper, a power source redundancy-optimization approach for aircraft electrical brake electromechanical actuation system was proposed. The PWM plus phase-shift (PPS) control method was introduced in Dual active half bridge, which limited the amplitude of transform's leakage inductance current, thus expanding the fluctuation range of input voltage. Then, the voltage gain formula was deduced. By analyzing the leakage current under different phase shift in one period, the average power and root-mean-square (RMS) value of leakage current can be compared. Then, the optimum modulation range of phase shift can be obtained. By analyzing the soft-switching operation in this range, all switches can realize zero-voltage-switching (ZVS). To ensure the output voltage stability and voltage balance across the leakage inductance, a closed loop control method is designed. Finally, a prototype of 28V/270V-1kW was built to verify the theoretical analysis and calculation.