In this paper,a power source redundancy-optimization approach for aircraft electrical brake electrome-chanical 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 fluc-tuation 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 op-eration 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.%提出了一种飞机全电刹车机电系统供电电源余度设计方法,在双有源半桥隔离双向DC-DC变换器的基础上采用PWM加移相控制方法,限制了不同输入电压下变压器漏感电流幅值,从而扩大了输入电压的波动范围.推导了输出增益公式,通过分析不同相位差下,一个周期内的漏电流,得出了不同相位差下输出平均功率和漏电流均方根值,并通过对比两者的关系,得出了相位差的最佳调制范围.通过分析该范围内的软开关情况,得出所有开关管,均可实现零电压开通.为了确保电压稳定以及漏电感两端电压平衡,设计了闭环控制方法,通过调节PWM占空比控制输出电压,利用相位差平衡了漏电感两端的电压,可抑制输出功率波动对输出电压的影响.设计了1台28 V/270 V功率1 kW的原理样机,验证了理论分析和计算的正确性.
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