飞机全电刹车机电系统供电电源余度设计  

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

作　　者：相里康[1] 马瑞卿[1] 

机构地区：[1]西北工业大学自动化学院,西安710072

出　　处：《西北工业大学学报》2018年第1期110-116,共7页Journal of Northwestern Polytechnical University

摘　　要：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。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 th tuation range of input voltage. Then, the voltage gain formula was deduced. By analyzing the leakage current different phase shift in one period, the average power and root-mean-square （RMS） value of leakage current e flucunder can be compared. Then, the optimum modulation range of phase shift can be obtained. By analyzing the so.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-lkW was built to verify the theoretical analysis and calculation.

关 键 词：全电刹车 供电电源 余度优化 双有源桥 双向变换器 闭环控制 

分 类 号：V240.2[航空宇航科学与技术—飞行器设计]