Switched Control of Three-Phase Voltage Source PWM Rectifier Under a Wide-Range Rapidly Varying Active Load

Switched Control of Three-Phase Voltage Source PWM Rectifier Under a Wide-Range Rapidly Varying Active Load
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DOI:
10.1109/tpel.2010.2095507
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发表时间:
2012-02
影响因子:
6.7
通讯作者:
Wei Zhang-;Yanze Hou;Xinbo Liu;Yuanjun Zhou
Wei Zhang-;Yanze Hou;Xinbo Liu;Yuanjun Zhou
中科院分区:
工程技术1区
文献类型:
--
作者:
Wei Zhang-;Yanze Hou;Xinbo Liu;Yuanjun Zhou

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飞机电动执行机构是未来电动飞机最重要的电气负载之一。飞机电动舵机的功率特性具有大范围快速变化的特点,在小信号意义上表现为恒功率负载特性。为了解决三相电压型脉宽调制整流器(VSR)在动态负载下的灵活调压问题,提出了一种基于串联结构的三相电压型脉宽调制整流器(VSR)直流母线电压切换控制方法。在VSR的不同工作点上设计了多个线性控制器,并根据一定的切换规律在VSR系统上实现了一个控制器。基于公共Lyapunov函数方法,保证了所提出的控制方法的稳定性。仿真和实验结果表明,在宽范围快变负载的情况下,VSR的调压控制效果良好。与经典的PI控制器相比,在飞机电动舵机负载的控制过程中,所设计的开关控制器可以显著地减小直流母线电压的跌落,并在一定程度上减小直流母线电压的超调量。
The aircraft electric actuator is one of the most important kind of electric loads of the future more electric aircraft. The power characteristic of an aircraft electric actuator possesses the feature of rapidly varying in a wide range, and it shows constant power load nature in the small-signal sense. In this paper, a novel dc-bus voltage switched control method of three-phase voltage source pulsewidth-modulated rectifiers (VSRs), which aims to solve the problem of flexible voltage regulating under dynamic loads, is proposed under a cascade structure in rotating synchronous coordinates d-q . Several linear controllers are designed on different operating points of the VSR, and one controller is implemented on the VSR system according to certain switching law. The stability of the proposed control approach is guaranteed based on the common Lyapunov function method. Simulation and experimental results show that the desired control performance is obtained in the voltage regulating of a VSR with wide-range rapidly varying load. Compared with a classical PI controller, the derived switched controller can achieve a considerable reduction in the dip of the dc-bus voltage and a certain reduction in the overshoot of the dc-bus voltage during the control process under an aircraft electric actuator load.