期刊
IEEE TRANSACTIONS ON INDUSTRIAL ELECTRONICS
卷 70, 期 4, 页码 3449-3460出版社
IEEE-INST ELECTRICAL ELECTRONICS ENGINEERS INC
DOI: 10.1109/TIE.2022.3176309
关键词
Capacitor voltage balance; common-mode voltage (CMV); coordinate-based hybrid modulation; more-electric-aircraft (MEA); three-level topology
In this article, a hybrid active modulation approach is proposed to tackle the challenges faced by conventional pulsewidth modulation (PWM) strategies in the aircraft electric starter/generator system. The proposed approach includes coordinate-based PWM for startup process and enhanced carrier-based virtual-space-vector modulation technique for generation mode. Bias-offset injection in the time and voltage domain is used to maintain balanced capacitor voltages. Simulation and experimental results obtained from a test rig validate the effectiveness of the presented algorithm.
In the aircraft electric starter/generator system, the three-level neutral-point-clamped converters play a crucial role in driving turbofan engines and delivering onboard electrical power. However, the conventional pulsewidth modulation (PWM) strategies face the challenge of capacitor voltage deviation, large common-mode voltage (CMV), and extra switching losses. Regarding the characteristics of the studied wide-speed range aerospace drives, the modulation scheme needs to be designed according to its operating conditions. To tackle the above demerits, a hybrid active modulation approach is, hence, proposed in this article. By the coordinate-based PWM, the nearest-three-vector is used in the startup process as the neutral-point (NP) voltage balance can be realized with fewer switching intervals; when the drives run in generation mode, an enhanced carrier-based virtual-space-vector modulation technique is involved, which aims to eliminate NP voltage fluctuation, suppress CMV, and simplify the modulation process. With the help of bias-offset injection in the time and voltage domain, capacitor voltages can be effectively kept at a balanced state even though the imbalance exists. The validity of the presented algorithm is proved by simulation and experimental results obtained from a 45 kW, 32 kr/min aircraft starter/generator test rig.
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