Abstract
This article presents a control scheme for a recently reported aircraft advanced power generation center (APGC) during postfault operation conditions. Within the APGC, two electrical generators extract power from two separate engine shafts and supply electrical power to a common high-voltage direct current (HVDC) bus through their dedicated main ac/dc power converters. An extra back-to-back (BTB) converter is also used to connect the ac terminals of the two generators. This architecture provides merits of fault tolerance capabilities of the APGC. In the case of main ac/dc power converter failure, the system can be reconfigured and the BTB converter provides an extra power flow path from the generators to the HVDC bus. This ensures electrical power generation capabilities onboard. This article discusses in detail about the control of the APGC under fault conditions with one main ac/dc converter failure. A seamless transition scheme from normal operation to postfault conditions is proposed using a voltage command initialization technique within the BTB converter. Both experimental and simulation results have verified the fault tolerance improvement and control performances of the APGC.
Highlights
The more-electric aircraft (MEA) concept is a major trend in the modern aerospace industry due to the advantages of high efficiency, low maintenance cost, and benefits to the environment
In stage 2, the electronic load (E-load) performs as a constant power load (CPL), consuming an extra 550W power
In stage 3 where the pulse-width modulation (PWM) signals for the HPR are disabled, idcHP falls to zero and idcLP is doubled
Summary
The more-electric aircraft (MEA) concept is a major trend in the modern aerospace industry due to the advantages of high efficiency, low maintenance cost, and benefits to the environment. As a result the electric power demand increases significantly and this introduces challenges in designing a suitable electrical power generation center (PGC) [1]. An electrical generator is coupled with the engine high-pressure spool (HPS) due to its relatively constant speed [2]. With the increase of electrical loads onboard, this single-generator structure has difficulty in meeting the increased electrical power demand of the MEA. Electrical power extracted from the engine HPS is limited as excessive power extraction will undermine the efficiency and stability of the engine [3]
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