Abstract
This paper proposes a capacitor voltage regulation method for the dual converter with a floating bridge for aerospace applications. This topology has previously been reported, but with a constrained voltage utilization factor due to the need for capacitor voltage regulations. In this paper, the effect of switching states on the voltage variation of capacitor is quantitatively modeled and an enhanced space vector modulation scheme with current feedback is proposed to achieve an active control of the floating capacitor voltages. This proposed method also allows further exploitation and utilization of converter voltage. The relationship between the allowed modulation index of dual converter and load power factor is obtained and expressed using a fitted polynomial equation. The advantages of the proposed method include boosted voltage utilization and superior performance in term of capacitor voltage balance. These advantages have been proven through simulation and experimental results on RL loads as well as with an open-end winding induction motor. The proposed modulation scheme can boost the converter voltage utilization by at least 10% while achieving full four-level operation. More importantly, the higher available voltage allows extending the constant torque region of the motor, the further beginning of field weakening operation could be postponed.
Highlights
A S to the push towards more electric aircraft (MEA) intensifies, aerospace systems are undergoing a transition from hydraulic, mechanical, and pneumatic power system into an integrated electric power system [1]–[3]
The MEA initiative can offer significant improvements in terms of the system efficiency and weight loss while reducing costs and emissions [4]–[6]. Considering this scenario, electromechanical actuators (EMAs) for flight control surface represent a key aspect of the MEA concept [7]
For a certain modulation index (M.I.) and a power factor (PF) angle, if |Qfc typeI | is larger than |Qfc typeII |, this means the charge caused by type II vector can be fully compensated by the charge resulted from type I vector over a fundamental cycle
Summary
A S to the push towards more electric aircraft (MEA) intensifies, aerospace systems are undergoing a transition from hydraulic, mechanical, and pneumatic power system into an integrated electric power system [1]–[3]. The first configuration (No.1) is capable of multilevel operation but it needs a bulky transformer to achieve isolation [18], [19] This would increase the volume and weight of system significantly, which is not desired in aerospace applications. According to conclusions in [18], [26], [27], due to the limitation of voltage regulation and achieving multilevel operation at the same time, the voltage utilisation of this dual converter configuration is constrained to the DC-link voltage. Under this condition, the capacitor voltage, which can be substantially beneficial for aerospace applications, is underutilised. These undesirable voltage steps would deteriorate output performance, which makes this configuration less attractive
Sign-in/Register to view highlights & summary Sign-in/Register to access full text options 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
