A Stable and Robust DC Power System for More Electric Aircraft

Mirzaeva, Galina; Miller, Dmitry; Goodwin, Graham C.; Wheeler, Patrick

doi:10.1109/ecce47101.2021.9595813

Cited by 4 publications

(1 citation statement)

References 13 publications

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“…So far as MEAs are concerned, a DC distribution system appears to be the best choice. After a thorough literature review in regards to the points mentioned above, the most suitable electric power system architecture for a More Electric Aircraft seems to be a DC power system (as compared to a constant voltage/constant frequency, constant voltage/variable frequency power system) owing to its better system stability and small size (Mirzaeva et al , 2021; Lin et al , 2021).…”

Section: Introductionmentioning

confidence: 99%

Implementation and performance analysis of a novel sliding mode controller for bidirectional DC to DC converter in aircraft application

Karvekar¹,

Joshi²

2023

WJE

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Purpose The purpose of this paper is to implement a closed loop regulated bidirectional DC to DC converter for an application in the electric power system of more electric aircraft. To provide a consistent power supply to all of the electronic loads in an aircraft at the desired voltage level, good efficiency and desired transient and steady-state response, a smart and affordable DC to DC converter architecture in closed loop mode is being designed and implemented. Design/methodology/approach The aircraft electric power system (EPS) uses a bidirectional half-bridge DC to DC converter to facilitate the electric power flow from the primary power source – an AC generator installed on the aircraft engine’s shaft – to the load as well as from the secondary power source – a lithium ion battery – to the load. Rechargeable lithium ion batteries are used because they allow the primary power source to continue recharging them whenever the aircraft engine is running smoothly and because, in the event that the aircraft engine becomes overloaded during takeoff or turbulence, the charged secondary power source can step in and supply the load. Findings A novel nonsingular terminal sliding mode voltage controller based on exponential reaching law is used to keep the load voltage constant under any of the aforementioned circumstances, and its performance is contrasted with a tuned PI controller on the basis of their respective transient and steady-state responses. The former gives a faster and better transient and steady-state response as compared to the latter. Originality/value This research gives a novel control scheme for incorporating an auxiliary power source, i.e. rechargeable battery, in more electric aircraft EPS. The battery is so implemented that it can get regeneratively charged when primary power supply is capable of handling an additional load, i.e. the battery. The charging and discharging of the battery is carried out in closed loop mode to ensure constant battery terminal voltage, constant battery current and constant load voltage as per the requirement. A novel sliding mode controller is used to improve transient and steady-state response of the system.

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Section: Introductionmentioning

confidence: 99%